基于流热固耦合仿真的航空发动机暖机特性及其对推力的影响

doi:10.7527/S1000-6893.2025.32104

Abstract

Abstract:

Aero-engine requires maintaining high rotational speeds for warm-up operations prior to takeoff； otherwise， thrust degradation may occur during the climb-out phase. To address this issue， this study focuses on a core engine of a small-bypass-ratio turbofan and develops a fluid-thermal-solid coupling computational methodology that integrates a 1D fluid domain model with a 2D axisymmetric finite element model of the solid structure. This approach enables coupled simulation across different scales for solid domain analysis， air system evaluation， multi-component thermal analysis， and deformation prediction. Simulation results reveal that tip clearance exceeding design specifications constitutes the primary cause of thrust reduction during takeoff. Warm-up operations effectively reduce tip clearances， resulting in a 0.85% improvement in high-pressure turbine efficiency and a 0.5% enhancement in compressor efficiency. These improvements drive a maximum 0.51% increase in high-pressure rotor speed， augment core mass flow， reduce engine bypass ratio， and ultimately elevate minimum takeoff thrust by 2.4%. Further analysis demonstrates that either extending warm-up duration or increasing warm-up rotational speed can enhance takeoff thrust. However， when the warm-up speed remains below 0.75， increasing rotational speed fails to effectively reduce high-pressure turbine tip clearance. Finally， leveraging sequential quadratic programming optimization， a warm-up parameter optimization model constrained by thrust requirements is established to achieve optimal combinations of minimum warm-up time and rotational speed across various operational conditions.

Key words: turbofan engine, warm-up, tip clearance, fluid-thermal-solid coupling, transient state

CLC Number:

V231.1

Faning SHAO, Chao YANG, Pingting CHEN, Feilong WANG, Weichen ZHAO, Bo NING, Junkui MAO. Warm-up characteristics and thrust impact of aero-engines based on fluid-thermal-solid coupled simulation[J]. Acta Aeronautica et Astronautica Sinica, 2026, 47(2): 132104.

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References 39

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阶段	N_2，Z	持续时间/min
启动0~t₁	0.675N_2，max	1
慢车t₁~t₂	0.675N_2，max	2
暖机t₂~t₃	N_H	Δt
起飞t₃~t₄	N_2，max	3

时间/s	0	234	320	339	399	639
∆δ_HPT计算结果/%	0	-24.0	-36.8	-21.5	-48.0	-51.6
∆δ_HPT测试结果/%	0	-24.4	-38.8	-21.2	-48.4	-56.0
相对误差/%		-1.6	-5.2	1.4	-0.8	-7.9

F_m	N_H	Δt /min
0.970	0.73	2.01
0.975	0.86	2.09
0.980	0.87	2.18
0.985	0.87	3.22
0.990	0.90	3.95

Warm-up characteristics and thrust impact of aero-engines based on fluid-thermal-solid coupled simulation

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