通用核心机涡轮气动设计准则

推进技术 ›› 2011, Vol. 32 ›› Issue (2): 165-174.

通用核心机涡轮气动设计准则

付超,邹正平,刘火星,李维,周颖

北京航空航天大学能源与动力工程学院/航空发动机气动热力重点实验室,北京 100191;北京航空航天大学能源与动力工程学院/航空发动机气动热力重点实验室,北京 100191;北京航空航天大学能源与动力工程学院/航空发动机气动热力重点实验室,北京 100191;中国航空动力机械研究所,湖南株洲 412002;中国航空动力机械研究所,湖南株洲 412002

发布日期:2021-08-15
作者简介:付超(1986—),男,硕士,研究领域为叶轮机内部复杂流动。E-mail:fch34040109@126.com
基金资助:
国家自然科学基金(50776003)。

Turbine aerodynamic design criteria of versatile core

National Key Lab. of Science and Technology on Aero-Engines/Inst.of Thermo-PowerEngineening, Beijing Univ.of Aeronautics and Astronautics, Beijing 100191,China;National Key Lab. of Science and Technology on Aero-Engines/Inst.of Thermo-PowerEngineening, Beijing Univ.of Aeronautics and Astronautics, Beijing 100191,China;National Key Lab. of Science and Technology on Aero-Engines/Inst.of Thermo-PowerEngineening, Beijing Univ.of Aeronautics and Astronautics, Beijing 100191,China;Chinese Aviation Powerplant Research Inst., Zhuzhou 412002, China;Chinese Aviation Powerplant Research Inst., Zhuzhou 412002, China

Published:2021-08-15

摘要/Abstract

摘要： 针对通用核心机对涡轮部件性能的要求,尝试给出了描述涡轮气动通用性的定义,研究了速度三角形系列参数对涡轮气动通用性的影响规律,在此基础上,得到了通用核心机涡轮部件气动设计参数选取准则,并通过S2和三维数值模拟手段,利用一组真实涡轮的数据对涡轮气动通用性的定义和设计参数选取准则进行了验证。结果表明:在涡轮设计参数选择中,存在使涡轮部件气动通用性最优的速度三角形参数范围；一般情况下气动设计参数在Ω=0.35~0.45,μ=1.65~1.9,K₁=0.55~0.6区域内时,所设计的涡轮气动通用性较好；一系列涡轮气动设计参数的分析表明本文给出的涡轮部件气动通用性的定义和得到的涡轮部件气动设计参数选取准则基本合理。

关键词: 通用核心机;涡轮;速度三角形;气动设计;准则

Abstract: In allusion to the requirement of designing versatile core, a definition of the aerodynamics versatility of turbine was demonstrated. Primarily, by analyzing the laws that parameters of velocity triangle affect the aerodynamic versatility, a design criterion of designing turbine aerodynamics of versatile core was put forward. Then numerical simulation with S2 and 3D viscous solvers was carried out, comparing with a set of details of some real turbines, to validate the definition and laws which describes the aerodynamics versatility of turbine. The results indicate that there is a range of selecting velocity triangle parameters which may contribute to an optimal design of aerodynamics versatility of turbine, especially, when selecting the parameters of velocity triangle,Ω=0.35~0.45, μ=1.65~1.9, K₁=0.55~0.6, the aerodynamics versatility of turbine was proved to be good. The analysis of the parameters of aerodynamics design of turbines was provided, and thus it is reasonable and credible to conclude that the definition of the aerodynamics versatility of turbine and the laws of selecting the aerodynamics design factors to design versatile core are valid.

Key words: Versatile core; Turbine; Velocity triangles; Aerodynamic design; Criteria

付超,邹正平,刘火星,李维,周颖. 通用核心机涡轮气动设计准则[J]. 推进技术, 2011, 32(2): 165-174.

参考文献

[2] 黄顺洲,王永明,江和甫.核心机及其派生发动机发展的方法研究[J].燃气涡轮试验与研究, 5,8(2):1-5.
[3] Bolin G W, Field J, Kevin J B, et al.F414 engine today and growth potential for 21st century fighter mission challenges[R].ISABE 99-7113．
[4] 陈光.航空发动机结构设计分析[M].北京:北京航空航天大学出版社,2006:215-237.
[5] 黄顺洲,胡骏,江和甫.核心机及其派生发动机发展的方法[J].航空动力学报, 6,1(2):241-247.
[6] 黄顺洲,黄红超,李刚团,等.核心机技术在发动机研制中的作用和地位[J].航空制造技术,7,2(2):56-59.
[7] 唐海龙, 朱之丽, 罗安阳, 等.以已有核心机为基础进行发动机系列发展的初步研究[J].航空动力学报, 4,9(5):636-639.
[8] 胡晓煜．世界中小型航空发动机手册[M].北京:航空工业出版社,2006:83-86.
[9] 方昌德．世界航空发动机手册[M].北京:航空工业出版社,1996:54-57.
[10] AIAA Air Breathing Propulsion Technical Committee.The versatile affordable advanced turbine engines (VAATE) initiative[R].AIAA Position Paper, 2006.
[11] Air Force Research Laboratory of Propulsion Directorate.Versatile core force area[R].VAATE PRDAI Pre-Proposal Conference, 2002.
[12] Squadron L R.Turbine engine research in the united states air force[R].IEEE AERO 2001-931393.
[13] Charles J, Timothy J.Smart materials and structures for future aircraft engines[C].Reno:40th AIAA Aerospace Sciences Meeting and Exhibit,2002:14-17.
[14] Axel A.Defence aerospace[R].2008 Rolls-Royce Seminar, 2008.
[15] 尹泽勇,曾源江,石建成,等.涡轴(涡桨)/涡扇(涡喷)发动机通用核心机技术[J].航空动力学报, 8,3(11):2088-2094.
[16] Stewart W L.Analytical investigation of single stage-turbine efficiency characteristics in terms of work and speed requirements[R].NACA-RM-E56G1,6.
[17] 《航空发动机设计手册》总编委会.航空发动机设计手册第10册:涡轮[M].北京:航空工业出版社, 2000:25-27.