Overall performance design of paralleled heat release and compression system for hypersonic aeroengine

Dong, Ping; Tang, Huazhong; Chen, Min; Zou, Zhengping

doi:10.1016/j.apenergy.2018.03.062

Cited by 44 publications

(7 citation statements)

References 24 publications

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“…The algorithms used in this method have been demonstrated to have good convergence [12,26,38,39]. Without a specific prototype, this method can still calculate and analyze the steady-state performance by using the general characteristics of the components [12][13][14][15][39][40][41][42][43]. Therefore, the zerodimensional model numeric simulation method is considered to have strong practicability and flexibility in the preliminary R&D stage of gas turbine engine [23,26,27,[39][40][41][42][43].…”

Section: Introductionmentioning

confidence: 99%

A Matching Problem between the Front Fan and Aft Fan Stages in Adaptive Cycle Engines with Convertible Fan Systems

Meng¹,

Zhu²,

Chen³

et al. 2021

Energies

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In the process of studying the steady-state performance and component matching of adaptive cycle engines with convertible fan system, it was found that the front fan and aft fan stage have a unique matching problem when the mode select valve is closed and engine is operating at higher Mach number conditions. The cause of this matching problem was studied with numeric simulation in this paper. Based on the features of adaptive cycle engines with convertible fan system, the possible methods and their feasibilities of solving this matching problem were also discussed. According to the results, the flow rate adjustment capacity of the aft fan stage directly determines the occurrence and severity of this matching problem. The matching problem can be ameliorated in some extent by either reducing the design second bypass ratio or adjusting the variable geometry mechanisms, but it cannot be completely solved at the aspect of component matching mechanism.

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Section: Introductionmentioning

confidence: 99%

A Matching Problem between the Front Fan and Aft Fan Stages in Adaptive Cycle Engines with Convertible Fan Systems

Meng¹,

Zhu²,

Chen³

et al. 2021

Energies

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“…Currently, considerable attention has been paid to the candidates of next generation aviation propulsion solution, such as variable cycle aeroengine [1], hypersonic precooled engine [2,3]. One noteworthy feature of these candidate solutions is the excellent multi-mission adaptability due to their special functions, such as variable geometry schedule, multi-cycle coupling mechanism [4], the regenerative cooling system [5], etc. Through implementing these innovative functions, the new propulsion solutions could combine the specialties of turbojet and turbofan, including the high specific thrust in supersonic penetration and low specific fuel consumption in subsonic cruise.…”

Section: Introductionmentioning

confidence: 99%

A Study on Aeroengine Conceptual Design Considering Multi-Mission Performance Reliability

Cao

Bai

2020

Applied Sciences

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Owing to the realization of multi-mission adaptability requires more complex mechanical structure, the candidates of future aviation propulsion are confronted with more overall reliability problems than that of the conventional gas turbine engine. This situation is challenging to a traditional aeroengine deterministic design method. To overcome this challenge, the Reliability-based Multi-Design Point Methodology is proposed for aeroengine conceptual design. The presented methodology adopted an unconventional approach of engaging the reliability prediction by artificial neural network (ANN) surrogate models rather than the time-consuming Monte Carlo (MC) simulation. Based on the Adaptive Particle swarm optimization, the utilization of the pre-training technique optimizes the initial network parameters to acquire better-conditioned initial network, which is sited closer to designated optimum so that contributes to the convergence property. Moreover, a new hybrid algorithm is presented to integrate the pre-training technique into neural network training procedure in order to enhance the ANN performance. The proposed methodology is applied to the cycle design of a turbofan engine with uncertainty component performance. The testing results certify that the prediction accuracy of pre-trained ANN is improved with negligible computational cost, which only spent nearly one-millionth as much time as the MC-based probabilistic analysis (0.1267 s vs. 95,262 s, for 20 testing samples). The MC simulation results substantiate that optimal cycle parameters precisely improve the engine overall performance to simultaneously reach expected reliability (≥98.9%) in multiple operating conditions without unnecessary performance redundancy, which verifies the efficiency of the presented methodology. The presented efforts provide a novel approach for aeroengine cycle design, and enrich reliability design theory as well.

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“…A variety of new generation supersonic civil aircraft concepts have been put forward in some literatures [4][5][6][7][8][9][10][11][12][13][14][15][16][17][18][19][20][21], for example, the conceptual design of Mach 5 TBCC engine which is applied into the supersonic civil aircraft has been investigated [22]. However, for Mach 5 TBCC engine, the inlet adjustment is more complicated, and the total inlet temperature can reach around 1300 K. So, it is more challenging to solve the airframe thermal protection problem based on the existing material and technology, due to the high stagnant temperature due to extremely high Mach.…”

Section: Introductionmentioning

confidence: 99%

“…where D j and V j mean the exit diameter of the nozzle and the speed of the jet, which could be calculated by the TBCC engine performance model [17]. Based on the similarity with the calculation of subsonic jet noise spectrum, the shock wave noise spectrum could be achieved.…”

mentioning

confidence: 99%

Research on Simulation and Performance Optimization of Mach 4 Civil Aircraft Propulsion Concept

Chen

Jia

Tang

et al. 2019

International Journal of Aerospace Engineering

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Supersonic civil aircraft is of a promising area in the development of future civil transport, and aircraft propulsion system is one of the key issues which determine the success of the aircraft. To get a good conceptual design and performance investigation of the supersonic civil aircraft engine, in this article, a fast, versatile as well as trust-worthy numerical simulation platform was established to analyze the Mach 4 turbine-based combined cycle (TBCC) engine concept so as to be applied to the supersonic civil aircraft. First, a quick and accurate task requirement analysis module was newly established to analyze the mission requirement of the Mach 4 supersonic civil aircraft. Second, the TBCC engine performance simulation model was briefly presented and the number of engines on the supersonic civil aircraft was analyzed, considering single engine inoperative. Third, the Stone model and the DLR method were investigated to estimate the engine jet noise and the NOx emission of the Mach 4 supersonic civil aircraft. Finally, a multiobjective optimization tool made up of a response surface method and a genetic algorithm was developed to optimize the design parameters and the control law of the TBCC engine, in order to make the Mach 4 supersonic civil aircraft engine with better performance, lower noise, and lower emissions. The uniqueness of the developed analysis tool lies in that it affords a numerical simulation platform capable of investigating the task requirement analysis module of the supersonic civil aircraft, engine jet noise prediction model, and the NOx emission prediction model, as well as a multiobjective performance optimization tool, which is beneficial for the conceptual design and performance research of Mach 4 supersonic civil aircraft’s propulsion system.

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Overall performance design of paralleled heat release and compression system for hypersonic aeroengine

Cited by 44 publications

References 24 publications

A Matching Problem between the Front Fan and Aft Fan Stages in Adaptive Cycle Engines with Convertible Fan Systems

A Matching Problem between the Front Fan and Aft Fan Stages in Adaptive Cycle Engines with Convertible Fan Systems

A Study on Aeroengine Conceptual Design Considering Multi-Mission Performance Reliability

Research on Simulation and Performance Optimization of Mach 4 Civil Aircraft Propulsion Concept

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