EFFECT OF STEADY-STATE CIRCUMFERENTIAL PRESSURE AND TEMPERATURE DISTORTIONS ON COMPRESSOR STABILITY

Lian Xiaochun; Chen Fuqun; Wang Li'an

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EFFECT OF STEADY-STATE CIRCUMFERENTIAL PRESSURE AND TEMPERATURE DISTORTIONS ON COMPRESSOR STABILITY

更新时间：2026-07-07

- EFFECT OF STEADY-STATE CIRCUMFERENTIAL PRESSURE AND TEMPERATURE DISTORTIONS ON COMPRESSOR STABILITY
- Vol. 8, Issue 2, (1993)
- 作者机构：
  
  1. 西北工业大学,710072
  2. 试飞研究院
- 作者简介：
- 基金信息：
- DOI：
  CLC：
- Published：1993
- 稿件说明：
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Lian Xiaochun, Chen Fuqun, Wang Li'an. EFFECT OF STEADY-STATE CIRCUMFERENTIAL PRESSURE AND TEMPERATURE DISTORTIONS ON COMPRESSOR STABILITY[J]. 1993, 8(2).
DOI：

Lian Xiaochun, Chen Fuqun, Wang Li'an. EFFECT OF STEADY-STATE CIRCUMFERENTIAL PRESSURE AND TEMPERATURE DISTORTIONS ON COMPRESSOR STABILITY[J]. 1993, 8(2). DOI：

摘要

本文对Melick提出的进口总压周向稳态畸变对压气机稳定性裕度损失的估算方法作了改进

并加以推广应用于进口总温周向稳态畸变的情况。在此基础上

本文提出了总温和总压组合畸变下压气机稳定性裕度损失的预测方法。以某型双轴涡喷发动机为例作了某些具体的计算。

Abstract

A model for predicting the effect of inlet steady state circumferential total pressure distortion on compressor stability pressented in reference [1] has been improved by considering the variation in compressor efficiency due to the distortion.The impr oved model is applicable to case of the inlet steady state circumferenti al total temperature distortion.Based on this model

a method has been dev eloped for estimating the effects of combined pressure and temperatur e distortions on the compressor stabilit y.A numerical analysis was conducted for a two spool turbojet engine with the pr essure and temperature distortions as we ll as the combined distortions.The results show that the variation in compressor efficiency due to distortion cannot be negligible for large amplitu de pressure distortion.For the combined distortions

the pressure and temperature distortion orientations play a certain role in the compressor stall.The maximum loss in the compressor stall margin occurs at superimposed (180° overlap) combined distortion.Conversely

the effect is minimum for the opposite combined distortion.

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Related Institution

Control and Intelligent Systems Engineering,Faculty of Science,University of Hull,Hull HU6 7RX,United Kingdom

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National Key Laboratory of Science and Technology on Aero-Engines, School of Jet Propulsion, Beijing University of Aeronautics and Astronautics

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