A Comprehensive Solution of the Problems of Ensuring the Strength of Gas Turbine Engine Compressor at the Design Stage

2017 International Conference on Aerospace Technology, Communications and Energy Systems

航空航天工程;无线电电子学;能源学

Vedeneev, V.V.^1 ; Kolotnikov, M.E.^1 ; Mossakovskii, P.A.^1 ; Kostyreva, L.A.^1 ; Abdukhakimov, F.A.^1 ; Makarov, P.V.^2 ; Pyhalov, A.A.^3 ; Dudaev, M.A.^3

Lomonosov Moscow State University, 1 Michurinskii prospect, Moscow

119192, Russia^1

Salut Gas Turbine Engineering Research and Production Center, 16 Budionny Ave, Moscow

105118, Russia^2

Irkutsk State Transport University, 15 Chernyshevskogo str., Irkutsk

664074, Russia^3

关键词: Blade flutter;    Compressor designs;    Design process;    Design stage;    High amplitudes;    Numerical convergence;    Resonant oscillation;   

Others  :  https://iopscience.iop.org/article/10.1088/1757-899X/302/1/012079/pdf
DOI  :  10.1088/1757-899X/302/1/012079

学科分类：航空航天科学

来源: IOP

【 摘 要 】

In this paper we present a complex numerical workflow for analysis of blade flutter and high-amplitude resonant oscillations, impenetrability of casing if the blade is broken off, and the rotor reaction to the blade detachment and following misbalance, with the assessment of a safe flight possibility at the auto-rotation regime. All the methods used are carefully verified by numerical convergence study and correlations with experiments. The use of the workflow developed significantly improves the efficiency of the design process of modern jet engine compressors. It ensures a significant reduction of time and cost of the compressor design with the required level of strength and durability.