Generation of 3D Turbine Blades for Automotive Organic Rankine Cycles: Mathematical and Computational Perspectives

: Organic Rankine cycle technology is gaining increasing interest as one of potent future waste heat recovery potential from internal combustion engines. The turbine is the component where power production takes place. Therefore, careful attention to the turbine design through mathematical and numerical simulations is required. As the rotor is the main component of the turbine, the generation of the 3D shape of the rotor blades and stator vanes is of great importance. Although several types of commercial software have been developed, such types are still expensive and time-consuming. In this study, detailed mathematical modelling was presented. To account for real gas properties, REFPROP software was used. Moreover, a detailed 3D CFD numerical analysis was presented to examine the nature of the ﬂow after generating the 3D shapes of the turbine. Moreover, ﬁnite element analysis was performed using various types of materials to obtain best-ﬁt material for the current application. As the turbine is part of a larger system (i.e., ORC system), the effects of its performance on the whole ORC system were discussed. The results showed that the ﬂow was smooth with no recirculation at the design point except at the last part of the suction surface where strong vortices were noticed. Despite the strong vortices, the mathematical model proved to be an effective and fast tool for the generation of the 3D shapes of turbine blades and vanes. The deviations between the 1D mean-line and 3D CFD in turbine efﬁciency and power output were 2.28% and 5.10%, respectively.


Introduction
Since the late 19th century, the average temperature on Earth has risen by approximately 0.9 • C because of the increased carbon dioxide (CO 2 ) and other man-made emissions to the atmosphere [1]. Besides the potential effects of CO 2 on global climate, transportation contributes to air pollution through mono-nitrogen oxides (NOx) and particulate matter (PM) emissions [2]. Transportation also contributes to global warming through CO 2 emissions which pose serious threats to public health. Among fuel-based applications, transportation burns most of the world's fuel, accounting for more than 28% of the total fuel consumption in the United States in 2018 [3] and more than 50% in the United Kingdom [4]. In addition, fuel prices have continually increased, from 1.191$/gallon in 1990 to 2.578$/gallon in the US [5]. Additionally, with the improvement of people's living standards, fuel consumption by the transportation sector will increase significantly [6]. These concerns necessitate the development of more efficient combustion engines to reduce fuel consumption and CO 2 emissions. In this regard, waste heat recovery (WHR) technology is one of the promising technologies in recovering the wasted fuel energy. with extensive CFD analyses and presented a maximum deviation of 5.02% in turbine power. Recently, Schuster et al. [46] presented an optimization model for ORC radial inflow turbines supported by CFD analyses. Their results showed sufficient agreement between 1D and CFD results. The brief review shows that CFD analysis allows the calculation of the flow field considering the viscous effects which are usually neglected in 1D model. Moreover, CFD can be applied as a reference of validation of mean-line models. Al Jubori et al. [47] developed a 1D mean-line model for designing a single stage radial turbine accompanied with CFD and experimental investigations. The results showed a tight race between the mean-line model and CFD. Flores et al. proposed a unidimensional design approach for a 10 kW radial inflow turbine. Both theoretical and numerical, proved to be in a good approximation.
In turbomachines, the rotor is the key component to produce work [48]. As small-scale radial inflow turbines are characterized with small mass flow rates, the turbine usually adopts radial blades at the inlet (zero-degree blade angle). Radial inlet blades are beneficial to avoid bending stresses. To increase the turbine work (enthalpy drop within the rotor), the tangential velocity at the rotor inlet should be increased according to the Euler equation as explained un the previous study [31]. Using backswept (non-radial) blades result in a positive relative angle which results in larger tangential velocity and hence, larger enthalpy drop. However, utilizing backswept blades results in higher bending stresses at the rotor leading edge. Failure is likely to occur when stresses are greater than the yield stress of the material of the rotor which may lead to catastrophic consequences both physically and economically [49]. The main challenge in the operation of turbine blades is the harsh operating environment (high temperature, high pressure and high rotational speed) in which thermal and structural stresses can result which further leads to creep and fatigue phenomenon and finally failure of the blades. Therefore, it is very essential to ensure that the turbine rotor can withstand the operating conditions of the flow and have adequate life in service. Therefore, structural evaluation of the turbine stage using FEA, which is widely applied in the analysis of engineering problems [50], is essential.
Research on bending stresses in ORC turbines is an area in which little available literature exists. However, enough studies were conducted aiming at analyzing bending stresses on air and steam turbines. Chen and Xie [51] created a finite element model of a low-pressure turbine blade to investigate the elastic-plastic conditions considering centrifugal load and aerodynamic load. Similarly, Fu [52] created a three-dimensional finite element model of the turbine blade to analyze the stress distribution of the turbine blade based on the thermo-elastic-plastic finite element under the conditions of centrifugal load and temperature load. Odabaee et al. [53] presented an FE analysis of a high-pressure ratio single stage radial-inflow turbine using ANSYS. The results showed a good agreement between the numerical and experimental data. Gad-el-Hak [54] presented a coupled CFD-FEA study with air as the working fluid and compared the results with experimental data. Similarly, Xie et al. [55] investigated the flow environment and blade thermal stresses using ANSYS with air as the working fluid. The authors considered both the thermal load and the centrifugal load. Banaszkiewicz [56] presented a methodology for analyzing both axial and radial stresses in steam turbine rotors and compared the proposed model with different methods available in the literature. Wang et al. [57] studied the effects of active thermal management on failure risk of disks and explores possible means for risk control. They concluded that the probability of disk failure increases with increasing the load cycle. They also concluded that the disk hub is the riskiest part and strongly influences the disk safety.
The brief literature review in the above paragraphs indicates the importance of developing a fast and accurate mathematical modelling of blade generation. Moreover, CFD and FE analyses are crucial steps for checking the turbine feasibility before sending the turbine for manufacturing and hence saving money. Moreover, ORC radial inflow turbines usually operate with the high-pressure ratio which necessities a careful examination of the flow environment, especially at the stator exit (due to the high Mach numbers at this region). In addition, ORC systems operate with high dense real fluids (organic fluids). Therefore, Mathematics 2020, 9, 50 5 of 30 proper modelling of the fluid properties should be considered. Very importantly, it can be noticed that the non-radial (backswept) blade in radial turbines is an area in which little available literature exists. Therefore, the proper mathematical modelling of backswept blades is presented. In addition, the thermodynamic parameters of the exhaust gas, such as mass flow rate and temperature can vary widely with time in heat sources such as ICEs. This variance causes heat sources to become unstable and uncontrollable. Therefore, the performance behaviour of the 3D shaped turbine when running at off-design rotational speeds and pressure ratios should be accurately predicted. In addition, the radial inflow turbine is part of a larger system which the ORC in the current study. Therefore, it is of great importance to analyze the performance of the ORC system under various operating conditions of the turbine. Moreover, the brief literature review also indicates the success of CFD discipline in validating mean-line models. This study aims at filling these gaps by providing a complete 3D-shape generation and CFD-FE analyses at design and off-design conditions. Figure 1 presents a flowchart of the current study. blades is presented. In addition, the thermodynamic parameters of the exhaust gas, such as mass flow rate and temperature can vary widely with time in heat sources such as ICEs. This variance causes heat sources to become unstable and uncontrollable. Therefore, the performance behaviour of the 3D shaped turbine when running at off-design rotational speeds and pressure ratios should be accurately predicted. In addition, the radial inflow turbine is part of a larger system which the ORC in the current study. Therefore, it is of great importance to analyze the performance of the ORC system under various operating conditions of the turbine. Moreover, the brief literature review also indicates the success of CFD discipline in validating mean-line models. This study aims at filling these gaps by providing a complete 3D-shape generation and CFD-FE analyses at design and off-design conditions. Figure 1 presents a flowchart of the current study.

