Influences of the Area Changes of the Trailing Edge Structure of the Guide on the Turbine Performance

MA Xiaofeng; FENG Kaikai; SONG Wenyan

doi:10.16080/j.issn1671-833x.2016.23/24.095

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Influences of the Area Changes of the Trailing Edge Structure of the Guide on the Turbine Performance

更新时间：2025-10-30

- Influences of the Area Changes of the Trailing Edge Structure of the Guide on the Turbine Performance
- Aeronautical Manufacturing Technology Vol. 59, Issue 23/24, (2016)
- 作者机构：
  
  1. 海军装备部,西安,710021
  2. 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：10.16080/j.issn1671-833x.2016.23/24.095
  CLC：
- Published：2016
- 稿件说明：
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马晓峰，冯凯凯，宋文艳. 导向器尾缘结构面积变化对涡轮性能的影响[J]. 航空制造技术, 2016, 59(23/24): 95-99. MA Xiaofeng1, FENG Kaikai2, SONG Wenyan2. Influences of the Area Changes of the Trailing Edge Structure of the Guide on the Turbine Performance. Aeronautical Manufacturing Technology, 2016, 59(23/24): 95-99.

MA Xiaofeng, FENG Kaikai, SONG Wenyan. Influences of the Area Changes of the Trailing Edge Structure of the Guide on the Turbine Performance[J]. Aeronautical Manufacturing Technology, 2016, 59(23/24).
马晓峰，冯凯凯，宋文艳. 导向器尾缘结构面积变化对涡轮性能的影响[J]. 航空制造技术, 2016, 59(23/24): 95-99. MA Xiaofeng1, FENG Kaikai2, SONG Wenyan2. Influences of the Area Changes of the Trailing Edge Structure of the Guide on the Turbine Performance. Aeronautical Manufacturing Technology, 2016, 59(23/24): 95-99. DOI： 10.16080/j.issn1671-833x.2016.23/24.095.

MA Xiaofeng, FENG Kaikai, SONG Wenyan. Influences of the Area Changes of the Trailing Edge Structure of the Guide on the Turbine Performance[J]. Aeronautical Manufacturing Technology, 2016, 59(23/24). DOI： 10.16080/j.issn1671-833x.2016.23/24.095.

摘要

涡轮导向器尾缘的精细结构由于加工误差的存在，会导致流道流通面积的改变，进而会使涡轮性能发生改变。从实际工程问题出发，采用数值模拟的方法，研究了某型发动机低压涡轮导向器尾缘的“劈缝”冷却结构由于变形导致的尾缘前后（叶盆尾缘处流道面积T1 和叶背尾缘处流道面积T2）面积变化对涡轮流场和性能的影响。研究结果表明：在设计状态下，涡轮的喉道为T2；当T2 大于设计值时，涡轮功率和涡轮流量变大，涡轮效率和涡轮功变小，但是涡轮的功率存在一个最高值的T2；当T1 大于设计值时，涡轮效率和涡轮功增加

Abstract

The fine structure of the trailing edge of the turbine guide leads to a change in the flow area of the flow path due to machining errors

which in turn can cause a change in turbine performance. Numerical simulation method is used for the trailing edge of slot cooling structure in a low-pressure turbine guide to study the flow field and performance caused by the front and rear of the trailing edge (the area of flow passage in suction trailing edge is T1 and the area of flow passage in pressure trailing edge is T2 ) area changes. The results show that in the design state

the throat of turbine is T2. When T2 is bigger than that in the design state

the rate of work and mass flow of the turbine will become bigger

and the turbine efficiency and turbine power will become smaller

but it has a nice T2 to let the rate of power comes to maximum value. When T1 is bigger than that in the design state

the turbine efficiency and turbine power will increase.

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