Performance Analysis of a Three-Stream Adaptive Cycle Engine during Throttling

Chen, Min; Zhang, Jiyuan; Tang, Huazhong

doi:10.1155/2018/9237907

Cited by 19 publications

(4 citation statements)

References 22 publications

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“…(C bp is the coefficient of bleed drag, A bleed is the bleed area, and A c is the inlet capture area.) Therefore, even if the shock wave remains at a position of high-pressure recovery coefficient, it may still cause a net loss of the propulsion system [3,4]. Because the pressure of fan inlet has influence on the normal shock wave position, it may be better to adopt the integrated adjustment of the bleed valve and engine to control the position.…”

Section: Introductionmentioning

confidence: 99%

Study on Inlet and Engine Integrated Model with Normal Shock Position Feedback

Chen

Zhang

et al. 2020

International Journal of Aerospace Engineering

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In order to consider the inlet and engine integrated model of supersonic airliner, the dynamic identification and control of inlet normal shock are studied. The research is based on the bleed air flow rate under supersonic conditions. With the two-dimensional CFD model of supersonic inlet, the dynamic and static effects of the bleeding flow rate on the normal shock position were investigated. The transfer function was identified, and simultaneously the paper carried out a comprehensive study of inlet and engine integrated model, which is established based on the inlet shock position model and engine component level model. The relationship between normal shock position and total pressure recovery coefficient has been taken into consideration in this model. Based on the inlet and engine integrated model, the closed-loop control simulation of normal shock position is carried out. The results show that the model could resist the disturbance of the inlet flow and keep the inlet and engine matching operation point stable near the optimal value.

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Section: Introductionmentioning

confidence: 99%

Study on Inlet and Engine Integrated Model with Normal Shock Position Feedback

Chen

Zhang

et al. 2020

International Journal of Aerospace Engineering

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“…Although the working principles of the different ACE concepts are generally similar, there are still many differences in their specific operation and component matching [12][13][14][15][16][17][18][19][20][21][22]. At present, not all ACE concepts have been studied in depth, and some important research results of ACE have not been published.…”

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

Self Cite

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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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“…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%

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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Performance Analysis of a Three-Stream Adaptive Cycle Engine during Throttling

Cited by 19 publications

References 22 publications

Study on Inlet and Engine Integrated Model with Normal Shock Position Feedback

Study on Inlet and Engine Integrated Model with Normal Shock Position Feedback

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

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

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