Organic Rankine Cycle and Radial Inflow Turbine
Typical ORC consists of four main components, namely: evaporator, turbine, condenser and pump, Figure 2. The working fluid is vaporized in the evaporator (7 to 1) and then expanded in the turbine (1 to 5) that drives a generator to produce electricity. Finally, the working fluid is condensed at constant pressure (5 to 6) and pumped again (6 to 7) to the evaporator. Points 1 to 5 represent the turbine stage as shown in Figure 3.
The detailed description of the ORC system and internal combustion engine can be found in the previous studies of the authors [14,15]. Three different radial inflow turbines were designed in the previous study [31], a separate turbine for each engine operating point. In this study, the operating conditions of the exhaust gas at P3 is selected as the heat source of the current study. In addition, the geometry of the radial inflow turbine of P3 is considered in the current simulation since P3 is considered as the optimum engine point. The detailed geometry of the P3 turbine can be seen in [31]. Table 1 presents the input conditions for the mean-line model, which are used as the input conditions for the current CFD study. Table 2 summarizes the basic equations in ORC and radial inflow turbine applied in the current study.

Organic Rankine Cycle and Radial Inflow Turbine
Typical ORC consists of four main components, namely: evaporator, turbine, condenser and pump, Figure 2. The working fluid is vaporized in the evaporator (7 to 1) and then expanded in the turbine (1 to 5) that drives a generator to produce electricity. Finally, the working fluid is condensed at constant pressure (5 to 6) and pumped again (6 to 7) to the evaporator. Points 1 to 5 represent the turbine stage as shown in Figure 3.     The detailed description of the ORC system and internal combustion engine can be found in the previous studies of the authors [14,15]. Three different radial inflow turbines were designed in the previous study [31], a separate turbine for each engine operating point. In this study, the operating conditions of the exhaust gas at P3 is selected as the heat source of the current study. In addition, the geometry of the radial inflow turbine of P3 is considered in the current simulation since P3 is considered as the optimum engine point. The detailed geometry of the P3 turbine can be seen in [31]. Table 1 presents the input  conditions for the mean-line model, which are used as the input conditions for the current  CFD study. Table 2 summarizes the basic equations in ORC and radial inflow turbine applied in the current study.

Equation Equation # Comments
Q in is the heat transfer in the evaporator in kW. h out and h in are enthalpies in kJ/kg at exit and inlet of the evaporator. m . w f is the working fluid mass flow rate in kg/s.
W pump is the power consumed by pump in kW. P out , P in , ρ in and η pump are outlet pressure, inlet pressure, inlet density and pump efficiency.
∆h act is the actual enthalpy drop within the turbine stage.
W out is the turbine power output in kW. U and C θ are the tip and tangential velocities.
W net is the cycle net power in kW.

Generation of 3D Model
This section presents the construction of the 3D model of the turbine stage, namely, stator and rotor. The volute is excluded since the losses are extremely small compared to the losses in the stator and rotor. Although the 3D generation of turbine blades and vanes have extensively explained in the literature such as in Aungier [27]. However, these equations are related to ideal gas equations of state. In the current study, real gas properties of the fluid have been accounted for using REFPROP [35].

Stator Model
The inlet and exit vane angles are 76.335 • and 66.75 • , respectively, as obtained from the turbine mean-line model [31]. The distribution of thickness is performed according to the procedure proposed by Aungier [27]. The thickness distribution is performed on a parabolic-arc camber-line as outlined in Aungier [27]. The governing equation for a parabolicarc camber-line is shown in Equation (7). The coordinate (x,y) is shown in Figure 4. g and b are the location and value of maximum camber along the chord, respectively. x 2 and x 3 are camber-line angles at inlet and exit, respectively.  The stator geometrical parameters can then be obtained based on the value of . The required parameters are chord length , maximum camber and its location . The leading 2 and trailing 3 edge blade angles can be obtained using Equations (8) and (9).The angle of the blade comber-line is then the sum of the two-blade angles.
Aungier [27] proposed several equations to calculate the blade thickness at any location along the camber-line as shown in Equations (10)- (14).
and are the maximum blade thickness and its location, respectively. The leading 2 and trailing 3 edge blade thicknesses can be obtained from the mean-line model. Figure 5 depicts the distributions of vane angles and thickness and Figure 6 shows the developed 3D model of the nozzle. The stator geometrical parameters can then be obtained based on the value of χ. The required parameters are chord length c v , maximum camber b and its location g. The leading χ 2 and trailing χ 3 edge blade angles can be obtained using Equations (8) and (9). The angle of the blade comber-line is then the sum of the two-blade angles.
Aungier [27] proposed several equations to calculate the blade thickness at any location along the camber-line as shown in Equations (10)- (14).
t max and d are the maximum blade thickness and its location, respectively. The leading t 2 and trailing t 3 edge blade thicknesses can be obtained from the mean-line model. Figure 5 depicts the distributions of vane angles and thickness and Figure 6 shows the developed 3D model of the nozzle.

