涡轮集气腔流动特性研究及流阻计算模型

推进技术 ›› 2017, Vol. 38 ›› Issue (2): 364-375.

涡轮集气腔流动特性研究及流阻计算模型

姚甜¹,毛军逵^1,2,蒋亮亮³,单文娟³,王海⁴,柴军生⁴,陆海鹰⁴

南京航空航天大学能源与动力学院，江苏省航空动力系统重点实验室，江苏南京 210016,南京航空航天大学能源与动力学院，江苏省航空动力系统重点实验室，江苏南京 210016; 先进航空发动机协同创新中心，北京 100191,中国商飞上海飞机设计研究院，上海 201102,中国商飞上海飞机设计研究院，上海 201102,中航工业沈阳发动机设计研究所，辽宁沈阳 110015,中航工业沈阳发动机设计研究所，辽宁沈阳 110015,中航工业沈阳发动机设计研究所，辽宁沈阳 110015

发布日期:2021-08-15
作者简介:姚甜，女，硕士生，研究领域为航空发动机传热传质。

Experimental Investigation on Flow Characteristics of Turbine Plenum Chamber and Flow Resistance Model

Nanjing University of Aeronautics and Astronautics，Jiangsu Province Key Laboratory of Aerospace Power System，Nanjing 210016，China,Nanjing University of Aeronautics and Astronautics，Jiangsu Province Key Laboratory of Aerospace Power System，Nanjing 210016，China; Collaborative Innovation Center for Advanced Aero-Engine，Beijing，100191，China,Chinese COMAC Shanghai Aircraft Design and Research Institute，Shanghai，201102，China,Chinese COMAC Shanghai Aircraft Design and Research Institute，Shanghai，201102，China,AVIC Shenyang Aeroengine Research Institute，Shenyang，110015，China,AVIC Shenyang Aeroengine Research Institute，Shenyang，110015，China and AVIC Shenyang Aeroengine Research Institute，Shenyang，110015，China

Published:2021-08-15

摘要/Abstract

摘要： 为了探究航空发动机涡轮集气腔的流动特性，对4个主进气口、双排125个出流孔的涡轮集气腔出口流量分配规律和流阻系数进行了实验研究，重点分析了进出口压比、集气腔腔室高度等参数变化带来的影响。研究发现，正对主进气口的出流孔流量最大，而紧邻其两侧的周向出流孔流量明显减小。随着出流孔周向位置远离主进气口，出流孔流量迅速恢复并基本维持一个定值。但是位于每2个主进气口间1/2周向夹角位置，会出现最小的出流流量。实验结果表明，尽管周向上局部出流孔出现了极大和极小出流流量，但其仅为进口总流量的9.34%和3.29%。在本文实验参数范围内，随着进出口压比、集气腔高度的增加，通过集气腔的空气流量均变大，但并没有改变周向出流孔的流量分配规律。两者相比，集气腔高度带来的影响明显微弱。最终本文拟合得到了流阻损失系数同集气腔几何参数、进/出口气动参数之间的经验关系式，并将其应用于开发的一维空气系统集气腔元件中，为后续空气系统的设计与优化提供依据。

关键词: 空气系统；涡轮集气腔；流量分配；流阻损失；经验关系式

Abstract: To obtain the flow characteristics of turbine plenum chamber such as the distribution of outflow and the flow resistance coefficient，a typical configuration，which has 4 air intakes and 125 exit holes located in two lines，was experimentally investigated. The ratio of inlet pressure to outlet pressure ，the chamber height were changed in experiments，then the flow characteristics of turbine plenum varying with these parameters were obtained. It was found that the holes directly facing the entrance had the maximum flow rate，while flow rate decreased greatly in the region very near those holes. As the holes’circumferential locations were away from the entrance，their flow rate quickly recovered and remained alomost the same. Meanwhile the minimum outflow rate was observed in the holes located circumferentially at the middle region between every two inlet holes. However these maximum and minimum mass flow rates were only 9.34% and 3.29% of the total flow，respectively. It was also found that with the increasing of inlet pressure and chamber height，the mass flow rate going through turbine plenum chamber increased，while the distribution of circumferential outflow did not change. Compared against inlet pressure，chamber height affected flow characteristics much more faintly. Finally correlation equations about flow resistance were concluded in this paper，which took geometrical parameters and inflow/outflow aerodynamic parameters into account. One dimensional component of turbine plenum chamber for secondary air system was also developed based on those correlation equations，which can support the design and optimization of secondary air system.

Key words: Secondary air system；Turbine plenum chamber；Flow distribution；Flow resistance；Correlation equations

姚甜,毛军逵,蒋亮亮,单文娟,王海,柴军生,陆海鹰. 涡轮集气腔流动特性研究及流阻计算模型[J]. 推进技术, 2017, 38(2): 364-375.

