Design technology of a variable curvature blade type swirl distortion generator

Xinyu ZHANG; Baofeng TU; Rui FANG; Guang YANG

doi:10.13224/j.cnki.jasp.20210343

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Design technology of a variable curvature blade type swirl distortion generator

Turbomachinery | 更新时间：2025-03-14

- Design technology of a variable curvature blade type swirl distortion generator
- Journal of Aerospace Power Vol. 37, Issue 9, Pages: 1957-1969(2022)
- 作者机构：
  
  南京航空航天大学能源与动力学院，南京 210016
- 作者简介：
- 基金信息：
- DOI：10.13224/j.cnki.jasp.20210343
  CLC：
- 稿件说明：
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Xinyu ZHANG, Baofeng TU, Rui FANG, et al. Design technology of a variable curvature blade type swirl distortion generator[J]. Journal of Aerospace Power, 2022, 37(9): 1957-1969.
DOI：

Xinyu ZHANG, Baofeng TU, Rui FANG, et al. Design technology of a variable curvature blade type swirl distortion generator[J]. Journal of Aerospace Power, 2022, 37(9): 1957-1969. DOI： 10.13224/j.cnki.jasp.20210343.

摘要

为了研究进气旋流畸变对压气机性能和稳定性的影响，设计了一种能够产生典型对涡与整体涡可变弯度叶片式旋流畸变发生器。结合正交仿真试验设计方法，分别以对涡旋流强度为优化目标和以对涡旋流强度、整体涡旋流强度和整体涡总压恢复系数为综合优化目标对旋流畸变发生器的几何参数，包括叶片稠度、叶片数量以及轮毂比等进行气动优化设计，并采用CFD数值模拟仿真研究了旋流畸变发生器生成旋流特征。经过单指标优化分析，旋流畸变发生器生成对涡旋流强度最高可达24.60°，整体涡旋流强度最高可达38.73°。经过多指标综合优化，旋流畸变发生器生成对涡和整体涡的总压恢复系数分别提高了4.26%和3.57%。叶片式旋流畸变发生器设计具有结构简单、操作方便、试验周期短等优点，并具有较好的工程应用性。

Abstract

In order to study the effect of inlet swirl distortion on the performance and stability of a compressor，a variable curvature blade type swirl distortion generator capable of producing typical twin swirls and bulk swirls was designed.In combination with the design method of orthogonal simulation test，the geometric parameters of the swirl distortion generator，including blade solidity，number of blades and hub ratio，were optimized with twin swirl intensity as the optimization objective and twin swirl intensity，bulk swirl intensity and bulk swirl total pressure recovery coefficient as the comprehensive optimization objectives，and the CFD numerical simulation was used to study the characteristics of the swirl produced by the generator.Under the single object optimization，the maximum twin swirl intensity was 24.60°，and the maximum bulk swirl intensity was 38.73°.After multi⁃index optimization design，the total pressure recovery coefficient of the twin swirl and the bulk swirl was improved by 4.26%and 3.57%，respectively.The design of the variable curvature blade type distortion generator has the advantages of simple structure，convenient operation，short testing time，presenting a favorable engineering application prospect.

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references

AULEHLA F . Intake swirl：a major disturbance parameter in engine/intake compatibility [C]∥ Proceedings of the 13th congress of International Council of the Aeronautical Sciences . Seattle,US : International Council of the Aeronautical Sciences , 1982 : 1415 ⁃ 1424 .

LOTTER K W , JORG J . The effect of intake flow disturbances on APU compressor blade high cycle fatigue in the Airbus A300 [R].AIAA CAS⁃82⁃4. 6 , 1982 .

姜健 , 屈霁云 , 史建邦 . 进气道旋流发生器的设计与数值模拟 [J]. 燃气涡轮试验与研究 , 2008 , 21 （ 1 ）: 43 ⁃ 46 .

JIANG Jian , QU Jiyun , SHI Jianbang . Design and numerical simulation of intake swirl generator [J]. Gas Turbine Experiment and Research , 2008 , 21 （ 1 ）: 43 ⁃ 46 . （in Chinese）

GENSSLER H P , MEYER W , FOTTNER L . Development of intake swirl generators for turbo jet engine testing [R]. DTIC （Defense Technical Information Center） Document,ADP005473 , 1987 .

SCHMID N R , LEINHOS D C , FOTTNER L . Steady performance measurements of a turbofan engine with inlet distortions containing co⁃and counter rotating swirl from an intake diffuser for hypersonic flight [J]. Journal of Turbomachinery , 2001 , 123 （ 2 ）: 379 ⁃ 385 .