Rotor Model
For the construction of the rotor, three geometrical aspects were constructed to generate the full rotor blade. These aspects are meridional profiles, blade angle distribution and thickness distribution.
The 2D rotor meridional profiles (end-wall contours) are defined by applying the methodology presented in Aungier [27]. In this study, a quarter ellipse is applied to define the three meridional profiles, namely, hub, mid and shroud, as shown in Figure 7. As explained in the previous study [31], 4 , 4 , and are the inlet blade height, inlet blade radius and axial length, respectively.

Rotor Model
For the construction of the rotor, three geometrical aspects were constructed to generate the full rotor blade. These aspects are meridional profiles, blade angle distribution and thickness distribution.
The 2D rotor meridional profiles (end-wall contours) are defined by applying the methodology presented in Aungier [27]. In this study, a quarter ellipse is applied to define the three meridional profiles, namely, hub, mid and shroud, as shown in Figure 7. As explained in the previous study [31], 4 , 4 , and are the inlet blade height, inlet blade radius and axial length, respectively.

Rotor Model
For the construction of the rotor, three geometrical aspects were constructed to generate the full rotor blade. These aspects are meridional profiles, blade angle distribution and thickness distribution.
The 2D rotor meridional profiles (end-wall contours) are defined by applying the methodology presented in Aungier [27]. In this study, a quarter ellipse is applied to define the three meridional profiles, namely, hub, mid and shroud, as shown in Figure 7. As explained in the previous study [31], b 4 , r 4 , and z are the inlet blade height, inlet blade radius and axial length, respectively.
In the current study, the blade is not radially fibred. The blade distribution of blade angles is determined by the numerical integration of Equations (15) and (16), where m is the meridional distance along the Z − R contour, Figure 7. The coefficients A to F are summarized in Table 3. Equation (15) is the blade camber-line along the shroud contour, whereas Equation (16) is the camber-line along the hub contour. The distribution of the blade angle is shown in Figure 8.
θ(m) = Dm + Em 2 + Fm 4 (16) Table 3. Definitions of blade thickness coefficients. In the current study, the blade is not radially fibred. The blade distribution of blade angles is determined by the numerical integration of Equations (15) and (16), where is the meridional distance along the − contour, Figure 7. The coefficients to are summarized in Table 3. Equation (15) is the blade camber-line along the shroud contour, whereas Equation (16) is the camberline along the hub contour. The distribution of the blade angle is shown in Figure 8.  Blade thickness is distributed in three regions, namely, leading-edge, meridional profile, and trailing edge. As will be shown later, blade root is the location where stress is the highest. Therefore, this region must be the thickest to improve the weight distribution of the blade. To obtain thick root, the blade is tapered from hub to tip. Thicknesses at inlet and exit of the leading edge and trailing edge, Figure 9, are calculated using Equations (17)- (20) [27,58]. 5 and 5ℎ are the tip and hub exit thicknesses and obtained from the mean-line model [31]. In the current study, the blade thickness at the hub ( ℎ ) is obtained using Equation (20) to keep thicker root. Figure 9 also presents the developed 3D rotor blade.  Blade thickness is distributed in three regions, namely, leading-edge, meridional profile, and trailing edge. As will be shown later, blade root is the location where stress is the highest. Therefore, this region must be the thickest to improve the weight distribution of the blade. To obtain thick root, the blade is tapered from hub to tip. Thicknesses at inlet and exit of the leading edge and trailing edge, Figure 9, are calculated using Equations (17)-(20) [27,58]. t 5t and t 5h are the tip and hub exit thicknesses and obtained from the mean-line model [31]. In the current study, the blade thickness at the hub (LE h ) is obtained using Equation (20) to keep thicker root. Figure 9 also presents the developed 3D rotor blade.

Computational Fluid Dynamics (CFD)
Before sending the turbine out for manufacturing, a complete CFD study of the full turbine stage is accomplished using ANSYS CFX [59]. In this section, the setup of the turbulence model, physical domain, boundary conditions and the organic fluid (NOVEC 649) are presented. A grid-independent study is also performed to ensure that the results are independent of the number of nodes. Figure 10 presents the flowchart of the adopted numerical analysis and Figure 11 presents a 3D view of a radial turbine stage and boundary conditions.

Computational Fluid Dynamics (CFD)
Before sending the turbine out for manufacturing, a complete CFD study of the full turbine stage is accomplished using ANSYS CFX [59]. In this section, the setup of the turbulence model, physical domain, boundary conditions and the organic fluid (NOVEC 649) are presented. A grid-independent study is also performed to ensure that the results are independent of the number of nodes. Figure 10 presents the flowchart of the adopted numerical analysis and Figure 11 presents a 3D view of a radial turbine stage and boundary conditions.

Computational Fluid Dynamics (CFD)
Before sending the turbine out for manufacturing, a complete CFD study of the full turbine stage is accomplished using ANSYS CFX [59]. In this section, the setup of the turbulence model, physical domain, boundary conditions and the organic fluid (NOVEC 649) are presented. A grid-independent study is also performed to ensure that the results are independent of the number of nodes. Figure 10 presents the flowchart of the adopted numerical analysis and Figure 11 presents a 3D view of a radial turbine stage and boundary conditions.

Grid Generation of the Fluid Model
In the current study, the solid parts are imported to ANSYS TurboGrid to generate the appropriate meshes, as shown in Figure 12. An automatic topology (ATM Optimised) is selected so ANSYS TurboGrid could select the suitable topology for the blade passage. If the mesh quality at a certain region, such as the rotor leading edge, is poor, then the control points can be adjusted by the user to solve the problem. Figure 13 presents the sensitivity analysis of the element number of the passage to the turbine isentropic efficiency and the static exit temperature at the rotor exit.

Grid Generation of the Fluid Model
In the current study, the solid parts are imported to ANSYS TurboGrid to generate the appropriate meshes, as shown in Figure 12. An automatic topology (ATM Optimised) is selected so ANSYS TurboGrid could select the suitable topology for the blade passage. If the mesh quality at a certain region, such as the rotor leading edge, is poor, then the control points can be adjusted by the user to solve the problem. Figure 13 presents the sensitivity analysis of the element number of the passage to the turbine isentropic efficiency and the static exit temperature at the rotor exit.

