SAE AIR 5686-2010 A Methodology for Assessing Inlet Swirl Distortion《进气道涡流变形评定方法》.pdf

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1、_ SAE Technical Standards Board Rules provide that: “This report is published by SAE to advance the state of technical and engineering sciences. The use of this report is entirely voluntary, and its applicability and suitability for any particular use, including any patent infringement arising there

2、from, is the sole responsibility of the user.” SAE reviews each technical report at least every five years at which time it may be revised, reaffirmed, stabilized, or cancelled. SAE invites your written comments and suggestions. Copyright 2017 SAE International All rights reserved. No part of this p

3、ublication may be reproduced, stored in a retrieval system or transmitted, in any form or by any means, electronic, mechanical, photocopying, recording, or otherwise, without the prior written permission of SAE. TO PLACE A DOCUMENT ORDER: Tel: 877-606-7323 (inside USA and Canada) Tel: +1 724-776-497

4、0 (outside USA) Fax: 724-776-0790 Email: CustomerServicesae.org SAE WEB ADDRESS: http:/www.sae.org SAE values your input. To provide feedback on this Technical Report, please visit http:/standards.sae.org/AIR5686 AEROSPACE INFORMATION REPORT AIR5686 Issued 2010-10 Reaffirmed 2017-07 A Methodology fo

5、r Assessing Inlet Swirl Distortion RATIONALE AIR5686 has been reaffirmed to comply with the SAE Five-Year Review policy. FOREWORD In some instances, inlet/engine compatibility may not be adequately described by consideration of total-pressure distortion, total-temperature distortion, or planar waves

6、, either singularly or in combination. Many gas turbine installations can generate significant flow angularity (“swirl”) as well as total-pressure distortion at the Aerodynamic Interface Plane (AIP). The SAE S-16 Turbine Engine Inlet Flow Distortion Committee has recognized the need for a methodolog

7、y for assessing swirl distortion to be used in conjunction with SAE document ARP1420 which was written for inlet spatial total-pressure distortion. This Aerospace Information Report brings together information and ideas which provide a framework for addressing swirl distortion. A common industry pra

8、ctice has yet to be established. TABLE OF CONTENTS 1. SCOPE 4 2. APPLICABLE DOCUMENTS 4 2.1 SAE Publications . 4 2.2 Other Applicable Documents 4 2.3 Definitions . 11 3. SUMMARY 14 4. PROBLEM DESCRIPTION . 15 4.1 Historical Case Studies of Swirl Effects 16 4.1.1 FighterAircraft Experience . 16 4.1.2

9、 Cruise-Missile Experience 18 4.1.3 Lift-Fan Experience . 20 4.1.4 Thrust-Reverser Experience . 23 4.1.5 Auxiliary Power Unit (APU) Experience 24 4.1.6 Case Study Summary . 26 5. SOURCES AND IMPACT OF SWIRL . 26 5.1 Types and Sources of Swirl 26 5.1.1 Bulk Swirl 27 5.1.2 Tightly-Wound Vortex 30 5.1.

10、3 Paired Swirl . 33 5.1.4 Cross-Flow Swirl . 38 5.2 Effects of Bulk Swirl on Compression Systems 40 5.3 Summary . 42 6. SWIRL DESCRIPTORS 42 6.1 Circumferential Swirl Distortion Elements . 43 6.1.1 Sector Swirl (SS) . 44 6.1.2 Swirl Intensity (SI) . 44 6.1.3 Swirl Directivity (SD) . 44 6.1.4 Swirl P

11、airs (SP) . 45 6.2 Examples of One-Per-Rev Swirl Descriptor Values 45 6.2.1 Twin Swirl 45 6.2.2 Offset Paired Swirl - Unequal Amplitudes 46 6.2.3 Offset Paired Swirl - Unequal Extents 46 6.2.4 Bulk Swirl - Constant Swirl Angle Distribution. 47 7. STABILITY PRESSURE RATIO LOSS CORRELATION . 47 8. IMP

12、LEMENTATION OF SWIRL METHODOLOGY 50 8.1 Step 1 - Identification of the AIP and Associated Instrumentation 51 8.1.1 AIP Location 51 8.1.2 Measurement Positions on AIP . 51 8.1.3 AIP Sensors 52 8.2 Step 2 - Inlet Swirl Characterization 53 8.2.1 Example of Swirl Characterization Using Test Information

