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Energies
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Aerothermal Interaction between Combustor and Turbine
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Aerothermal Interaction between Combustor and Turbine

A special issue of Energies (ISSN 1996-1073). This special issue belongs to the section "J: Thermal Management".

Deadline for manuscript submissions: closed (31 May 2022) | Viewed by 5615

Special Issue Editors

Prof. Dr. Heinz-Peter Schiffer

E-Mail Website
Guest Editor
Institute of Gas Turbines and Aerospace Propulsion, Technical University Darmstadt, 64287 Darmstadt, Germany
Interests: turbine aerodynamics; turbine cooling; compressor aerodynamics and aeroelasticity; aerothermal combustor turbine interaction
Dr. Sebastian Leichtfuß

E-Mail Website
Guest Editor
Institute of Gas Turbines and Aerospace Propulsion, Technical University Darmstadt, 64287 Darmstadt, Germany
Interests: turbine aerodynamics; turbine cooling; compressor aerodynamics and aeroelasticity; turbocharger aerodynamics; aerothermal combustor turbine interaction; aerothermal measurement techniques; numerical and optimization methods

Special Issue Information

Dear Colleagues,

Today, both gas turbines and aero engines face demanding regulatory and ecological challenges, driven by the threatening climate change and the ever-growing environmental awareness. Both reach maximum efficiency at the design point, but aiming for always increasing efficiency becomes more and more challenging as well. Therefore, taking into account component interaction during the design process becomes essential when striving for higher component and engine efficiency. The trend of increased transient operation in the field of gas turbines, due to the growing application of regenerative energy sources, and the trend toward smaller core sizes in the field of aero engines fosters even more the necessity for a coupled component design. Coupled methods and design processes accounting for component interaction of the whole system are required, aiming for the so-called “Virtual Engine” or “Digital Twin". This is especially challenging at the combustor-turbine interface, since aerodynamic, chemical, and thermal processes interact, and the flow alters from incompressible combustion to compressible expansion in the turbine. Transient load changes come along with fast fuel variations, even intensifying the level of interaction, especially component- and time-wise. Digitization, novel materials, and analysis methods for combustor and turbine components can increase efficiency and reliability and reduce life cycle costs and development times. This will also enable the development of efficient, low-maintenance, and competitive turbomachines for the future.

This Special Issue will deal with analytical and numerical modeling, novel optimization techniques, measurement methods and results and the application of artificial intelligence at the combustor-turbine interface.

Prof. Dr. Heinz-Peter Schiffer
Dr. Sebastian Leichtfuß
Guest Editors

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Keywords

  • Combustor-turbine interaction (CTI)
  • Numerical methods
  • High-pressure turbine design and research
  • High-pressure turbine aerodynamics and cooling
  • Optimization methods applied for CTI
  • Artificial intelligence applied at the combustor and/or high-pressure turbine
  • Measurement methods and results
  • Application of new materials driven by CTI
  • Lean burn impacts on aerothermal turbine performance
  • Impact of hot streak, swirl and turbulence

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Published Papers (2 papers)

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Research

19 pages, 8980 KiB  
Article
Effects of Bulk Flow Pulsation on Film Cooling Involving Compound Angle
by Seung-Il Baek and Joon Ahn
Energies 2022, 15(7), 2643; https://doi.org/10.3390/en15072643 - 4 Apr 2022
Cited by 2 | Viewed by 2017
Abstract
The main flow could be unsteady in flow fields of film cooling for several reasons such as flow interactions between the rotor and the stator in the turbine. Understanding the characteristics of the film-cooling flow with an unsteady flow is important in the [...] Read more.
The main flow could be unsteady in flow fields of film cooling for several reasons such as flow interactions between the rotor and the stator in the turbine. Understanding the characteristics of the film-cooling flow with an unsteady flow is important in the design of gas turbines. The effects of 36-Hz pulsations in the main flow on the streamwise velocity distributions, turbulence statistics, and temperature fluctuations in the film-cooling flow from a cylindrical hole with an orientation angle are investigated by numerical methods. Large-eddy simulation (LES) results match the experimental data with an acceptable accuracy, whereas the Reynolds-averaged Navier–Stokes simulation (RANS) results show large deviations with the experimental data and the LES results. Under 36-Hz pulsations, the URANS results predict a weaker streamwise velocity of the coolant jet that blocks the main flow compared with the LES. With 36-Hz pulsations at the time-averaged blowing ratio of 0.5, urms, the root mean squared fluctuating velocity in the streamwise direction around the coolant core increased due to intensive mixing, and vrms, the root mean squared fluctuating velocity in the wall-normal direction, increased along the trajectory of the injected coolant. Moreover, wrms, the root mean squared fluctuating velocity in the spanwise direction, increased around the wall compared to those at a steady state. The dimensionless temperature fluctuations increased in the region of the core of the coolant compared with those at a steady state. When the orientation angle was 30°, the distribution of the results moved in the z-direction; however, the overall trend was similar to that of a simple angle. Full article
(This article belongs to the Special Issue Aerothermal Interaction between Combustor and Turbine)
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23 pages, 13959 KiB  
Article
Generation of Realistic Boundary Conditions at the Combustion Chamber/Turbine Interface Using Large-Eddy Simulation
by Benjamin Martin, Florent Duchaine, Laurent Gicquel and Nicolas Odier
Energies 2021, 14(24), 8206; https://doi.org/10.3390/en14248206 - 7 Dec 2021
Cited by 7 | Viewed by 2921
Abstract
Numerical simulation of multiple components in turbomachinery applications is very CPU-demanding but remains necessary in the majority of cases to capture the proper coupling and a reliable flow prediction. During a design phase, the cost of simulation is, however, an important criterion which [...] Read more.
Numerical simulation of multiple components in turbomachinery applications is very CPU-demanding but remains necessary in the majority of cases to capture the proper coupling and a reliable flow prediction. During a design phase, the cost of simulation is, however, an important criterion which often defines the numerical methods to be used. In this context, the use of realistic boundary conditions capable of accurately reproducing the coupling between components is of great interest. With this in mind, this paper presents a method able to generate more realistic boundary conditions for isolated turbine large-eddy simulation (LES) while exploiting an available integrated combustion chamber/turbine LES. The unsteady boundary conditions to be used at the inflow of the isolated turbine LES are built from the modal decomposition of the database recorded at the interface between the two components of the integrated LES simulation. Given the reference LES database, the reconstructed field boundary conditions can then be compared to standard boundary conditions in the case of isolated turbine configuration flow predictions to illustrate the impact. The results demonstrate the capacity of this type of conditions to reproduce the coupling between the combustion chamber and the turbine when standard conditions cannot. The aerothermal predictions of the blade are, in particular, very satisfactory, which constitutes an important criterion for the adoption of such a method during a design phase. Full article
(This article belongs to the Special Issue Aerothermal Interaction between Combustor and Turbine)
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