Turbulence Model, Physical Domain, Boundary Conditions, and Governing Equations
During the past two decades, two main turbulence models have been developed: k − model, which is based on the turbulence dissipation rate , and k − ω model, which is based on the specific dissipation rate ω. Fajardo [60] indicated that k − ω is more accurate than k − in computing the near-wall layers. However, k − converges faster and is robust with real gas applications [36]. Menter [61] developed less complex and less computationally expensive model called shear stress transport (SST) model. The SST model applies the k − ω model to capture the near-wall region accurately and switches to the k − model in the free-stream to avoid the sensitivity of k − ω to the effects of freestream turbulence. Menter's predicted results using the SST model are in good agreement with the experimental data. Therefore, k − ω SST is applied in the current analysis for both the design point and off-design analyses.
To reduce computational time, a single flow passage for the rotor and stator is simulated and rotational periodicity is applied by setting an appropriate pitch ratio at the interface between the stator and rotor. Different meshing is required because of the different components considered in the simulation. Therefore, the position of the grid nodes in one domain may not match those in the other domains. The general grid interface is applied to avoid such non-matching interface. Domain interfaces are required because a change in reference frame between stationary (stator) and rotating (rotor) domains occurs. ANSYS CFX has two main interfaces, namely, mixing plane and frozen rotor. The main difference between the two interfaces is that the mixing plane applies the average qualities on the interface for upstream and downstream components; therefore, it is applied in the current study. Figure 14 shows the modelled components with the corresponding fluid domains.

Finite Element Analysis (FEA)
Rotors in radial inflow turbines experience aerodynamic and mechanical loads. Therefore, it is essential to investigate the mechanical integrity of such components. In addition, rotor blades in conventional radial turbines are usually radially fibered (zero inlet blade angle) to minimize bending stresses. However, since backswept blades are used in the current study, the centrifugal stresses at the leading edge must be analyzed and checked carefully. The purpose of the current analysis is to identify the limits of blade tip deformation and total von Mises stresses using ANSYS Static Structure. The resulted maximum stress and displacement should not exceed the material tensile strength and the running tip clearance (0.6 mm [31]). The running tip clearance is the clearance between the rotor and the casing. Figure 15 shows the specified fixed support and direction of rotation.  Navier-Stokes equations that are discretized by a finite volume approach are integrated into the current study. These equations are applied to solve for velocity, pressure and temperature associated with a moving fluid. Navier-Stokes equations describe the conservation of mass, momentum and energy, as shown in Equations (21)

Finite Element Analysis (FEA)
Rotors in radial inflow turbines experience aerodynamic and mechanical loads. Therefore, it is essential to investigate the mechanical integrity of such components. In addition, rotor blades in conventional radial turbines are usually radially fibered (zero inlet blade angle) to minimize bending stresses. However, since backswept blades are used in the current study, the centrifugal stresses at the leading edge must be analyzed and checked carefully. The purpose of the current analysis is to identify the limits of blade tip deformation and total von Mises stresses using ANSYS Static Structure. The resulted maximum stress and displacement should not exceed the material tensile strength and the running tip clearance (0.6 mm [31]). The running tip clearance is the clearance between the rotor and the casing. Figure 15 shows the specified fixed support and direction of rotation.
conventional radial turbines are usually radially fibered (zero inlet blade angle) to minimize bending stresses. However, since backswept blades are used in the current study, the centrifugal stresses at the leading edge must be analyzed and checked carefully. The purpose of the current analysis is to identify the limits of blade tip deformation and total von Mises stresses using ANSYS Static Structure. The resulted maximum stress and displacement should not exceed the material tensile strength and the running tip clearance (0.6 mm [31]). The running tip clearance is the clearance between the rotor and the casing. Figure 15 shows the specified fixed support and direction of rotation.

Material Selection
Various types of materials are investigated. Fullcure 720 which is a multipurpose Polymer is considered as a cost-effective and efficient way for turbine manufacturing [62]. In other studies [63,64], rotor blades are made of the aluminium alloy due to its light weight, ease of machining, strength-to-weight ratio and corrosion resistance. In Kaczmarczyk et al. [65], rotor blades were made of stainless steel to provide adequate heat compensation and minimize the propagation of vibrations of the machine to the entire installation. Moreover, rotors made of Titanium alloy are used in some studies such as [66,67] to provide high mechanical resilience. Table 4 presents the properties of considered types of materials.

Mesh Generation and Sensitivity Analyses
Like the CFD study, the independency study for FEA is carried out using different element sizes as shown in Table 5. Several meshes are generated with different node numbers. The deviation between two executive operations decreases till reaches 0.33% in von Mises stress and 0.002% in total deformation between operation 8 and operation 9. Therefore, the mesh in operation 8 is selected as the grid independence values. The mesh of the turbine rotor is generated with mapped face/tetrahedrons mesh type as shown in Figure 16.   Table 5.

Validation of the Numerical Analysis
Although CFD is a powerful and robust simulation tool, it still needs to be verified experimentally. The turbine model has already been manufactured and tested as shown in the previous studies of the authors [14,15]. Unfortunately, the test has been run at highly off-design conditions due to the technical issue of the engine dynamometer. Therefore, the test results cannot be directly used to verify the proposed mean-line model. However, the test results can be applied to validate the numerical analysis. Therefore, the test results of the study [14] are used to validate the CFD results in the current study. Figure 17 shows a comparison between the CFD and test results at 20,000 rpm for different pressure ratios. As seen in the figure, the CFD numerical results show very good agreement with the test results. A maximum deviation of 3.23% is noticed at a pressure ratio of 5.4, while the average deviation is 2.67%. Therefore, the current CFD model can be applied more confidently as a validation model for the proposed mean-line model. Although CFD is a powerful and robust simulation tool, it still needs to be verified experimentally. The turbine model has already been manufactured and tested as shown in the previous studies of the authors [14,15]. Unfortunately, the test has been run at highly off-design conditions due to the technical issue of the engine dynamometer. Therefore, the test results cannot be directly used to verify the proposed mean-line model. However, the test results can be applied to validate the numerical analysis. Therefore, the test results of the study [14] are used to validate the CFD results in the current study. Figure 17 shows a comparison between the CFD and test results at 20,000 rpm for different pressure ratios. As seen in the figure, the CFD numerical results show very good agreement with the test results. A maximum deviation of 3.23% is noticed at a pressure ratio of 5.4, while the average deviation is 2.67%. Therefore, the current CFD model can be applied more confidently as a validation model for the proposed mean-line model.