13、. 54 8.2.2 Example of Inlet Swirl Characterization Using CFD . 56 8.2.3 Example of CFD Application in the Selection of AIP Measurement Positions for Test 59 8.3 Step 3 - Compressor/Engine Sensitivity Determination 61 8.3.1 Test Methods 61 8.3.2 Computational Methods for Sensitivity Analysis . 64 8.4

14、 Step 4 - Assessment of Inlet-Engine System Compatibility 69 9. METHODS TO REDUCE SWIRL DISTORTION 70 10. SUMMARY AND CONCLUSIONS 71 _ SAE INTERNATIONAL AIR5686 Page 2 of 110APPENDIX A - CASE STUDIES . 72 APPENDIX B - DESCRIPTORS FOR MULTIPLE-PER-REV PATTERNS 80 APPENDIX C - METHODS OF REDUCING SWIR

15、L 87 _ SAE INTERNATIONAL AIR5686 Page 3 of 1101. SCOPE This Aerospace Information Report (AIR) addresses the subject of aircraft inlet-swirl distortion. A structured methodology for characterizing steady-state swirl distortion in terms of swirl descriptors and for correlating the swirl descriptors w

16、ith loss in stability pressure ratio is presented. The methodology is to be considered in conjunction with other SAE inlet distortion methodologies. In particular, the combined effects of swirl and total-pressure distortion on stability margin are considered. However, dynamic swirl, i.e., time-varia

17、nt swirl, is not considered. The implementation of the swirl assessment methodology is shown through both computational and experimental examples. Different types of swirl distortion encountered in various engine installations and operations are described, and case studies which highlight the impact

18、 of swirl on engine stability are provided. Supplemental material is included in the appendices. This AIR is issued to bring together information and ideas required to address the inlet-swirl problem for which common industry practice has yet to be established. This document should foster the tests

19、and analyses necessary to mature the ideas proposed by the committee to a recommended practice. These tests and analyses must include information that justifies three main features of the proposed swirl methodology: (1) swirl descriptors for correlating inlet swirl and stability pressure ratio loss,

20、 (2) computational techniques for analyzing compression systems (inlets, fans, compressors), and (3) test protocols (instrumentation and test techniques). The committee anticipates serving the industry by using such information to establish the consensus necessary for issuance of an SAE recommended

21、practice. 2. APPLICABLE DOCUMENTS The references for this document encompass SAE publications, papers, and reports that support the material in the body of the report, as well as papers and reports which were reviewed and may be sources for added insight for the interested reader. The following publ

22、ications form a part of this document to the extent specified herein. The latest issue of SAE publications shall apply. In the event of conflict between the text of this document and references cited herein, the text of this document takes precedence. Nothing in this document, however, supersedes ap

23、plicable laws and regulations unless a specific exemption has been obtained. 2.1 SAE Publications Available from SAE International, 400 Commonwealth Drive, Warrendale, PA 15096-0001, Tel: 877-606-7323 (inside USA and Canada) or 724-776-4970 (outside USA), www.sae.org ARP1420 Gas Turbine Engine Inlet

24、 Flow Distortion Guidelines. AIR1419 Inlet Total-Pressure Distortion Considerations for Gas-Turbine Engines. AIR5866 An Assessment of Planar Waves. AIR5867 An Assessment of the Inlet/Engine Temperature Distortion Problem. AIR5656 Statistical Stability Assessment. AIR5826 Distortion Synthesis/Estimat

25、ion Techniques. 2.2 Other Applicable Documents 1. Hercock, R.G., “Effects on Intake Flow Distortion on Engine Stability,” Paper 20, AGARD-CP-324. 2. Ludwig, G., “Tomahawk Engine/Inlet Compatibility Study for F107-WR-400/402 Engines,” Williams International Report CMEP 5003-2025, October 1989. 3. Sch

26、uab, U., and Bassett, R., “Flow Distortion and Performance Measurements on 12-Inch Fan-in-Wing Model for a Range of Forward Speeds and Angle of Attack Settings,” National Research Council of Canada, Quarterly Bulletin of the Division of Mechanical Engineering and the National Aeronautical Establishm

27、ent, June, 1972. _ SAE INTERNATIONAL AIR5686 Page 4 of 1104. Schuab, U., and Bassett, R., “Analysis of the Performance of a Highly-Loaded 12-Inch VTOL Z-Axis, Fan-in-Wing Model at Zero Forward Speed,” NRC, DME Aero, Report LR-439, National Research Council of Canada, Ottawa, Canada, September 1965.

