PDF下载 分享
[1]姜金朋,石竟成,苏立超,等.叶型尺寸比例变化对预测涡轮气动性能和气动力的影响[J].火箭推进,2018,44(06):29-38.
　JIANG Jinpeng,SHI Jingcheng,SU Lichao,et al.Effects of airfoil scaling on the predicted aerodynamic performance and forcing of turbine[J].Journal of Rocket Propulsion,2018,44(06):29-38.
点击复制

叶型尺寸比例变化对预测涡轮气动性能和气动力的影响

《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V] 卷: 44 期数: 2018年06期 页码: 29-38 栏目: 研究与设计 出版日期: 2018-12-31
Title:
Effects of airfoil scaling on the predicted aerodynamic performance and forcing of turbine
文章编号:
1672-9374(2018)06-0029-10
作者:
姜金朋1; 石竟成1; 苏立超1; 巩 帆1; 王 珏2
1.中国运载火箭技术研究院 空间物理重点实验室,北京 100076; 2.中国运载火箭技术研究院,北京 100076
Author(s):
JIANG Jinpeng1;  SHI Jingcheng1;  SU Lichao1;  GONG Fan1;  WANG Jue2
1.Science and Technology on Space Physics Laboratory, China Academy of Launch Vehicle Technology, Beijing 100076, China; 2.China Academyof Launch Vehicle Technology, Beijing 100076, China
关键词:
叶型比例变化;  数值模拟;  气动性能;  气动力
Keywords:
airfoil scaling;  numerical simulation;  aerodynamic performance;  aerodynamic forcing
分类号:
V434+.11-34
文献标志码:
A
摘要:
以某火箭发动机涡轮为对象,研究了动静叶叶型尺寸比例变化技术对预测涡轮气动性能和非定常气动力的影响。该涡轮为一级轴流涡轮,含18个静叶和32个动叶。针对不同比例系数变化的结构进行了三维定常和非定常数值模拟,以原始结构作为基准算例进行对比分析。结果表明,动静叶比例变化对定常和非定常时均叶片压力和性能预测影响很小,尺寸变化超过10%时,预测偏差不到2%。对时域上的非定常压力和气动力进行快速傅立叶变换(FFT)得到频域特性。分析表明,比例变化对频率特性的预测几乎没有影响,而对幅值特性影响很大,预测的幅值偏差与变化比例大小没有直接关系,但是尺寸变化较小的情况确实显示出相对稳定且较小的预测偏差。
Abstract:
Effects of vane/blade airfoil scaling on the prediction of aerodynamic performance and unsteady forcing have been investigated for the turbine.A single-stage axial-flow turbine with 18 vanes and 32 blades was adopted.3D steady and unsteady simulations were conducted for configurations with different scaling factors, and the full-scale case was used as the baseline simulation.The results show that the vane/blade airfoil scaling has little influence on the steady and time-averaged pressure on the blade and performance of turbine.The predicted deviation is below 2% even if the scaling deviation exceeds 10%.The fast Fourier transform(FFT)is used to transform the unsteady pressure and forcing predicted in the time domain to obtain the characteristics in the frequency domain.The vane/blade airfoil scaling has little difference on the frequency characteristics of unsteady pressure and aerodynamic forces, while amplitude is greatly affected.The results show that the predicted amplitude deviation is not directly related to the scaling deviation, but the case with small scaling deviation(3.125% in this study)indeed shows relatively stable and minor error.

参考文献/References:

[1] CIZMAS P G A, DORNEY D J.The influence of clocking on unsteady forces of compressor and turbine blades[J].International journal of turbo jet-engines, 2000, 17: 133-142.
[2] PARK J Y, CHOI M S, BACK J H.Effects of axial gap on unsteady secondary flow in one-stage axial turbine[J].International journal of turbo jet-engines, 2003, 20: 315-333.
[3] CHANG D, TAVOULARIS S.Effect of the axial spacing between vanes and blades on a transonic gas turbine performance and blade loading[J].International journal of turbo jet-engines, 2013, 30(1): 15-31.
[4] TANG E, LEROY G, PHILIT M, et al.Unsteady analysis of inter-rows stator-rotor spacing effects on a transonic, low-aspect ratio turbine [C]//Proceedings of ASME Turbo Expo 2015: Turbine Technical Conference and Exposition.Montréal, Canada, GT2015-42227, 2015
[5] FENG Z P, LI H T, SONG L M, et al.Aerodynamic inverse design optimization for turbine cascades based on control theory[J].Science China technological sciences, 2013, 56(2): 308-323.
[6] 李旭升,郑继坤,吴玉珍.某型超音速冲击式氧涡轮叶型气动优化[J].火箭推进, 2014, 40(5): 44-49.
LI X S, ZHENG J K, WU Y Z.Aerodynamic optimization for blade profile of a supersonic impulse oxygen turbine[J].Journal of rocket propulsion, 2014, 40(5): 44-49.
[7] 郑晓宇,林奇燕,王磊.小型部分进气亚声速涡轮流动损失研究及优化[J].火箭推进, 2017, 43(1): 32-37.
ZHENG X Y, LIN Q Y, WANG L.Research and optimization for flow loss of a small partial admission subsonic turbine[J].Journal of rocket propulsion, 2017, 43(1): 32-37.
[8] KIM J H, CHOI K J, KIM K Y.Aerodynamic analysis and optimization of a transonic axial compressor with casing grooves to improve operating stability[J].Aerospace science and technology, 2013, 29: 81-91
[9] KAWATSU K, TANI N, YAMANISHI N.Numerical study on rotor-stator interaction of a supersonic reaction turbine for a liquid rocket engine[C]//Proceedings of the ASME 2010 3rd Joint US-European Fluids Engineering Summer Meeting and 8th International Conference on Nanochannels, Microchannels, and Minichannels.Montreal, Montreal, Canada, FEDSM-ICNMM2010-30640, 2010.
[10] ZHAO B, YANG C, CHEN S, et al.Unsteadyflow variability driven by rotor-stator interaction at rotor exit[J].Chinese journal of aeronautics, 2012, 25(6): 871-878.
[11] DORNEY D J, GRIFFIN L W, HUBER F, et al.Unsteady flow in a supersonic turbine with variable specific heats[J].Journal of propulsion, 2001, 18(2): 493-496.
[12] DORNEY D J, GRIFFIN L W, HUBER F, et al.Off-design performance of a multi-stage supersonic turbine[C]//41st Aerospace Sciences Meeting and Exhibit, Reno, Nevada, AIAA, 2003
[13] HUDSON S T, ZOLADZ T F, DORNEY D J.Rocket engine turbine blade surface pressure distributions: experiment and computations[J].Journal of propulsion and power, 2003, 19(3): 364-373.
[14] TOKUYAMA Y, FUNAZAKI K, KATO H.Computational analysis of unsteady flow in a partial admission supersonic turbine stage[C]//Proceedings of ASME Turbo Expo 2014: Turbine Technical Conference and Exposition, Düsseldorf, Germany, GT2014-26071, 2014
[15] SAKAI N, HARADA T IMAI Y0.Numerical study of partial admission stages in steam turbine[J].JSME international journal series B, 2006, 49(2): 212-217.

