Equilibrium running principle analysis on an adaptive cycle engine

The risks and costs of developing a new aeroengine are fundamentally depending on the performance design final proposal. Thus, this paper presents a novel aeroengine performance design methodology that is committed to managing the effectiveness and economic availability of the design proposal. To reach such a target, the presented methodology formulates the traditional thermal cycle design problem as a reliability-based fuzzy optimization. The performance reliability is predicted by the deep neural network (DNN)-based surrogate models while a hyperparameter tuning technique is proposed to find the optimal DNN topology for better implementing a particular deep learning task. The testing results imply the DNN models with optimized topology possess remarkable function approximation capability in global so that achieves significantly higher prediction accuracy. Moreover, the DNN-based surrogate models only cost nearly 0.003% as much computing time as MC simulation (2.3591 sec vs 64746 sec, for 20 samples). Such kind of remarkably higher computational efficiency facilitates the optimization for reliability-based fitness calculation. The efficiency of the presented methodology can be further verified by abundant feasible cycle proposals. The obtained cycle solutions can achieve expected reliability (>95%) in all reference states without unnecessary performance redundancy. Besides, the diversity of feasible cycle solutions contributes to the selection of best proposal associated with engineering situation. The presented effort is favorable to acquire a more cost-efficient design proposal and enrich thermodynamic system design theory.

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“…More details of modeling techniques of each component can be found in these references [22][23][24].…”

Section: ) Off-design Point Simulationmentioning

confidence: 99%

DNN-Based Surrogate Modeling-Based Feasible Performance Reliability Design Methodology for Aircraft Engine

Cao

Bai

2020

IEEE Access

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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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“…It is known that for low supersonic cruising speeds, turbofan engines are preferable, and for high supersonic speeds -ramjets [3]. But ramjets have no starting thrust and low efficiency at subsonic speeds, which necessitates the use of combined power plants (PP) [4][5][6]. In this case, takeoff, climb and achieving supersonic cruising speed are carried out using a gas turbine engine and cruising -a ramjet.…”

Section: Introductionmentioning

confidence: 99%

Development of a method for selecting a cruising mode and engine control program of a ramjet aircraft

Kislov

Shevchenko

2021

EEJET

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For supersonic cruising, combined power plants can be used, in which a gas turbine engine reaches the cruising mode, and a ramjet is used for cruising. Supersonic transoceanic flights are characterized by a long cruising segment, which is decisive in terms of required fuel mass. Therefore, the selection of cruising and engine operation parameters is an important task. As a rule, when selecting the cruising mode, the range parameter is used, which depends on the flight and engine operation modes. To take into account the influence of the ramjet operating mode on the range parameter, dimensionless relationships of engine parameters with control factors were obtained. Using the obtained relationships together with the equations of aircraft motion in steady horizontal flight, it is shown that the values of the engine control factors and the range parameter do not change at the altitudes of 11...20 km. This made it possible to conclude that the range parameter can be increased only by selecting the cruising and engine parameters that provide the minimum specific fuel consumption. The variable cruising parameters are speed and initial altitude. A method for selecting the cruising and ramjet operation parameters was developed, based on the analysis of the relationship between the range parameter and the flight speed and initial altitude at the most advantageous values of the engine control factors. The obtained relationships allow selecting the cruising parameters and the engine operating mode, taking into account the restrictions. It is shown that the specific fuel consumption decreases by 0...30 %, depending on the engine operating mode, when the control program is optimized

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Equilibrium running principle analysis on an adaptive cycle engine

Cited by 56 publications

References 10 publications

DNN-Based Surrogate Modeling-Based Feasible Performance Reliability Design Methodology for Aircraft Engine

DNN-Based Surrogate Modeling-Based Feasible Performance Reliability Design Methodology for Aircraft Engine

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

Development of a method for selecting a cruising mode and engine control program of a ramjet aircraft

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