Results at Design Point
The results in this section are based on the boundary conditions presented in Table 1. Figure 18 depicts the contours of the total pressure and temperature through the turbine stage at a span of 50%. From the inlet of the stator to the exit of the rotor, the pressure decreases from 900 kPa to 130 kPa, while the temperature decreases from 471 K to 448 K. The pressure drop through the turbine stage satisfies the expansion requirement of the design point. However, the high-pressure ratio results in high Mach number values at the stator exit and high loading on the turbine blades, resulting in higher friction losses and, therefore, lower efficiency, as shown in Figures 19 and 20. However, this high value of Mach number is expected owing to the sudden expansion of flow at this area. Mach number is also influenced by the operating mass flow rate of the working fluid and the throat opening of the stator vanes. The pressure drop across the stator vanes is used to accelerate the organic fluid as it moves towards the circumferential direction. However, the pressure loss across the stator vane is significantly high and results in shock waves. Through the rotor blades, the values of Mach number are below unity. Figure 19 also shows the location of the shock waves, where a violent change in the pressure gradient occurred in the throat area. It is worth mentioning that the modelling approach accounting for the high Mach number values is presented in [31].

Results at Design Point
The results in this section are based on the boundary conditions presented in Table 1. Figure 18 depicts the contours of the total pressure and temperature through the turbine stage at a span of 50%. From the inlet of the stator to the exit of the rotor, the pressure decreases from 900 kPa to 130 kPa, while the temperature decreases from 471 K to 448 K. The pressure drop through the turbine stage satisfies the expansion requirement of the design point.

Results at Design Point
The results in this section are based on the boundary conditions presented in Table 1. Figure 18 depicts the contours of the total pressure and temperature through the turbine stage at a span of 50%. From the inlet of the stator to the exit of the rotor, the pressure decreases from 900 kPa to 130 kPa, while the temperature decreases from 471 K to 448 K. The pressure drop through the turbine stage satisfies the expansion requirement of the design point. However, the high-pressure ratio results in high Mach number values at the stator exit and high loading on the turbine blades, resulting in higher friction losses and, therefore, lower efficiency, as shown in Figures 19 and 20. However, this high value of Mach number is expected owing to the sudden expansion of flow at this area. Mach number is also influenced by the operating mass flow rate of the working fluid and the throat opening of the stator vanes. The pressure drop across the stator vanes is used to accelerate the organic fluid as it moves towards the circumferential direction. However, the pressure loss across the stator vane is significantly high and results in shock waves. Through the rotor blades, the values of Mach number are below unity. Figure 19 also shows the location of the shock waves, where a violent change in the pressure gradient occurred in the throat area. It is worth mentioning that the modelling approach accounting for the high Mach number values is presented in [31]. However, the high-pressure ratio results in high Mach number values at the stator exit and high loading on the turbine blades, resulting in higher friction losses and, therefore, lower efficiency, as shown in Figures 19 and 20. However, this high value of Mach number is expected owing to the sudden expansion of flow at this area. Mach number is also influenced by the operating mass flow rate of the working fluid and the throat opening of the stator vanes. The pressure drop across the stator vanes is used to accelerate the organic fluid as it moves towards the circumferential direction. However, the pressure loss across the stator vane is significantly high and results in shock waves. Through the rotor blades, the values of Mach number are below unity. Figure 19 also shows the location of the shock waves, where a violent change in the pressure gradient occurred in the throat area. It is worth mentioning that the modelling approach accounting for the high Mach number values is presented in [31].   Flow recirculation is a common phenomenon in ORC turbines due to the high loading on the turbine blades. Figure 21 portrays the flow streamlines through the turbine stage. The fluid flows smoothly, and the velocity is homogenously distributed along the blade without any flow reversals at a span of 90%. The flow is smooth at the leading edge at a span of 50%, signifying that the incidence angle at the rotor leading edge is optimum. However, flow recirculation is observed downstream of the rotor blades at the suction side, resulting in a moderate level of diffusion at this area. Such flow recirculation occurs due to the difference between the actual and idealised flows in the blade passage. The fluid velocities in the end-wall boundary layers are lower than those of the mainstream, thereby causing the fluid to turn sharply and resulting in flow vortices. This indicates that this part of the blade needs to be further optimized.    Flow recirculation is a common phenomenon in ORC turbines due to the high loading on the turbine blades. Figure 21 portrays the flow streamlines through the turbine stage. The fluid flows smoothly, and the velocity is homogenously distributed along the blade without any flow reversals at a span of 90%. The flow is smooth at the leading edge at a span of 50%, signifying that the incidence angle at the rotor leading edge is optimum. However, flow recirculation is observed downstream of the rotor blades at the suction side, resulting in a moderate level of diffusion at this area. Such flow recirculation occurs due to the difference between the actual and idealised flows in the blade passage. The fluid velocities in the end-wall boundary layers are lower than those of the mainstream, thereby causing the fluid to turn sharply and resulting in flow vortices. This indicates that this part of the blade needs to be further optimized.  Figure 20 shows the blade loading. As the enclosed area by the pressure and suction surfaces increases, the turbine produces higher power output (net torque). At the three profiles, blade loading is uniform in the pressure and suction surfaces. The lower pressure values in the suction surface correspond to the location of the throat, where the area is the lowest and speed is the highest.
Flow recirculation is a common phenomenon in ORC turbines due to the high loading on the turbine blades. Figure 21 portrays the flow streamlines through the turbine stage. The fluid flows smoothly, and the velocity is homogenously distributed along the blade without any flow reversals at a span of 90%. The flow is smooth at the leading edge at a span of 50%, signifying that the incidence angle at the rotor leading edge is optimum. However, flow recirculation is observed downstream of the rotor blades at the suction side, resulting in a moderate level of diffusion at this area. Such flow recirculation occurs due to the difference between the actual and idealised flows in the blade passage. The fluid velocities in the end-wall boundary layers are lower than those of the mainstream, thereby causing the fluid to turn sharply and resulting in flow vortices. This indicates that this part of the blade needs to be further optimized.

Results at Off-Design Points
To evaluate the performance of the turbine at off-design conditions, the pressure ratio is varied from 3 to 6.9, and the turbine inlet temperature is varied from 400 K to 471.55 K, for two-speed lines (30,000 rpm and 40,000 rpm).

