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 reaffirmed, revised, or cancelled. SAE invites your written comments and suggestions. Copyright 2008 SAE International All rights reserved. No part of this publication m
3、ay 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: 724-776-4970 (outside USA)
4、 Fax: 724-776-0790 Email: CustomerServicesae.org SAE WEB ADDRESS: http:/www.sae.org AIR5866 AEROSPACE INFORMATION REPORT Issued 2008-02 An Assessment of Planar Waves RATIONALE Due to the needs of the industry, this document has been upgraded to an AIR (Aerospace Information Report) from an ARD (Aero
5、space Research Document) status and was formerly catalogued as ARD500026. Most of the report is unchanged since the material is as useful now as it was when first published in 1995. A few paragraphs have been updated to reflect knowledge gained on recent aircraft programs. Other changes reflect cons
6、istency with more recently adopted definitions, and minor editorial and typographical corrections. However in the course of this upgrade, it became apparent that the original figures were no longer available nor were the means to recreate them. In some cases, figures have been redrawn. For the remai
7、ning figures (and tables), the best available copy was scanned. The committee apologizes for any lack of clarity produced by this procedure. FOREWORD As applications for turbine engines have become more sophisticated and the operating conditions more severe, inlet planar time-variant full-face total
8、-pressure variations, usually accompanied by spatial total pressure distortion, can become a significant destabilizing factor. The SAE S-16 Turbine Engine Inlet Flow Distortion Committee has recognized the need for guidelines and procedures that would address inlet planar waves and the desirability
9、of documentation similar to SAE documents ARP1420 and AIR1419 that were written for inlet spatial total-pressure distortion. This Aerospace Information Report (AIR) brings together information and ideas that are required to address the planar wave problem. A common industry practice has yet to be es
10、tablished. SAE AIR5866 - 2 - TABLE OF CONTENTS 1. SCOPE 4 2. REFERENCES 4 2.1 Applicable Documents 4 2.2 Other Applicable References 4 2.3 Related Publications . 5 2.4 List of Nomenclature and Symbols . 8 3. SUMMARY 9 4. INTRODUCTION. 9 5. PROBLEM ASSESSMENT. 10 5.1 Case History Studies 11 5.1.1 Sys
11、tem “A” 11 5.1.2 System “B” 14 5.2 Combined Spatial Pressure Distortion and Planar Waves . 19 6. APPROACH TO PLANAR WAVE METHODOLOGY . 19 6.1 Categorization of Inlet Planar Waves . 22 6.2 Determination of Engine Response to Planar Waves 24 6.2.1 Engine or Compression System Tests . 24 6.2.2 Computer
12、 Simulations. 24 6.2.3 Analytical Solutions. 25 6.3 Planar Wave Methodology Approaches . 30 6.3.1 Computer Simulation Prediction . 30 6.3.2 Sensitivity Analysis 30 6.4 Combined Spatial Total-Pressure Distortion and Planar Waves 33 6.4.1 Spatial Distortion. 33 6.4.2 Stability Margin 36 6.4.3 Stabilit
13、y Margin Accounting. 37 7. TESTING REQUIREMENTS 44 7.1 Inlet Testing. 45 7.1.1 Inlet Development Tests . 45 7.1.2 Engine and Compression System Testing 48 7.1.3 Instrumentation . 49 7.1.4 Data Processing and Screening . 49 7.2 Compression System Component Testing . 49 7.2.1 Planar Wave Generators 51
14、 7.2.2 Compression System Modeling 53 7.3 Verification Testing 53 8. CONCLUSIONS AND RECOMMENDATIONS 53 8.1 Conclusions. 53 8.2 Recommendations 53 APPENDIX A DOCUMENT REVIEW MATERIAL. 55 APPENDIX B ANALYTICAL MODEL FOR ESTIMATING COMPRESSOR SENSITIVITY TO A SINUSOIDAL PLANAR WAVE 56 APPENDIX C ELEME
