1+3/2级对转涡轮气动性能试验研究

吴中野; 方祥军; 刘思永; 赵大勇

doi:10.13700/j.bh.1001-5965.2015.0849

1+3/2级对转涡轮气动性能试验研究

doi: 10.13700/j.bh.1001-5965.2015.0849

1.
北京航空航天大学能源与动力工程学院, 北京 100083
2.
中航工业沈阳发动机设计研究所, 沈阳 110015

详细信息

作者简介:
吴中野, 男, 博士研究生。主要研究方向:涡轮设计与试验研究。E-mail:wuzhongye@126.com

通讯作者:
方祥军, 男, 博士, 研究生导师。主要研究方向:叶轮机设计与气动研究。Tel.:010-82317421, E-mail:turbinebuaa@buaa.edu.cn

中图分类号: V221
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出版历程
- 收稿日期: 2015-12-28
- 录用日期: 2016-03-18
- 网络出版日期: 2017-12-20

Experimental research of 1+3/2 contra-rotating turbine aerodynamic performance

1.
School of Energy and Power Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100083, China
2.
AVIC Shenyang Engine Design Institute, Shenyang 110015, China

More Information

Corresponding author: Tel.:010-82317421, E-mail:turbinebuaa@buaa.edu.cn

摘要

摘要:
无导叶对转涡轮是高性能发动机的关键技术之一。本文采用试验方法对1+ 3/2级对转涡轮进行了气动性能研究。本试验分为3个阶段，第1阶段为单独高压涡轮（HPT）试验，第2阶段为加大HPT和低压涡轮（LPT）间轴向间距联合试验，第3阶段为HPT和LPT间正常轴向间距联合试验。在正常轴向间距HPT和LPT试验中，LPT状态的确定通过利用单独HPT试验获得的效率与压比特性反推获得。试验表明，HPT喉道面积减小，而LPT喉道面积增大，这导致在总膨胀比一定情况下，HPT膨胀比增大，LPT膨胀比下降，同时LPT的存在对HPT特性影响不大。在总膨胀比分配中，HPT膨胀比变化很小，而LPT膨胀比变化范围较宽。涡轮级总效率由HPT决定，LPT轮一般相对较低，加大HPT和LPT间轴向间距对LPT性能影响很小。
- 对转涡轮 /
- 试验方法 /
- 特性反推 /
- 膨胀比分配 /
- 效率特性
Abstract:
Vaneless contra-rotating turbine is one of the key technologies of the high performance engine. Experimental research was conducted to investigate aerodynamic performance of 1+3/2 contra-rotating turbine. The experiment was tested over three phases:first the alone high pressure turbine (HPT) experiment, second the HPT and low pressure turbine (LPT) with axial gap enlarging between them, and finally HPT and LPT with normal axial gap. In the normal gap experiment, the condition of LPT was confirmed by HPT performance curve by converse calculation. Research shows that LPT has little effect on HPT performance; HPT throat decreases while LPT throat increases, which leads to HPT expansion ratio increasing at the constant total expansion ratio. HPT expansion ratio changes very little during the total expansion ratio varying; however LPT expansion ratio changes greatly. The turbine efficiency is mainly determined by HPT, and the LPT is generally relative low. Enlarging axial gap between HPT and LPT has little influence on LPT performance.
- contra-rotating turbine /
- experimental method /
- converse performance calculation /
- expansion ratio distribution /
- efficiency performance

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图 1 超跨音对转涡轮试验台简图

Figure 1. Schematic of supersonic and transonic contra-rotating turbine facility

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图 2 加大高低压涡轮轴向间距子午流道

Figure 2. Meridional channel of increasing axial gap between HPT and LPT

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图 3 高压涡轮出口相对气流角

Figure 3. Outlet relative flow angle of HPT

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图 4 1+3/2级对转涡轮测试截面

Figure 4. Test section of 1+3/2 contra-rotating turbine

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图 5 高压涡轮流量特性、效率特性及出口绝对气流角

Figure 5. Mass flow performance, efficiency performance and outlet absolute flow angle

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图 6 高压涡轮动叶进口速度三角形变化

Figure 6. Change of HPT rotor inlet velocity triangle

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图 7 带低压涡轮的高压涡轮效率特性和流量特性

Figure 7. Efficiency performance and mass flow performance of HPT with LPT

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图 8 低压涡轮流量特性

Figure 8. Mass flow performance of LPT

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图 9 高低压涡轮联合试验效率与膨胀比分配

Figure 9. Efficiency and expansion ratio distribution of HPT and LPT

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图 10 涡轮总效率特性

Figure 10. Total efficiency performance of turbine

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图 11 动叶叶顶间隙对涡轮效率的影响^[18]

Figure 11. Effect of rotor tip clearance on turbine efficiency^[18]

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表 1 原型涡轮设计参数

Table 1. Design parameters of original turbine

参数	数值
参数	高压涡轮	低压涡轮
折合转速/(r·min^-1·^-1)	352.3	274.5
折合流量/(kg·s^-1··kPa^-1)	1.23	3.49
折合功/(J·K^-1)	245.5	180.9
总对总绝热效率	0.90	0.89
膨胀比	2.686 2	2.088 8

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