 Different Pressure ratios and Rotational Speeds
Mach number of the flow crucially influences the aerodynamic behaviour of turbines. It depends on the rotational speed, pressure ratio through the stage, and speed of sound of the working fluid. The results in the previous sub-section indicated that the flow choked at the interspace (the gap between stator and rotor). This means that the turbine operates at a fixed mass flow rate, regardless of the pressure ratio. This, in turn, results in shock waves and performance deterioration of the turbine. However, higher values of specific power are achieved at choked flow. Therefore, the turbine is designed to operate at choked conditions based on the simulation of the thermodynamic cycle. In the current CFD simulations, pressure ratio and turbine speed are under the control of the designer. For each run, they are changed and the simulation is re-run as shown in the next paragraphs. Figure 22 presents temperature distribution, Mach number distribution, and velocity streamlines through the turbine stage for different pressure ratios and rotational speeds. At PR = 3 and 40,000 rpm, Figure 22a clearly shows that there is no choking at the interspace between the stator exit and rotor inlet, and the Mach number at this region is lower than 0.93. However, running the turbine at off-design points results in a non-optimum turbine performance which results in deficient flow as depicted by the velocity streamlines in the figure. At 50% of the rotor blade, a flow recirculation is formed at the rotor leading edge in the pressure side (Figure 22a), because of the nonoptimum incidence angle, before mixing out with the mainstream. The pressure ratio is then increased to 4.5 while the rotational speed is maintained constant. As shown in Figure 22b, Mach number increases significantly compared to PR = 3, reaching sonic condition (Ma = 1). Moreover, strong vortices are created downstream of the blade suction surface.

Results at Off-Design Points
To evaluate the performance of the turbine at off-design conditions, the pressure ratio is varied from 3 to 6.9, and the turbine inlet temperature is varied from 400 K to 471.55 K, for two-speed lines (30,000 rpm and 40,000 rpm).

• Different Pressure ratios and Rotational Speeds
Mach number of the flow crucially influences the aerodynamic behaviour of turbines. It depends on the rotational speed, pressure ratio through the stage, and speed of sound of the working fluid. The results in the previous sub-section indicated that the flow choked at the interspace (the gap between stator and rotor). This means that the turbine operates at a fixed mass flow rate, regardless of the pressure ratio. This, in turn, results in shock waves and performance deterioration of the turbine. However, higher values of specific power are achieved at choked flow. Therefore, the turbine is designed to operate at choked conditions based on the simulation of the thermodynamic cycle. In the current CFD simulations, pressure ratio and turbine speed are under the control of the designer. For each run, they are changed and the simulation is re-run as shown in the next paragraphs. Figure 22 presents temperature distribution, Mach number distribution, and velocity streamlines through the turbine stage for different pressure ratios and rotational speeds. At PR = 3 and 40,000 rpm, Figure 22a clearly shows that there is no choking at the interspace between the stator exit and rotor inlet, and the Mach number at this region is lower than 0.93. However, running the turbine at off-design points results in a non-optimum turbine performance which results in deficient flow as depicted by the velocity streamlines in the figure. At 50% of the rotor blade, a flow recirculation is formed at the rotor leading edge in the pressure side (Figure 22a), because of the non-optimum incidence angle, before mixing out with the mainstream. The pressure ratio is then increased to 4.5 while the rotational speed is maintained constant. As shown in Figure 22b, Mach number increases significantly compared to PR = 3, reaching sonic condition (Ma = 1). Moreover, strong vortices are created downstream of the blade suction surface.
The simulation is then re-run again at two different pressure ratios (PR = 3 and PR = 6.9) with 30,000 rpm as shown in Figure 22c,d. It is known that turbine size is inversely proportional to the turbine speed. Therefore, the turbine size with 30,000 rpm is considered overestimated which makes the flow does not follow the blade passage properly as shown in Figure 22c,d. Mach numbers in these cases are higher than that in Figure 22a,b, although they have the same pressure ratio. However, this is justified by the higher absolute velocities. Figure 22d presents the results at PR = 6.9 and 30,000 rpm. Compared to the 40,000 rpm (Figure 22a), Mach numbers are higher due to the higher velocities as shown by the streamlines. In addition, the flow is more uniform in the 40,000 rpm case while strong vorticity is created in the 30,000 rpm. The simulation is then re-run again at two different pressure ratios ( = 3 = 6.9) with 30,000 rpm as shown in Figure 22c,d. It is known that turbine size is inversely proportional to the turbine speed. Therefore, the turbine size with 30,000 rpm is considered overestimated which makes the flow does not follow the blade passage properly as shown in Figure 22c,d. Mach numbers in these cases are higher than that in Figure 22a,b, although they have the same pressure ratio. However, this is justified by the higher absolute velocities. Figure 22d presents the results at = 6.9 and 30,000 rpm. Compared to the 40,000 rpm (Figure 22a), Mach numbers are higher due to the higher velocities as shown by the streamlines. In addition, the flow is more uniform in the 40,000 rpm case while strong vorticity is created in the 30,000 rpm.
A parametric study is performed using ANSYS CFX to evaluate the turbine isentropic efficiency and power output at different pressure ratios and rotational speeds. The results are presented in Figure 23. It is clearly shown that the turbine operates more efficiently at off-design speeds 30,000 rpm than the design point 40,000 rpm at low pressure ratios. However, this is expected since the turbine is designed to operate under high-pressure ratios, which clarifies the high turbine efficiencies at high-pressure ratios. Figure 23 also shows that turbine efficiency increases with increasing the pressure ratio, reaching a maximum value and then decreases. The turbine power, on the other hand, is a function of the enthalpy drop and turbine speed, Equation (4). As shown in Figure 23, turbine power increases significantly with increasing the pressure ratio due to the increased enthalpy drop. A parametric study is performed using ANSYS CFX to evaluate the turbine isentropic efficiency and power output at different pressure ratios and rotational speeds. The results are presented in Figure 23. It is clearly shown that the turbine operates more efficiently at off-design speeds 30,000 rpm than the design point 40,000 rpm at low pressure ratios. However, this is expected since the turbine is designed to operate under high-pressure ratios, which clarifies the high turbine efficiencies at high-pressure ratios. Figure 23 also shows that turbine efficiency increases with increasing the pressure ratio, reaching a maximum value and then decreases. The turbine power, on the other hand, is a function of the enthalpy drop and turbine speed, Equation (4). As shown in Figure 23, turbine power increases significantly with increasing the pressure ratio due to the increased enthalpy drop.

• Different Turbine Inlet Temperatures
Temperatures of exhaust gases in an internal combustion engine vary considerably according to vehicle's operation. As mentioned in the previous study [14], the turbine inlet temperature increases linearly with increasing heat source temperature. Therefore, turbine performance is also investigated at different inlet temperatures and rotational speeds in the current study.
Like the design point, flow vortices are noticed downstream of the rotor blades at the suction side for all off-design points, as shown in Figure 24. This indicates that this part of the blade is not optimum. Figure 24 also indicates that flow pattern improves with increasing turbine inlet temperature for the same rotational speed. The closer inlet temperature gets to design point, the more uniform flow results as shown in Figure 24a,b. At off-design rotational speed (30,000 rpm), the flow is more uniform than that in design point speed (40,000) for low temperatures due to low fluid densities at the stator exit. In contrast, flow pattern improves better with 40,000 rpm than 30,000 rpm at high temperatures since the fluid density at the stator exit is 33% lower.