28、5. Cockshutt, E., “VTOL Propulsion - 1970 Perspective,” Canadian Aeronautics and Space Journal, Volume 17, No. 4, April, 1971, pp. 117-130. 6. Reid, C., “The Response of Axial Flow Compressors to Intake Flow Distortion,” ASME Paper 69-GT-29. 7. Lieblein, S., Yuska, J., and Diedrich, J., “Wind Tunnel

29、 Tests of a Wing-Installed Model VTOL Lift Fan with Coaxial Drive Turbine,” NASA TMX-67854, 1971. 8. Schuab, U., and Bassett, R., “Analytic and Experimental Studies of Normal Inlets with Special Reference to Fan-in-Wing VTOL Powerplants,” Proceedings of the International Council of Aeronautical Scie

30、nces, Spartan, 1965, pp.519-553. 9. Schuab, U., Sharp, and Bassett, R., “An Investigation of the Three-Dimensional Flow Characteristics of a Non-Nulling Five-Tube Probe,” NRC, DME Aero, Report LR-393, National Research Council of Canada, Ottawa, Canada, February 1964. 10. Schuab, U., “Experimental S

31、tudies of VTOL Fan-in-Wing Inlets,” Aerodynamics of Powerplant Installation, AGARDograph 103, Pt. 2, AGARD, October, 1965, pp. 715-747. 11. Bassett, R., “Fan-in-Wing Crossflow Studies,” NRC, DME, Film Serial 22 National Research Council of Canada, Ottawa, Canada, 1970. 12. Beeler, E., and Przedpelsk

32、i, Z., “Lift Fan Design Considerations,” Annals of the New York Academy of Sciences, Vol. 154, Art. 2, November, 1968, pp. 619-640. 13. Motycka, D. L., “Ground Vortex Limit to Engine/Reverser Operation,” ASME Paper No. 75-GT-3, Transactions of the ASME, 1975. 14. Lotter, K. W. and Jrg, J., “The Effe

33、ct of Intake Flow Disturbances on APU Compressor Blade High Cycle Fatigue in the Airbus A300,” ICAS-82-4.6.2, Seattle, Aug., 1982, pp. 1072-1081. 15. Klien, H., “An Aerodynamic Screen for Jet Engines,” Inst. of Aero Sci. Preprint No. 676, January 1957. 16. de Siervi, F., Viguier, H. C., Greitzer, E.

34、 M., and Tan, C. S., “Mechanisms of Inlet Vortex Formation,” Journal of Fluid Mechanics, Vol. 124, 1982, pp. 173-207. 17. Shin, H. W., Greitzer, E. M., Cheng, W. K., Tan, C. S., and Shippee, C. L., ”Circulation Measurements and Vortical Structure in an Inlet Vortex Flow Field,“ Journal of Fluid Mech

35、anics, Vol. 162, 1986, pp. 463-487. 18. Murphy, J. P., MacManus, D. G., and Taylor, M. D., “A Quantitative Study of Inlet Ground Vortex,” ISABE-2007-1209. 19. Motycka, D. L., Walter, W. A., and Muller, G. L., “Analytical and Experimental Study of Inlet Ground Vortices,” AIAA Paper No. 73-1313, Nov.

36、1973. 20. Miller, D. S., Internal Flow Systems, British Hydromechanics Research Association, Fluid Engineering Series, Volume 5, 1978, pp. 43-44. 21. Schuab, U., “Crossflow-Induced Flow Distortion and its Influence on the Performance of a Vertical Axis Lifting Fan,” Carlton University Report ME 73-4

37、, September, 1973. _ SAE INTERNATIONAL AIR5686 Page 5 of 11022. Bouldin, B. and Sheoran, Y., “Inlet Flow Angularity Descriptors Proposed for Use with Gas Turbine Engines”, SAE 2002-01-2919. 23. Kihm, K. D., Chigier, N., and Sun, F., “Laser Doppler Velocimetry Investigation of Swirler Flowfields,” Jo

