Advanced Propulsion System and Thermal Management Technology

Topic Information

Dear Colleagues,

Propulsion systems continue to attract significant research attention, especially aircraft engines, rocket engines and scramjets. New propulsion systems have been proposed that combine two basic propulsion systems, such as RBCC and TBCC, as well as new types of propulsion systems, such as combined space–air–ocean systems and highly integrated power systems, which can allow aircraft to fly safely from overland regions to oceanic environments. Propulsion systems are being developed to achieve a wide speed range and long endurance for both civil and military applications. Studies on propulsion systems mainly addresses overall design, combustion, aerodynamics, internal flow and heat transfer. High efficiency is pursued not only by optimized design but also via the development of suitable materials and the use of powdered fuels.

Alongside the development of high-efficiency propulsion systems, thermal management technologies are also being developed to address the increased heat from external aerodynamic heating and internal combustion at high speeds. These thermal management technologies can transfer excessive heat to other low-temperature regions or provide thermal protection for structures via blade cooling in gas turbines and regenerative cooling in rocket engines. The thermal protection of engines is highly efficient due to the enhancement of convective heat transfer, such as the usage of superficial fluids, nanofluids, or newly designed roughened surfaces. Additionally, some heat transfer enhancement methods used in heat exchangers, batteries and fuel cells have been implemented in propulsion systems.

This Topic focuses on bringing together innovative developments in the fields of advanced propulsion systems and thermal management technology. Potential topics include, but are not limited to:

• Propulsion system design;
• Heat transfer enhancement;
• Turbulent combustion;
• Supercritical fluid;
• Regenerative cooling;
• Flow control;
• Laser-based combustion diagnostics;
• Spray dynamics;
• Nanofluids;
• Blade cooling;
• Film cooling;
• Transpiration cooling;
• Multiphase flow;
• Heat transfer in propulsion system;
• Aerodynamics;
• Combustion instability;
• Powder fuel;
• Spray dynamics;
• Convective heat transfer;
• Supersonic vehicles;
• Thermal management in other fields.

Dr. Jian Liu
Dr. Yiheng Tong
Topic Editors

Keywords

Participating Journals

Journal Name	Impact Factor	CiteScore	Launched Year	First Decision (median)	APC
Aerospace aerospace	2.5	4.8	2014	22.9 Days	CHF 2400	Submit
Applied Sciences applsci	2.9	6.1	2011	16 Days	CHF 2400	Submit
Astronautics astronautics	-	-	2026	15.0 days *	CHF 1000	Submit
Energies energies	3.9	8.3	2008	16.8 Days	CHF 2600	Submit
Machines machines	3.0	6.1	2013	17.6 Days	CHF 2400	Submit
Sci sci	4.1	5.4	2019	26.7 Days	CHF 1400	Submit
Thermo thermo	3.9	4.4	2021	26.1 Days	CHF 1200	Submit

* Median value for all MDPI journals in the second half of 2025.

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Published Papers (2 papers)

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All Aerospace Applied Sciences Astronautics Energies Machines Sci Thermo

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28 pages, 5305 KB  

Open AccessArticle

Thermodynamic Performance Enhancement and NOx Emission Assessment in a Triple-Spool Turbofan Engine with an Interstage Turbine Burner

by Raed Kafafy

Thermo 2026, 6(2), 47; https://doi.org/10.3390/thermo6020047 - 17 Jun 2026

Viewed by 241

Abstract

The increasing demand for higher efficiency and lower emissions in aircraft gas turbines motivates investigation of alternative thermodynamic cycle architectures. This study assesses the performance and nitrogen oxides (NOx) emission behavior of a triple-spool, separate-exhaust turbofan engine equipped with an interstage turbine burner [...] Read more.

The increasing demand for higher efficiency and lower emissions in aircraft gas turbines motivates investigation of alternative thermodynamic cycle architectures. This study assesses the performance and nitrogen oxides (NOx) emission behavior of a triple-spool, separate-exhaust turbofan engine equipped with an interstage turbine burner (ITB). A baseline engine representative of the RB211 Trent 892 is first modeled at maximum takeoff, sea-level static conditions and verified against publicly available takeoff reference data. The cycle is then modified by introducing an isobaric secondary combustion process between the high-pressure and intermediate-pressure turbines. The effects of fan pressure ratio, bypass ratio, overall pressure ratio, high-pressure turbine inlet temperature, and ITB exit temperature are examined using two-parameter response surface sweeps. Main combustor NOx is estimated using an RQL-type cycle correlation, while the ITB contribution is represented using an engineering source–sink model accounting for new NOx formation and partial reburning of upstream NOx. The baseline model predicts specific thrust, thrust-specific fuel consumption (TSFC), and NOx emission index (EINOx) within ±8% of reference values. At a selected ITB operating point, specific thrust increases by 1.98%, TSFC increases by 9.84%, thermal efficiency decreases by 2.56%, and the adopted engineering source–sink model predicts a 20.03% reduction in fuel flow-weighted EINOx. The corresponding takeoff-mode NOx-per-thrust indicator decreases by approximately 12.1%. These results indicate that ITB integration introduces a coupled performance–emissions trade-off and should not be evaluated solely as a thrust augmentation method. Full article

(This article belongs to the Topic Advanced Propulsion System and Thermal Management Technology)

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27 pages, 11625 KB  

Open AccessArticle

A Model for Accurate Prediction of Discharge Coefficients in Rotating Orifices with Different Wall Inclination Angles

by Jiaxi Yan, Song Wei, Junkui Mao, Zhiyin Yang, Feng Han and Longfei Wang

Aerospace 2026, 13(6), 555; https://doi.org/10.3390/aerospace13060555 - 16 Jun 2026

Viewed by 273

Abstract

Accurate prediction of discharge coefficients (C_d) in rotating orifices is essential for the design of aero-engine internal air systems, yet existing correlations usually treat axial and radial orifices separately and do not fully represent intermediate wall inclination angles. In this [...] Read more.

Accurate prediction of discharge coefficients (C_d) in rotating orifices is essential for the design of aero-engine internal air systems, yet existing correlations usually treat axial and radial orifices separately and do not fully represent intermediate wall inclination angles. In this study, steady-state RANS simulations in a rotating reference frame, supported by validation against published data and by rotating orifice experiments, are used to investigate the combined effects of wall inclination angle α and length-to-diameter ratio L/d on C_d. The numerical results show that, under typical conditions (N = 3000 rpm, Π = 1.03, L/d = 1.5), C_d increases from 0.301 to 0.340 as α increases from π/2 to π, corresponding to a 12.96% increase. Under low rotational speeds and high pressure ratios, the Coriolis force reduces the relative tangential velocity and the incidence angle, thereby increasing C_d with α; however, at high rotational speeds and low pressure ratios, the centrifugal resistance to radial inflow becomes dominant, and at N = 7000 rpm, the C_d for the α = π orifice is 38.96% lower than that for the α = π/2 orifice. Increasing L/d promotes flow redevelopment and amplifies the Coriolis-force effect, leading to a larger C_d increase for orifices with larger α. Based on these mechanisms, a generalized incidence-angle formulation incorporating Coriolis and centrifugal effects is developed, and a C_d prediction model applicable to π/2 ≤ α ≤ π and different L/d values is proposed. Experimental validation shows that the maximum prediction error is reduced to 2.37%, demonstrating the accuracy of the proposed model for rotating inclined orifices. Full article

(This article belongs to the Topic Advanced Propulsion System and Thermal Management Technology)

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