 Different Turbine Inlet Temperatures
Temperatures of exhaust gases in an internal combustion engine vary considerably according to vehicle's operation. As mentioned in the previous study [14], the turbine inlet temperature increases linearly with increasing heat source temperature. Therefore, turbine performance is also investigated at different inlet temperatures and rotational speeds in the current study.
Like the design point, flow vortices are noticed downstream of the rotor blades at the suction side for all off-design points, as shown in Figure 24. This indicates that this part of the blade is not optimum. Figure 24 also indicates that flow pattern improves with increasing turbine inlet temperature for the same rotational speed. The closer inlet temperature gets to design point, the more uniform flow results as shown in Figure24a,b. At off-design rotational speed (30,000 rpm), the flow is more uniform than that in design point speed (40,000) for low temperatures due to low fluid densities at the stator exit. In contrast, flow pattern improves better with 40,000 rpm than 30,000 rpm at high temperatures since the fluid density at the stator exit is 33% lower. Figure 24 shows also that the Mach number at stator exit increases with increasing the turbine inlet temperature for the same rotational speed. Mach number is a function of flow absolute velocity and speed of sound. As temperature increases, flow velocity increases resulting in higher Mach number. Compared to Figure 24d, Mach number in Figure 24c decreases by 19.74% since the absolute velocity decreases by 31.87%. Figure 24 shows also that Mach number decreases with increasing rotational speed for the same temperature and pressure ratio, according to the flow velocity. At 30,000 rpm (Figure 24c), the flow velocity at the stator exit is 20.80% higher than that at 40,000 rpm ( Figure  24a). The relationship between flow velocity and rotational speed is explained in the velocity triangle in a previous study [31]. Lowering the rotor rotational speed results in higher tangential velocity in the interspace which results in higher absolute velocity, and consequently, higher Mach number. Turbine performance is explored at different turbine inlet temperatures and rotational speeds as shown in Figure 25. For the design point speed, turbine efficiency increases with increasing inlet temperature, reaching a maximum value at the design point inlet temperature (471.55 K). For the 30,000 rpm, turbine efficiency decreases linearly with increasing inlet temperature. At 430 K, enthalpy  Figure 24 shows also that the Mach number at stator exit increases with increasing the turbine inlet temperature for the same rotational speed. Mach number is a function of flow absolute velocity and speed of sound. As temperature increases, flow velocity increases resulting in higher Mach number. Compared to Figure 24d, Mach number in Figure 24c decreases by 19.74% since the absolute velocity decreases by 31.87%. Figure 24 shows also that Mach number decreases with increasing rotational speed for the same temperature and pressure ratio, according to the flow velocity. At 30,000 rpm (Figure 24c), the flow velocity at the stator exit is 20.80% higher than that at 40,000 rpm (Figure 24a). The relationship between flow velocity and rotational speed is explained in the velocity triangle in a previous study [31]. Lowering the rotor rotational speed results in higher tangential velocity in the interspace which results in higher absolute velocity, and consequently, higher Mach number.
Turbine performance is explored at different turbine inlet temperatures and rotational speeds as shown in Figure 25. For the design point speed, turbine efficiency increases with increasing inlet temperature, reaching a maximum value at the design point inlet temperature (471.55 K). For the 30,000 rpm, turbine efficiency decreases linearly with increasing inlet temperature. At 430 K, enthalpy drop with 30,000 rpm is higher than that in 40,000 rpm clarifying the higher efficiency and power output at this point. As the temperature increase, the enthalpy drop with 40,000 rpm becomes higher which results in higher turbine efficiency and power output. Figure 25 shows also that turbine efficiency decreases with increasing turbine inlet temperature for 30,000 rpm. This is due to the flow deficiency downstream of the rotor blades at the suction side. Although flow vortices are created in both cases (Figure 24c,d), the latter results in lower flow velocity (compared to the upstream flow) which increases the strength of the vortices and consequently lower turbine efficiency.

Comparison between the Mean-Line Model and CFD Results
One of the main aims of the CFD simulation at the design point is to validate the mean-line model as presented in Table 6. ANSYS provides a summary of the mass averaged solution variables (total pressure, total temperature and static temperature), area-averaged solution variables (static pressure and velocities), and derived quantities (as total to static efficiency and power output). These variables are computed at the inlet and exit of each component of the turbine, as shown in Table 6. Such variables are selected as the comparison variables between the 1D and 3D simulations.
As seen in Table 6, the majority of the 1D parameters are in excellent agreement with 3D simulations. Maximum deviations of 15.39% can be noticed in rotor exit absolute velocity. This is justified by the assumption of the isentropic flow through the stator as shown in [31]. As a result, at

Comparison between the Mean-Line Model and CFD Results
One of the main aims of the CFD simulation at the design point is to validate the mean-line model as presented in Table 6. ANSYS provides a summary of the mass averaged solution variables (total pressure, total temperature and static temperature), area-averaged solution variables (static pressure and velocities), and derived quantities (as total to static efficiency and power output). These variables are computed at the inlet and exit of each component of the turbine, as shown in Table 6. Such variables are selected as the comparison variables between the 1D and 3D simulations. As seen in Table 6, the majority of the 1D parameters are in excellent agreement with 3D simulations. Maximum deviations of 15.39% can be noticed in rotor exit absolute velocity. This is justified by the assumption of the isentropic flow through the stator as shown in [31]. As a result, at a fixed mass flow rate, the meridional velocity, C m4 , increases to conserve the mass flow rate. This increase in the meridional velocity results in higher absolute velocity, and consequently, higher deviation in rotor relative velocity, W 4 . This is not the case in the CFD analysis where the stagnation pressure drop in the stator is considered; therefore, the flow is not isentropic as shown in Figure 18. The deviation in the turbine efficiency and work output are 2.28% and 5.10%, respectively. Overall, the CFD results indicate that the proposed 1D design methodology can accurately predict the turbine performance and flow features for high-pressure ratio ORC radial inflow turbines.

