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 ther
2、efrom, 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
3、publication 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: +1 724-776-49
4、70 (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/AIR5867 AEROSPACE INFORMATION REPORT AIR5867 Issued 2017-11 Assessment of the Inlet/Engine Tot
5、al Temperature Distortion Problem RATIONALE Due to the needs of the industry, this document has been upgraded to an AIR (Aerospace Information Report) from an ARD (Aerospace Research Document) status and was formerly catalogued as ARD50015. Most of the report is unchanged since the material is as us
6、eful now as it was when first published in 1991. Considerable total temperature distortion research has been accomplished since the publication of the original document, but these data are not available for public release. Thus, complete revision of this document is not presently warranted. A few pa
7、ragraphs have been updated to reflect knowledge gained on recent aircraft programs. Other changes reflect consistency with more recently adopted definitions, and minor editorial and typographical corrections. Attempts were also made to update quality and timeliness of the original figures and tables
8、. However, because it was not possible to retrieve some of the original material, the existing relevant figures and tables were kept, resulting in a varying appearance throughout this revision. As applications for turbine engines have become more sophisticated and the operating conditions more sever
9、e, the SAE S-16 Turbine Engine Inlet Flow Distortion Committee has recognized the need for guidelines and procedures that would address inlet flow total-temperature distortion in a manner similar to that accomplished for inlet flow total-pressure distortion, which resulted in the SAE documents ARP14
10、20C and AIR1419C. This document brings together information and ideas which are required to address total temperature distortion problems. This document has been cleared for public release. The SAE S-16 Committee welcomes input from both industry and government organizations relative to the contents
11、 of this report and information on current and future programs in this important technical area as the committee attempts to define standard guidelines. SAE INTERNATIONAL AIR5867 Page 2 of 57 TABLE OF CONTENTS 1. SCOPE 4 1.1 Purpose . 4 1.2 Field of Application 4 2. REFERENCES 4 2.1 Applicable Docum
12、ents 4 2.1.1 SAE Publications . 4 2.1.2 ASME Publications 5 2.1.3 AIAA Publications 5 2.1.4 U.S. Government Publications 5 2.2 Applicable References 7 2.3 Definitions . 8 3. CONCLUSIONS 9 4. INLET TOTAL TEMPERATURE DISTORTION PROBLEM ASSESSMENT . 10 5. STATUS OF PAST AND PRESENT EFFORTS . 12 5.1 Spa
13、tial Total Temperature Distortion 12 5.2 Total Temperature Ramps 13 5.3 Laboratory Test Data 13 5.4 Flight Test Data . 15 5.5 Combined Total Pressure and Total Temperature Distortion . 17 5.6 Computer Simulation of Engine Response . 17 6. SUGGESTED APPROACH TO A TOTAL TEMPERATURE DISTORTION METHODOL
14、OGY . 18 6.1 Spatial Total Temperature Distortion 19 6.1.1 Definition of Face-Average Total Temperature . 19 6.1.2 Definition of Stability Pressure Ratio Loss and Stability Margin Loss 19 6.1.3 Spatial Distortion Descriptor Elements . 20 6.1.4 Time-Variant Total Temperature Distortion. 20 6.1.5 Stab
15、ility Total Pressure Ratio Loss Due to Spatial Total Temperature Distortion 21 6.2 Total Temperature Ramp with Spatial Total Temperature Distortion . 21 6.3 Stability and Performance Assessments 22 6.3.1 Stability Assessment of Total Temperature Distortion 22 6.3.2 Performance Assessment . 23 6.4 Te
16、sting. 23 6.4.1 Inlet and Aircraft Component Tests 24 6.4.2 Inlet Model Tests/Scaling Requirements 24 6.4.3 Engine and Engine Component Tests 25 6.4.4 Propulsion System Tests 25 6.4.5 Stability/Performance Tests 25 6.5 Interface Instrumentation 26 6.5.1 Inlet/Engine Aerodynamic Interface Plane (AlP)
17、 . 26 6.5.2 Rake/Probe Array 26 6.5.3 Instrumentation Selection 27 6.5.4 Corrections for Total Temperature Probe Response 27 APPENDIX A PROPOSED SPATIAL TOTAL TEMPERATURE DISTORTION DESCRIPTORS 29 APPENDIX B TOTAL TEMPERATURE RAMP/DISTORTION METHODOLOGY 37 APPENDIX C SIMILARITY AND SCALING REQUIREME
18、NTS. 44 Figure 1 Hot gas recirculation mechanisms 11 Figure 2 Hydrogen-fueled total temperature distortion generator . 13 Figure 3 Total temperature ramp data expressed as total temperature rise versus total temperature ramp rate 14 Figure 4 Typical total temperature measurements with hot gas re-ing