15、NTS OF METHODOLOGY VALIDATION. 63 FIGURE 1 LOCAL FLOW SEPARATION ON INLET RAMP DURING OFF DESIGN OPERATION AT LOW AIRFLOW. 12 FIGURE 2 WIND TUNNEL/FLIGHT TEST COMPARISON OF PLANAR WAVES, MACH 0.85. 12 FIGURE 3 PLANAR WAVE AMPLITUDE 13 FIGURE 4 SPATIAL DISTORTION CHARACTERISTICS. 14 FIGURE 5 ECS PREC
16、OOLER ASSEMBLY. 15 FIGURE 6 RESONANCE CHARACTERISTICS IN ECS SCOOP INLET 15 FIGURE 7 EFFECT OF GEAR WAKE INGESTION ON PLANAR WAVES 16 FIGURE 8 COMPRESSOR INLET PLANAR WAVE EXPERIENCE AS A FUNCTION OF FLIGHT PROFILE FOR IDLE AND BELOW IDLE AIRFLOWS 16 FIGURE 9 COMPRESSOR INLET PRESSURE SIGNATURES . 1
17、7 SAE AIR5866 - 3 - FIGURE 10 COMPRESSOR INLET PLANAR WAVE EXPERIENCE AS A FUNCTION OF ENGINE SPEED AND INLET MASS FLOW RATIO . 18 FIGURE 11 WAVEFORMS OF COMPRESSOR-FACE AVERAGE TOTAL-PRESSURE AND DISTORTION FACTORS . 20 FIGURE 12 POWER SPECTRAL DENSITY PLOTS OF WAVEFORMS 21 FIGURE 13 TIME-VARIANT D
18、ISTORTION, INLET PLUS ENGINE TESTS . 22 FIGURE 14 CATEGORIZATION OF INLET DATA 23 FIGURE 15 ENGINE AND COMPRESSION SYSTEM COMPUTER SIMULATION CONSIDERATIONS . 25 FIGURE 16 PLANAR-WAVE SENSITIVITY, SIMPLE ILLUSTRATIVE ANALYSIS 27 FIGURE 17 PLANAR-WAVE SENSITIVITY, AMPLITUDE TO STALL 27 FIGURE 18 INLE
19、T PLANAR PRESSURE WAVE - PREDICTED AMPLITUDE TO CAUSE STALL, SINE WAVES 28 FIGURE 19 PERIODIC PLANAR WAVES, INLET TOTAL-PRESSURE DISTORTION (EXAMPLE) . 29 FIGURE 20 PERIODIC PLANAR WAVES, FAN-STABILITY-MARGIN VARIATION (EXAMPLE) 29 FIGURE 21 PERIODIC PLANAR WAVES, HIGH-PRESSURE-COMPRESSOR STABILITY-
20、MARGIN VARIATION (EXAMPLE) 30 FIGURE 22 DYNAMIC DISTORTION SENSITIVITY VERSUS FREQUENCY - N/ = 100% . 31 FIGURE 23 FAN-COMPONENT PLANAR-WAVE SENSITIVITY 31 FIGURE 24 CATEGORIZATION OF ANALYTICAL TECHNIQUES 34 FIGURE 25 RING CIRCUMFERENTIAL DISTORTION (ONE-PER-REV-PATTERN) 35 FIGURE 26 RADIAL DISTORT
21、ION PATTERN 35 FIGURE 27 STABILITY MARGIN DEFINITION . 36 FIGURE 28 COMBINED PLANAR WAVE AND SPATIAL DISTORTION 39 FIGURE 29 COMPRESSOR OPERATING-POINT-EXCURSION PLANAR-WAVE SINUSOID. 39 FIGURE 30 AIR-INTAKE TIME-VARIANT SPATIAL DISTORTION WITH EMBEDDED PLANAR WAVE . 41 FIGURE 31 COMPOSITE DISTORTIO
22、N DESCRIPTOR-OVERALL FACE 42 FIGURE 32 COMPOSITE DESCRIPTOR, DPCOM. 43 FIGURE 33 PLANAR WAVE CONSIDERATIONS FOR INLET DEVELOPMENT TESTS . 46 FIGURE 34 TYPICAL LIMITED PROBE ARRANGEMENTS. 47 FIGURE 35 PLANAR WAVE INLET DATA PROCESS . 50 FIGURE 36 DYNAMIC DISTORTION SENSITIVITY VERSUS FREQUENCY - N/ =
23、 100% . 51 FIGURE 37 ROTATING PERFORATED DISK (GE AND NASA) 51 FIGURE 38 ROTATING SPOKES (AEDC AND U.K.) . 52 FIGURE 39 AIRJET DISTORTION GENERATOR (AEDC AND NASA) . 52 TABLE 1 LIST OF NOMENCLATURE AND SYMBOLS 8 SAE AIR5866 - 4 - 1. SCOPE “An Assessment of Planar Waves” provides background on some o
24、f the history of planar waves, which are time-dependent variations of inlet recovery, as well as establishing a hierarchy for categorizing various types of planar waves. It further identifies approaches for establishing compression-component and engine sensitivities to planar waves, and methods for
25、accounting for the destabilizing effects of planar waves. This document contains an extensive list and categorization (see Appendix A) of references to aid both the newcomer and the practitioner on this subject. The committee acknowledges that this document addresses only the impact of planar waves
26、on compression-component stability and does not address the impact of planar waves on augmenter rumble, engine structural issues, and/or pilot discomfort. 2. REFERENCES The references for this document encompass SAE publications, papers and reports to support the material in the body of the report,