Results of ORC System at Design and Off-Design Conditions
The effects of turbine operating conditions on cycle thermal efficiency and net power are also investigated as shown in Figures 26 and 27. Increasing the pressure ratio results in higher cycle network due to the increased turbine power as discussed in Figure 23 Similarly, cycle efficiency increases as turbine pressure ratio increases. It is worth mentioning that cycle optimum point differs from the turbine one. The former is obtained at a pressure ratio equal to 9.5 while the latter results at a pressure ratio equal to 6.9. Cycle efficiency is a function of cycle net power that increases with increasing turbine pressure ratio.

Results of Finite Element Analyses (FEA)
For safe operation, the maximum von Mises stress and stress and total displacement should not exceed be the material tensile strength and the tip clearance gap between the rotor and casing. Figure   Figure 26. Cycle thermal efficiency and net power at various pressure ratios. thermal efficiency is a function of cycle net power divided by heat input. The heat input increases with increasing the inlet temperature. For 30,000 rpm, the rate of increase of heat input is greater than that of cycle net power for all operating temperatures. For 40,000 rpm, on the other hand, the rate of increase of heat input from 430 to 450 K is 8.60% compared 4.17% of net power. From 450 to 471.55 K, the rate of increase in heat input is 4.07% compared to 5.80% of net power. This clarifies the trend of cycle thermal efficiency operating with 40,000 rpm.

Results of Finite Element Analyses (FEA)
For safe operation, the maximum von Mises stress and stress and total displacement should not exceed be the material tensile strength and the tip clearance gap between the rotor and casing. Figure   Figure 27. Cycle thermal efficiency and net power at various turbine inlet temperatures. Figure 27 shows that cycle net power increases linearly with increasing turbine inlet temperature because of the increased turbine power, Figure 25. The cycle thermal efficiency, on the other hand, shows different trends. For 40,000 rpm, it decreases with increasing inlet temperature then increases, reaching the design point. For 30,000 rpm, the cycle efficiency decreases with increasing temperature. The different trend in both speeds is related to the definition of the cycle thermal efficiency. Cycle thermal efficiency is a function of cycle net power divided by heat input. The heat input increases with increasing the inlet temperature. For 30,000 rpm, the rate of increase of heat input is greater than that of cycle net power for all operating temperatures. For 40,000 rpm, on the other hand, the rate of increase of heat input from 430 to 450 K is 8.60% compared 4.17% of net power. From 450 to 471.55 K, the rate of increase in heat input is 4.07% compared to 5.80% of net power. This clarifies the trend of cycle thermal efficiency operating with 40,000 rpm.

Results of Finite Element Analyses (FEA)
For safe operation, the maximum von Mises stress and stress and total displacement should not exceed be the material tensile strength and the tip clearance gap between the rotor and casing. Figure 28 presents the results of the FEA at the design point using Fullcure 720. In addition, Table 7 summarizes the FEA at design and off-design points for the considered types of material. As can be seen in Figure 28, the maximum stress and deformation due to fluid pressure are 0.54 MPa and 0.001 mm which are well below the limits (60 MPa and 0.6 mm). However, it is apparent from Table 7 that maximum stress and deformation due to rotation increase significantly. Although the maximum stress (29.22 MPa) is still below the material tensile strength, the deformation at the blade tip is 0.48 mm which is very close to the assigned clearance gap (0.6 mm). Therefore, although Fullcure 720 is cost-effective, using such material in the current application is risky due to the possibility of metal fusion near the blade tip. It is evident from Figure 28 that the maximum stress occurs at the blade root in the hub for both fluid pressure and rotation. The maximum deformation, on the other hand, occurs at the at exit tip for both fluid pressure and rotation. Similar locations of maximum stress and deformation are also noticed for all considered types of materials and with different operating conditions (i.e., off-design operation). It is worth mentioning that the locations of maximum stress and deformation agree with locations mentioned in Moustapha et al. [68]. For other types of material, the maximum stress and deformation are well below limits for both fluid pressure and rotation.    At off-design operations, similar observations are noticed. However, reducing the rotational speed from 40,000 to 30,000 rpm results in lower blade tip deformation (0.27 mm compared to 0.48 mm). Table 7 also indicates that stainless steel is not appropriate for the current application due to high resulted stress. Therefore, the best option for the current application is either a titanium alloy or aluminium alloy. However, titanium alloy is typically 20 times more expensive than a corresponding aluminium part [69].

Conclusions
This paper presented the fluid-structure interaction of a high pressure-ratio backswept radial inflow turbine operating with high-dense working fluid at design and off-design points. The main conclusions of the current study are summarized below:

•
The proposed mathematical modelling for generating 3D shapes of turbine blades and vanes is fast and accurate.

•
The CFD simulations indicated the robustness of the proposed 1D mean-line model. The deviations between the 1D mean-line and 3D CFD in turbine efficiency and power output were 2.28% and 5.10%, respectively. In addition, the 3D CFD results confirmed the optimum blade angle value optimized by the 1D mean-line model.

•
At the design point, the flow at the stator exit was supersonic as expected. However, it was smooth with no flow-vortices. In the rotor blades, the fluid was flowing smoothly, and the velocity was homogenously distributed at 90% span. At the 50% span, flow recirculation was observed downstream of the rotor blades at the suction side, resulting in a moderate level of diffusion at this area. The results also indicated that the curvature downstream the blade should be optimized.

•
At off-design conditions, the performance of the turbine was non-optimum. In addition, strong flow vortices resulted in the passage of the rotor blade. Increasing the stage pressure ratio resulted in high Mach numbers which negatively affected the turbine performance while affected the output power positively. For low turbine inlet temperatures, the flow is more uniform at 30,000 rpm than that in design point speed (40,000 rpm). In contrast, flow pattern improves better with 40,000 rpm than 30,000 rpm at high temperatures since the fluid density at the stator exit is lower.

•
The FEA indicated that material selection is a trade-off between its mechanical integrity and cost. Fullcure 720 should be avoided in the current application due to the possibility of metal fusion near the blade tip. Similarly, stainless steel is not appropriate for the current application due to high resulted stress. Titanium alloy and aluminium alloy can be used for the current applications, although the former is typically 20 times more expensive.

•
Cycle thermal efficiency and net power were investigated at various pressure ratios and turbine inlet temperatures. As pressure ratio increases, cycle thermal efficiency and net power increases due to the increased turbine power output. The results also indicated that cycle net power increases linearly with increasing turbine inlet temperature while cycle thermal efficiency showed different trends according to the rotational speed.