PAZUR W , FOTTNER L . The influence of inlet swirl distortions on the performance of a jet propulsion two⁃stage axial compressor [R]. ASME Paper 90⁃GT⁃147 , 1990 .

FLITCROFT J E , DUNHAM J , ABBOTT W A . Transmission of inlet distortion through a fan [R]. DTIC （Defense Technical Information Center） Document,ADP005469 , 1987 .

GOVARDHAN M , VISWANATH K . Investigations on an axial flow fan stage subjected to circumferential inlet flow distortion and swirl [J]. Journal of Thermal Science , 1997 , 6 （ 4 ）: 241 ⁃ 250 .

DAVID B , KEVIN C , PETER K . Development of improved method for simulating aircraft inlet distortion in turbine engine ground tests [R]. AIAA⁃2002⁃3045 , 2002 .

SHEORAN Y , BOULDIN B , KRISHNAN P M . Advancements in the design of an adaptable swirl distortion generator for testing gas turbine engines [R]. ASME Paper GT2009⁃59146 , 2009 .

DAVIS M , BEALE D , SHEORAN Y . Integrated test and evaluation techniques as applied to an inlet swirl investigation using the F109 gas turbine engine [R]. ASME Paper GT2008⁃50074 , 2008 .

SHEORAN Y , BOULDIN B , KRISHNAN P . Compressor performance and operability in swirl distortion [J]. Journal of Turbomachinery , 2012 , 134 （ 4 ）: 2453 ⁃ 2464 .

KEVIN M H , WALTER F , O'BRIEN W F . The streamvane method：a new way to generate swirl distortion for jet engine research [R]. AIAA⁃2013⁃3665 , 2013 .

NELSON M , LOWE K T ， O'BRIEN W F , et al . Stereoscopic PIV measurements of swirl distortion on a full⁃scale turbo⁃fan engine inlet [R]. AIAA⁃2014⁃0533 , 2014 .

GUIMARÃES T , LOWE K T ， NELSON M , et al . Stereoscopic PIV measurements in a turbofan engine inlet with tailored swirl distortion [R]. AIAA⁃2015⁃2866 , 2015 .

张磊 . 新型旋流畸变网的设计及与跨声速压气机联合仿真研究 [D]. 西安 : 空军工程大学 , 2018 .

ZHANG Lei . Design of new type of swirl distortion screen and joint simulation with a transonic compressor [D]. Xi'an ： Air Force Engineering University , 2018 . （in Chinese）

屠宝锋 , 胡骏 , 尹超 . 叶片式旋流畸变发生器数值模拟研究 [J]. 推进技术 , 2015 , 36 （ 12 ）: 1817 ⁃ 1824 .

TU Baofeng , HU Jun , YIN Chao . Numerical simulation for blade type swirl distortion generator [J]. Journal of Propulsion Technology , 2015 , 36 （ 12 ）: 1817 ⁃ 1824 . （in Chinese）

叶飞 . 进气道出口旋流模拟技术 [D]. 南京 : 南京航空航天大学 , 2007 .

YE Fei . Simulated technology of intake swirl [D]. Nanjing ： Nanjing University of Aeronautics and Astronautics , 2007 . （in Chinese）

宋国兴 , 李军 , 周游天 , 等 . 轴流压气机进气旋流畸变实验与仿真研究 [J]. 风机技术 , 2017 , 59 （ 5 ）: 2 ⁃ 12 .

SONG Guoxing , LI Jun , ZHOU Youtian , et al . The experiment and simlation of inlet swirl distortion for axial compressor [J]. Chinese Journal of Turbomachinery , 2017 , 59 （ 5 ）: 2 ⁃ 12 . （in Chinese）

Society of Automotive Engineers . A method for assessing inlet swirl distortion [R]. S16 Turbine Engine Inlet Flow Distortion Committee,AIR 5686 , 2010 .

彭成一 , 马家驹 , 尹军飞 . 新机试飞中的进气道旋流测量 [J]. 推进技术 , 1994 , 15 （ 4 ）: 8 ⁃ 13 .

PENG Chengyi , MA Jiaju , YIN Junfei . Measurement of inlet swirls in flight [J]. Journal of Propulsion Technology , 1994 , 15 （ 4 ）: 8 ⁃ 13 . （in Chinese）

费智聪 . 熵权‑层次分析法与灰色‑层次分析法研究 [D]. 天津：天津大学 , 2009 .

FEI Zhicong . Study on the hierarchy analysis based on entropy method‑hierarchy analysis and gray relational analysis method [D]. Tianjin ： Tianjin University , 2009 . （in Chinese）

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