27、and papers and reports that were reviewed and may be sources for added insight for the interested reader. 2.1 Applicable Documents The following publications form a part of this document to the extent specified herein. The latest issue of SAE publications shall apply. In the event of conflict betwee
28、n the text of this document and references cited herein, the text of this document takes precedence. Nothing in this document, however, supersedes applicable laws and regulations unless a specific exemption has been obtained. 2.1.1 SAE Publications Available from SAE International, 400 Commonwealth
29、Drive, Warrendale, PA 15096-0001, Tel: 877-606-7323 (inside USA and Canada) or 724-776-4970 (outside USA), www.sae.org. 2.1.1.1 ARP1420, “Gas Turbine Engine Inlet Flow Distortion Guidelines.” 2.1.1.2 AIR1419, “Inlet Total-Pressure Distortion Considerations for Gas-Turbine Engines.” 2.1.1.3 ARD500015
30、, “A Current Assessment of the Inlet/Engine Temperature Distortion Problem“ and to be republished as AIR5867, “An Assessment of the Inlet/Engine Temperature Distortion Problem.” 2.2 Other Applicable References 2.2.1 MacMiller, C. J. and Haagenson, W. R., “Unsteady Inlet Distortion Characteristics wi
31、th the B-1B,” NA-86-1490A, presented at the 68th(A) Specialists Meeting of the AGARD Propulsion and Energetics Panel on Engine Response to Distorted Inflow Conditions, Munich, Germany, September 8-9, 1986. 2.2.2 Burstadt, P. L. and L. M. Wenzel, AIAA 76-703, “A Method to Account for Variations of Av
32、erage Compressor Inlet Pressure During Instantaneous Distortion Analysis,” July 1976. 2.2.3 Willoh, R. H. and Seldner, K., NASA TM X-1880, “Multistage Compressor Simulation Applied to the Prediction of Axial Flow Instabilities,” NASA, September 1969. 2.2.4 Davis, M. W., ASME 82-GT-189, “A Stage-by-S
33、tage Dual Spool Compression System Modeling Technique.” 2.2.5 Reynolds, G. G. and W. G. Steenken, AFAPL-TR-76-76, “Dynamic Digital Blade Row Compression Component Stability Model - Model Validation and Analysis of Planar Pulse Generator and Two-Stage Fan Test Data,” AFAPL, August 1976. 2.2.6 Tesch,
34、W. A., R. E. Moszee and W. G. Steenken, NASA CR-135162, “Linearized Blade Row Compression Component Model - Stability and Frequency Response Analysis of a J85-13 Compressor”, NASA, September 1976. SAE AIR5866 - 5 - 2.2.7 Steenken, W. G., AIAA 88-3264, “Planar Wave Stability Margin Loss Methodology,”
35、 AIAA/ASME/SAE/ASEE 24th Joint Propulsion Conference, Boston, Massachusetts, July 11-13, 1988. 2.2.8 Reynolds, G. G., W. F. Vier and T. P. Collins, AFAPL-TF-73-43, “An Experimental Evaluation of Unsteady Flow Effects on an Axial Compressor-P3 Generator Program,” USAF AFAPL, July 1973. 2.2.9 Steenken
36、, W. G., William, J. G., and Walsh, K. R., NASA/TM-1999-206587, “Inlet Flow Characteristics During Rapid Maneuvers for an F/A-18A Airplane,” October 1999. 2.2.10 Seybert, A. F. and C. U. R. Cheng, “Application of the Boundary Element Method to Acoustic Cavity Response and Muffler Analysis,” Journal
37、of Vibration, Acoustics, Stress, and Reliability in Design, Vol. 109, pp. 15-21, January 1987. 2.2.11 Utsuno, H. and T. W. Wu and A. F. Seybert, “Prediction of Sound Fields in Cavities with Sound Absorbing Materials,” AIAA Journal, Vol. 28, No. 11, pp. 1870-1876, 1990. 2.2.12 Prakash, G. K. Ravi, “A
38、 Computational Method for the Analysis of Acoustic Radiation from Turbofan Inlets,” PhD dissertation under the direction of Dr. John Carruthers, University of Tennessee Space Institute, May 1992. 2.2.13 Peacock, R. E. and D. K. Das, “The Excitation of Compressor/Duct Systems”, Symposium on “Fluid/St