19、estion . 16 Figure 5 Reduction in spatial total temperature distortion tolerance due to a total temperature ramp . 16 Figure 6 Stability margin degradation . 19 Figure 7 Compressor map characteristics with total temperature distortion . 21 SAE INTERNATIONAL AIR5867 Page 3 of 57 Figure 8 Probe orient
20、ation - view looking forward . 27 Table 1 Importance of temperature ramps . 13 Table 2 A typical stability margin assessment including effect of inlet total temperature distortion 24 SAE INTERNATIONAL AIR5867 Page 4 of 57 1. SCOPE This report revises ARD50015 document to the AIR format. This report,
21、 as was the original, is intended to complement ARP1420C and AIR1419C documents issued by the SAE S-16 Committee on spatial total-pressure distortion. These previous documents addressed only total-pressure distortion and excluded total temperature distortion. The subject of inlet total temperature d
22、istortion is addressed in this report with some background and identification of the problem area. The status of past efforts is reviewed, and an attempt is made to define where we are today. Deficiencies, voids, and limitations in knowledge and test techniques for total temperature distortion are i
23、dentified. 1.1 Purpose Suggested approaches to fill these voids and a proposed total temperature distortion methodology are presented. Successful techniques, employed to date, are reviewed and recommendations for future research work are indicated. 1.2 Field of Application Intake/engine aerodynamic
24、compatibility continues to be a major interface operability consideration affecting the design and development of aircraft propulsion systems. Engine performance degradation, including power loss due to engine blowout and/or compressor instability, has been attributed to engine inlet total temperatu
25、re distortion (time-variant spatial total temperature distortion and/or total temperature ramp at the Aerodynamic Interface Plane (AlP). Reported inlet distortion sources include ingestion of gases from armament firings, ingestion of steam from catapult launch systems, ingestion of engine exhaust ga
26、ses from thrust reverser systems, and ingestion of engine exhaust gases during helicopter and V/STOL aircraft operations. System operability problems generally have been solved by avoiding or minimizing AlP total temperature variations by system configuration changes and/or operating procedure chang
27、es (reduced system operability) to remove the source of high-temperature gases from the capture region of the aircraft inlet system, or by engine accommodations to withstand the distortion. Total temperature distortion avoidance techniques are not practical for all systems. In order to properly acco
28、unt for and accommodate total temperature distortion, guidelines for understanding turbine engine response to and accounting for total temperature distortion are required. A significant database that can be used as a start for the future formulation of recommended industry guidelines is reported. An
29、 inlet total temperature distortion problem assessment and status review, based on available data, are summarized in this report with suggestions for the development of practical guidelines. 2. REFERENCES 2.1 Applicable Documents The following publications form a part of this document to the extent
30、specified herein. The latest issue of SAE publications shall apply. The applicable issue of other publications shall be the issue in effect on the date of the purchase order. In the event of conflict between the text of this document and references cited herein, the text of this document takes prece
31、dence. 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 Drive, Warrendale, PA 15096-0001, Tel: 877-606-7323 (inside USA and Canada) or +1 724-776-4970
32、 (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 ARP246 Orientation of Engine Axis, Coordinate and Numbering Systems for Aircraft Gas Turbine Engines SAE INT
33、ERNATIONAL AIR5867 Page 5 of 57 2.1.2 ASME Publications Available from ASME, P.O. Box 2900, 22 Law Drive, Fairfield, NJ 07007-2900, Tel: 800-843-2763 (U.S./Canada), 001-800-843-2763 (Mexico), 973-882-1170 (outside North America), www.asme.org. 2.1.2.1 ASME (81-WA/FE-18) - Baghdadi, S. and Lueke, J.
34、E., Compressor Stability Analysis, Detroit Diesel Allison/USAF APL, 1982. 2.1.2.2 ASME Paper No. 79-GT-10 - Lewis, W. J. and Hurd, R., Augmented Vectored Thrust Engines and the Problem of Avoiding Hot Gas Recirculation, March 1979. 2.1.2.3 ASME 82-GT-189 - Davis, M. W., Jr., A Stage-By-Stage Dual-Sp