相似文献/References:

[1]崔明功,郭 然.环形引射器流场研究[J].火箭推进,2015,41(02):75.
　CUI Ming-gong,GUO Ran.Study on flow field of annular ejector[J].Journal of Rocket Propulsion,2015,41(06):75.
[2]刘昌波,周立新,雷凡培.雾化过程的数值模拟研究综述[J].火箭推进,2014,40(01):10.
　LIU Chang-bo,ZHOU Li-xin,LEI Fan-pei.Overview on numerical simulations of primary atomization[J].Journal of Rocket Propulsion,2014,40(06):10.
[3]南向军.带抑流楔升力前体设计初探[J].火箭推进,2014,40(01):50.
　NAN Xiang-jun.Design of lift-forebody with transverse flow restraining wedge[J].Journal of Rocket Propulsion,2014,40(06):50.
[4]王海韵,王长辉,范匆.结构参数设计对微喷管性能的影响[J].火箭推进,2017,43(05):14.
　WANG Haiyun,WANG Changhui,FAN Cong.Effects of structure parameter design onperformance of micro-nozzle[J].Journal of Rocket Propulsion,2017,43(06):14.
[5]赵 鼎,刘 琳,孙龙飞.钛合金夹层结构扩散钎焊工艺研究[J].火箭推进,2018,44(01):67.
　ZHAO Ding,LIU Lin,SUN Longfei.Study on diffusion brazing process for titanium alloy sandwich structure[J].Journal of Rocket Propulsion,2018,44(06):67.
[6]高兴峰,张建伟,孙 冰,等.推力室头部最优气膜参数研究[J].火箭推进,2018,44(02):10.
　GAO Xingfeng,ZHANG Jianwei,SUN Bing,et al.Study on optimal gas film parameters of near-injection region in thrust chamber[J].Journal of Rocket Propulsion,2018,44(06):10.
[7]徐鸿鹏,张志涛,唐斌运,等.发动机试验液氧贮箱放气系统动态特性研究[J].火箭推进,2018,44(05):71.
　XU Hongpeng,ZHANG Zhitao,TANG Binyun,et al.Study on dynamic characteristics of gas-exhaust-system for liquid oxygen tank used for liquid rocket engine ground test[J].Journal of Rocket Propulsion,2018,44(06):71.
[8]宋大亮,凌前程,章荣军.双组元离心式喷嘴外喷嘴流动数值模拟分析[J].火箭推进,2018,44(04):10.
　SONG Daliang,LING Qiancheng,ZHANG Rongjun.Numerical analysis on flow characteristics of outer nozzle of bipropellant pressure-swirl injector[J].Journal of Rocket Propulsion,2018,44(06):10.
[9]杨瑞康,张勤练,周 舟,等.推力室外壁机器人自适应焊接控制研究[J].火箭推进,2019,45(01):66.
　YANG Ruikang,ZHANG Qinlian,ZHOU Zhou,et al.Research on robot adaptive welding control of thrust chamber outer wall[J].Journal of Rocket Propulsion,2019,45(06):66.
[10]周璟莹,邹伟龙,黄立还.冲压发动机风洞引射器引射性能模拟[J].火箭推进,2019,45(02):53.
　ZHOU Jingying,ZOU Weilong,HUANG Lihuan.Simulation study on ejection performance of ramjet engine wind tunnel ejector[J].Journal of Rocket Propulsion,2019,45(06):53.

备注/Memo

Received date:2018-01-26; Revised date: 2018-04-23 Biography:JIANG Jinpeng(1988—), female, Ph.D., engineer, specialized in rocket engines

更新日期/Last Update: 2018-12-25