39、ructure Interactions in Turbomachinery,” Winter Annual Meeting of ASME, Washington, D.C., November 1-520, 1981. 2.3 Related Publications The following publications are provided for information purposes only and are not a required part of this SAE Aerospace Technical Report. 2.3.1 Chung, K., Hosny, W
40、. M. and W. G. Steenken, NASA CR-165141, “Aerodynamic Stability Analysis of NASA J85-13 Planar Pressure Pulse Generator Installation,” NASA, November 1980. 2.3.2 Das, D. K. and A. Trippi, AIAA-85-1135, “Effects of Inlet Pressure Fluctuations on Axial Flow Compressors: Some Experimental and Theoretic
41、al Results,” AIAA/SAE/ASME 21st Joint Propulsion Conference, July 1985. 2.3.3 Kimzey, W. F., AEDC-TR-77-80, “An Analysis of the Influence of Some External Disturbances on the Aerodynamic Stability of Turbine Engine Axial Flow Fans and Compressors,” August 1977. 2.3.4 Kuhlberg, J. F., D. E. Sheppard,
42、 E. O. King and J. R. Baker, AIAA 69-486, “Dynamic Simulation of Turbine Engine Compressors,” June 1969. 2.3.5 Lazalier, G. R. and J. T. Tate, AFAPL-TR-69-103, “Development of a Prototype Discrete Frequency, Total Pressure Fluctuation Generator for Jet Engine-Inlet Compatibility Investigations,” ARO
43、 Inc., AEDC, June 1970. 2.3.6 Mason, J. R., J. W. Park and R. F. Jaekel, NASA CR-165261, “Extended Frequency Turbofan Model,” December 1980. 2.3.7 McAulay, J. E., NASA TM X-2081, “Effect of Dynamic Pressure Variations in Engine-Inlet Pressure on the Compressor System of a Twin-Spool Turbofan Engine,
44、” September 1970. 2.3.8 Milner, E. J., L. M. Wenzel and F. J. Paulovich, NASA TM X-3012, “Frequency Response of an Axial-Flow Compressor Exposed to Inlet Pressure Perturbations,” April 1974. 2.3.9 November, G., ASME Technical Paper 67-VIBR-57, “Causes of Variable Acoustic Resonance During Tests of J
45、et Engine Compressors,” 1967. SAE AIR5866 - 6 - 2.3.10 Peacock, R. E. and D. K. Das, “An Experimental Study of Pulsating Flow in a Three-Stage Axial Flow Compressor” Symposium on “Non-Steady Fluid Dynamics,” Winter Annual Meeting of ASME, San Francisco, CA, December 1978. 2.3.11 Peacock, R. E., D. C
46、. Eralp and D. K. Das, AIAA 80-1080, “Compressor Response to Pulsed Transients,” AIAA/SAE/ASME 16th Joint Propulsion Conference, July 30-July 2, 1980, Hartford, CN. 2.3.12 Peacock, R. E. and D. K. Das, AIAA-81-1590, “Performance Analysis of a Family of Planar Pulse Generators,” AIAA/SAE/ASME 17th Jo
47、int Propulsion Conference, Colorado Springs, CO, July 27-29, 1981. 2.3.13 Steenken, W. G., AGARD Conference Proceedings No. 324, “Modeling Compression Component Stability Characteristics - Effects of Inlet Distortion and Fan Bypass Duct Disturbances,” AGARD Conference Proceedings No. 324, “Engine Ha
48、ndling,” Paper No. 24, October 1982. 2.3.14 Sussman, M. B. and G. W. Lampard, AFAFL-TR-69-103, “A Possible Mechanism for Inlet/Engine Interactions due to Inlet Flow Fluctuations,” 1969, Boeing Company, Commercial Airplane Division. 2.3.15 Wenzel, L. M., NASA TM X-1928, “Experimental Investigation of
49、 the Effects of Pulse Pressure Distortions Imposed on the Inlet of a Turbofan Engine,” November 1969. 2.3.16 Burcham, F. W. and Bellman, D. R., “A Flight Investigation of Steady-State and Dynamic Pressure Phenomena in the Air Inlets of Supersonic Aircraft,” Presented at the 38th Meeting of AGARD Propulsion and Energetics Panel, Sandeford, Norway, September 13-17, 1971. 2.3.17 McIlveen, M.W., AIAA 79-1185, “Further Test Results with the Ai