35、ool Compression System Modeling Technique, 1982. 2.1.3 AIAA Publications Available from American Institute of Aeronautics and Astronautics, 1801 Alexander Bell Drive, Suite 500, Reston, VA 20191-4344, Tel: 703-264-7500, www.aiaa.org. 2.1.3.1 AIAA-80-1246 - Walter, W. and Delany, J., Stability Analys
36、is of YF401 Engine in a XFV-12 Aircraft, Pratt and Whitney/Rockwell International, July 1980. 2.1.3.2 AIAA 73-1316 - Braithwaite, W. M., Graber, E. J., and Mehalic, C. M., The Effects of Inlet Temperature and Pressure Distortion on Turbojet Performance, NASA., November 1973 (NASA TMX 71431). 2.1.3.3
37、 AIAA 74-236 - Graber, E. J. and Braithwaite, W. M., Summary of Recent Investigations of Inlet Flow Distortion Effects on Engine Stability, NASA, February 1974. 2.1.3.4 AIAA 70-625 - Rudey, R. A. and Antl, R. J., The Effects of Inlet Temperature Distortion on the Performance of a Turbofan Engine Com
38、pressor System, NASA, June 1970. 2.1.3.5 AIAA 79-1310 - Walter, W. A. and Shaw, M., Predicted F100 Engine Response to Circumferential Pressure and Temperature Distortion, Pratt and Whitney, June 1979. 2.1.3.6 AIAA 82-1266 - Das, D. K., Trippi, A., and Peacock, R. E., Unsteady Response of an Axial Fl
39、ow Compressor to Planar Temperature Transients, Cranfield Institute of Technology/U.S. Naval Post Graduate School, June 1982. 2.1.3.7 AIAA Journal of Aircraft - Amin, N. F. and Richards, C. J., Thrust Reverser Exhaust Plume Reingestion Model Tests, Vol. 21, No. 6, June 1984. 2.1.3.8 AIAA 79-1309 - B
40、raithwaite, W. M. and Soeder, R. H., Combined Pressure and Temperature Distortion Effects on Internal Flow of a Turbofan Engine, June 1979. 2.1.4 U.S. Government Publications Copies of these documents are available online at http:/quicksearch.dla.mil. 2.1.4.1 AEDC-TR-79-39 - Chamblee, C. E., Applica
41、tion of the Multistage Axial Flow Compressor Time-Dependent Mathematical Modeling Technique to the TF41-A-1 Modified (Block 76) Compressor, September 1979. 2.1.4.2 AFAPL-TR-77-58 - Ludwig, G. R., Wind Tunnel Model Study of the Hot Exhaust Plume from the Compressor Research Facility at Wright Patters
42、on Air Force Base, Ohio, October 1977 (also presented as ASME Paper No. 79-GT-186). 2.1.4.3 NACA RM E55E25 - Childs, H. J., Kichendorfer, F. D., Lubick, R. J., Friedman, R., Stall arid Flameout Resulting from Firing of Armament, NACA, August 1955. 2.1.4.4 NACA RM E57C22 - Wallner, L. E., Useller, J.
43、 W., and Saari, M. J., A Study of Temperature Transients at the Inlet of a Turbojet Engine, NACA, June 1957. SAE INTERNATIONAL AIR5867 Page 6 of 57 2.1.4.5 NACA TN 3766 - Glawe, G. E., Simmons, F. S., and Stickney, T. M., Radiation and Recovery Corrections and Time Constants of Several Chromel-Alume
44、l Thermocouple Probes in High-Temperature, High-Velocity Gas Streams, NACA, October 1956. 2.1.4.6 MIL-E-5007D, Military Specification, Engines, Aircraft, Turbojet and Turbofan, General Specification for, Revised October 1973 (Paragraph 3.1.2.10.5, 3.1.2.10.6, 4.6.4.9). 2.1.4.7 NASA CR-134709 - Hambl
45、y, D., Wind Tunnel Test of Model Target Thrust Reversers for the Pratt and Whitney Aircraft JT8D-100 Series Engine Installed in a 727-200 Airplane, NASA/Boeing, September 1974. 2.1.4.8 NASA TM X-2990 - Mehalic, C. M. and Lottig, R. A., Steady-State Inlet Temperature Distortion Effects on the Stall L
46、imits of a J85-GE-13 Turbojet Engine, NASA, February 1974. 2.1.4.9 NASA TM 79136 - Braithwaite, W. M. and Soeder, R. H., Combined Pressure and Temperature Distortion Effects on Internal Flow of a Turbofan Engine, NASA, June 1979 (AIAA 79-1306). 2.1.4.10 NASA TM 82699 - Abdelwahab, M., Effects of Fan
47、 Inlet Temperature Disturbances on the Stability of a Turbofan Engine, NASA, December 1981. 2.1.4.11 NASA TP 1031 - Abdelwahab, M., Effects of Temperature Transients at Fan Inlet of a Turbofan Engine, NASA, September 1977. 2.1.4.12 NASA TM X-2921 - Braithwaite, W. M., Experimental Evaluation of a TF
48、30-P-3 Turbofan Engine in an Altitude Facility: Effect of Steady-State Temperature Distortion, NASA, 1974. 2.1.4.13 NASA TMX 52788 - Rudey, R. A. and Antl, R. J., The Effect of Inlet Temperature Distortion on the Performance of a Turbofan Engine Compressor System, June 1970. 2.1.4.14 NASA TM 79237 -
49、 Soeder, R. H. and Bobula, G. A., Effect of Steady-State Temperature Distortion and Combined Distortion on Inlet Flow to a Turbofan Engine, August 1979. 2.1.4.15 NASA CR-159754 - Walter, W. A. and Shaw, M., Distortion Analysis for F100(3) Engine, January 1980. 2.1.4.16 NASA CR-135124 - Mazzawy, R. S. and Banks, G. A., Circumferential Distortion Modeling of the TF30-P-3 Compression System (PWA-5448), January 1977. 2.1.4.17 NASA TP 1099