38、urnal of Propulsion, Vol. 6, No. 4, pp. 364-374, July-August 1990. 24. Tsinober, A., Kit, E., and Dracos, T., “Experimental Investigation of the Field of Velocity Gradients in Turbulent Flows,” Journal of Fluid Mechanics, Vol. 242, pp 169-192, 1992. 25. Goldstein, R. J., Fluid Mechanics Measurements

39、, Taylor and Francis, 1996. 26. Clancy, P. S., Samimy, M., and Erskine, W. R., “Planar Doppler Velocimetry: Three Component Velocimetry in Supersonic Jets,” AIAA Paper No. 98-0506. 27. Beutner, T. J., Williams, G. W., and Baust, H. D., “Characterization and Applications of Doppler Global Velocimetry

40、,” AIAA Paper No. 99-0266. 28. Beutner, T. J., Elliot, G., Mosedale, A., and Carter, C., “Doppler Global Velocimetry Applications in Large Scale Facilities,” AIAA Paper No. 98-2608. 29. Beresh, S. J., Kearney, S. P., Bourdon, C. J., and Grasser, T. W., “Development of a Doppler Global Velocimeter fo

41、r a Highly-Overexpanded Supersonic Jet,” AIAA Paper No. 2003-0915. 30. Mosedale, A. D., Elliott, G. S., Carter, C. D., Weaver, W. L., and Beutner, T. J., “On the Use of Planar Doppler Velocimetry,” AIAA Paper No. 98-2809. 31. Fleming, G. A., “Unified Instrumentation: Examining the Simultaneous Appli

42、cation of Advanced Measurement Techniques for Increased Wind Tunnel Testing Capability,” AIAA Paper No. 2002-3244. 32. Meyers, J. F., “Development of Doppler Global Velocimetry for Wind Tunnel Testing,” AIAA Paper No. 94-2582. 33. Clancy, P., Kim, J. H., and Samimy, M., “Planar Doppler Velocimetry i

43、n High Speed Flows,” AIAA Paper No. 96-1990. 34. McKenzie, R. L., “Planar Doppler Velocimetry Performance in Low-Speed Flows,” AIAA Paper No. 97-0498. 35. Nobes, D. S., Ford, H. D., and Tatam, R. P., “Three Dimensional Planar Doppler Velocimetry Using Imaging Fibre Bundles,” AIAA Paper No. 2002-0692

44、. 36. Hileman, B. T., Samimy, M., and Lempert, W., “Progress Towards Real-Time Planar Doppler Velocimetry,” AIAA Paper No. 2003-0916. 37. Raffel, M., Willert, C., and Kompenhans, J., Particle Image Velocimetry, A Practical Guide, Springer, Berlin, 1998. 38. Westerweel, J., “Fundamentals of Digital P

45、article Image Velocimetry,” Meas. Sci. Technol. 8 137992. 39. Stanislas, M., Kompenhans, J., and Westerweel, J., Particle Image Velocimetry: Progress Towards Industrial Applications, Springer, 2000. 40. Lotter, K., “APU Garrett TSCP 700-5 Low Pressure Compressor Fatigue Failures, Review of Garrett a

46、nd MBB Investigations and Proposal for Modification to the Engine and Air Intake,” MBB Report No. MBB/FE124/A300/R/3, April 10, 1981. _ SAE INTERNATIONAL AIR5686 Page 6 of 11041. Dean, R. C., Jr., “Aerodynamic Measurements,” Gas Turbine Laboratory, Massachusetts Institute of Technology, 1953. 42. Ma

47、rquart, E. J., Stepanek, S. A., Byers, M. T., and Donaldson, J. C., “Development and Calibration of Miniature Mach/Flow-Angularity Probes,” AIAA Paper No. 84-0630. 43. Everett, K. N., Gerner, K. A., and Durston, D. A., “Theory and Calibration of Non-Nulling Seven Hole Probes for Use in Complex Flow Measurements,“ AIAA Paper No. 82-0232. 44. Naughton, J. W., Cattafesta III, J. N., and Seettles, G. S., “A Miniature, Fast-Response 5 Hole Probe for Supersonic Flow Field Measurements,” AIAA Paper No. 92-0266. 45. Stevens, C. H., Spong, E. D., and Hammoc