YAO Tian¹,MAO Jun-kui^1,2,JIANG Liang-liang³,SHAN Wen-juan³,WANG Hai⁴,CHAI Jun-sheng⁴,LU Hai-ying⁴. Experimental Investigation on Flow Characteristics of Turbine Plenum Chamber and Flow Resistance Model[J]. Journal of Propulsion Technology, 2017, 38(2): 364-375.

参考文献

[1] Rolls-Royce. The Jet Engine[M]. England: The Technical Publications Department, 1996.
[2] 沈毅, 李云单, 吕春雁, 等. CFD技术在航空发动机空气系统设计中的应用[J]. 航空发动机, 2011, 37(3): 34-37.
[3] 赵曙, 朱惠人, 杜晓琴, 等. 涡轮集气腔流动特性实验研究[C]. 贵阳:中国航空学会第七届动力年会论文摘要集, 2010.
[4] 曾军, 王鹏飞. 民用航空发动机涡轮叶尖间隙主动控制技术分析[J]. 航空科学技术, 2012, (2): 1-6.
[5] 周骁, 张海波, 王继强, 等. 考虑主动间隙控制的涡轮叶尖间隙建模计算研究[J]. 推进技术, 2015, 36(7): 1093-1102. (ZHOU Xiao, ZHANG Hai-bo, WANG Ji-qiang, et al. Research on Turbine Tip Clearance Modeling Considering Active Tip Clearance Control[J]. Journal of Propulsion Technology, 2015, 36(7): 1093-1102.)
[6] 姜远刚, 毛军逵, 李毅, 等. 间隙主动控制系统中冷却空气管换热特性实验研究[J]. 推进技术, 2014, 35(3): 365-371. (JIANG Yuan-gang, MAO Jun-kui, LI Yi, et al. Experimental Studies on Heat Transfer Characteristics in Air Cooling Pipe of Turbine Tip Clearance Control System[J]. Journal of Propulsion Technology, 2014, 35(3): 365-371.)
[7] Riccardo Da Soghe, Antonio Andreini. Numerical Characterization of Pressure Drop across the Manifold of Turbine Casing Cooling System[R]. ASME GT2013-031017-1.
[8] DaSoghe R, Maiuolo F, Tarchi L, et al. Discharge Coefficient Characterization of Jet Array Impingement Holes for an Active Clearance Control System[R]. Proceedings of the ETC, ETC2011-252.
[9] Andreini A, Da Soghe R, Facchini B, et al. Experimental and Numerical Analysis of Multiple Impingement Jet Arrays for an Active Clearance Control System[R]. ASME GT2012-68791.
[10] 姜远刚. 间隙主动控制系统中冷却流路流动特性/换热特性研究[D]. 南京:南京航空航天大学, 2013.
[11] 王峻晔, 葛晓陵, 吴东棣. 分支流理论研究进展[J]. 力学进展, 1998, 28(3): 392-401.
[12] McNown J S. Mechanics of Manifold Flow[J]. Trans ASCE, 1954, 119: 1103-1142.
[13] Bassiouny M K, Martin H. Flow Distribution and Pressure Drop in Plate Heat Exchangers [J]. Chemical Engineering Science, 1984, 39(4): 693-700.
[14] 吴玮, 严忠民. 多分支管道若干流动特性研究[J]. 河海大学学报:自然科学版, 2004, 32(3): 272-275.
[15] 廖振强. 多分支管道若干流动现象和特性的探讨[J]. 气动实验与测量控制, 1996, 10(3): 31-40.
[16] 廖振强. 数值模拟具有四个腔室的多分支管道二维非定常流动[J]. 气动实验与测量控制, 1996, 10(4):18-26.
[17] Wang J Y. Theory of Flow Distribution in Manifolds [J]. Chemical Engineering Journal, 2011, 168: 1331-1345.
[18] 钟贤和, 张力, 伍成波. 较大流量多支管流量分配实验与数值模拟[J]. 重庆大学学报(自然科学版), 2006, 29(1): 41-44.
[19] 缪斌. 并联管组流量分配的模拟计算和实验研究[D]. 西安:西安石油大学, 2011.
[20] 朱玉琴, 缪斌. 并联管组流动特性的数值模拟[J]. 西安石油大学学报(自然科学版), 2011, 36(3): 94-96.
[21] 华绍曾, 杨学宁. 实用流体阻力手册[M]. 北京:国防工业出版社, 1985. 　收稿日期:2015-08-22；修订日期:2015-11-05。作者简介:姚甜,女,硕士生,研究领域为航空发动机传热传质。E-mail: Yao_lliana@163.com(编辑:张荣莉)