Dynamic changes rule of aero-engine turbine tip clearance in maneuver flight

JIA Bing-hui; ZHANG Xiao-dong; PENG Kai

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Dynamic changes rule of aero-engine turbine tip clearance in maneuver flight

更新时间：2026-07-07

- Dynamic changes rule of aero-engine turbine tip clearance in maneuver flight
- Vol. 26, Issue 12, (2011)
- 作者机构：
  
  西北工业大学动力与能源学院,西安,710072
- 作者简介：
- 基金信息：
- DOI：
  CLC：
- Published：2011
- 稿件说明：
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JIA Bing-hui, ZHANG Xiao-dong, PENG Kai. Dynamic changes rule of aero-engine turbine tip clearance in maneuver flight[J]. 2011, 26(12).
DOI：

JIA Bing-hui, ZHANG Xiao-dong, PENG Kai. Dynamic changes rule of aero-engine turbine tip clearance in maneuver flight[J]. 2011, 26(12). DOI：

摘要

在对涡轮叶尖间隙的变化机理进行初步分析的基础上

建立机匣、叶片和转子的简化模型

并重点研究了转子在飞行器机动飞行情况下的振动幅值对叶尖间隙的影响.结果表明:高压涡轮叶尖间隙动态变化范围约为0.44mm到1.45mm

同时飞行器均加速导致的转子振动会引起间隙局部增大或减小

俯仰机动和水平盘旋机动飞行都会使得间隙动态变化的非线性明显增强.

Abstract

Based on the preliminary analysis of the change mechanism of the turbine blade tip clearance

the simplified model of blade

rotor and casing was established

and the effect of rotor vibration amplitude of aero craft in-flight maneuver state was researched.The results show:reduction of clearance is approximately 0.44 to 1.45 mm;local tip clearance would increase or decvease caused by uniformity acceleration of aero craft;pitching maneuver and horizontal circling would bring vibration of tip clearance

which makes the nonlinear of clearance variation markedly enhanced.

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