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 2009 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: +1 724-776-4970 (outside U
4、SA) 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:/www.sae.org/technical/standards/AIR4827A AEROSPACE INFORMATION REPORT AIR4827 REV. A Issued 1993-05 Reaffirmed 1999-05 Revise
5、d 2009-06 Superseding AIR4827 Modeling Techniques for Jet Engine Test Cell Aerodynamics RATIONALE Revision based on the 5 Year Review. FOREWORD One of the strongest motives for developing the scale modeling techniques to allow investigation of engine test cell aerodynamics as described in this work
6、was the generally poor understanding of the aerodynamics associated with the ground level testing of turbofan and turbojet engines within enclosed testing facilities. In those instances where the understanding was not so poor, there sometimes remained a lack of appreciation for the fundamental impor
7、tance of the aerodynamics of the engine testing environment. It is known that such a poor understanding or a lack of appreciation for the importance of the aerodynamics of the testing environment can and does lead to disastrous consequences. With proper attention to scale modeling techniques, the ae
8、rodynamics of a jet engine test facility can readily be investigated and documented. Modifications to a test cell based on scale model test results can lead to a stable and reliable full-scale operating environment for the testing of aircraft engines indoors. A much improved understanding and height
9、ened awareness of the fundamental importance of the aerodynamics of the engine testing environment have resulted in significantly improved engine test facilities now in use world-wide. ABSTRACT Research studies focusing on jet engine test cell aerodynamics, acoustics, and cell flow characteristics a
10、s affecting engine performance can be conducted with scale models for a variety of test cells. Such studies require the simulation of a number of jet engines in rather accurate detail, both as to geometry and as to flow characteristics. It has been demonstrated that simulators of low-bypass afterbur
11、ning turbojets, high-bypass turbofans, turboshaft engines (without propellers), and unducted fan engines can be designed, fabricated, and successfully operated using either high-pressure air ejector systems or turbine driven systems for the motive power. Specific components of a test cell such as in
12、lets or exhaust sections alone may be tested independently by employing a vacuum source and bellmouth to simulate engine inlet flow or compressed air and scaled nozzle to simulate engine exhaust flow. The peculiar problems associated with scale model testing and engine simulators and the methods whi
13、ch can be used to attack these problems are described. Copyright SAE International Provided by IHS under license with SAENot for ResaleNo reproduction or networking permitted without license from IHS-,-,-SAE AIR4827A Page 2 of 28 TABLE OF CONTENTS 1. SCOPE 4 1.1 Purpose . 4 1.1.1 Provision of Guidel
14、ines . 4 1.1.2 Discussion of Considerations . 4 2. REFERENCES 4 2.1 Applicable Documents 4 2.2 Symbols and Abbreviations 6 2.2.1 Parameters 6 2.2.2 Abbreviations 6 2.2.3 Subscripts . 7 3. TECHNICAL BACKGROUND . 7 3.1 Model Testing as a Tool 11 4. ENGINE TEST CELLS 12 4.1 Test Cell Design Considerati
15、ons 12 4.2 Test Cell Performance Requirements . 13 5. TEST CELL MODELING TECHNIQUES 13 5.1 Selection of Scale Factor 13 5.2 Model Hardware Requirements and Considerations 14 5.3 Model Test Cell Instrumentation Techniques . 14 5.4 Model Data Acquisition and Reduction . 18 6. ENGINE SIMULATION . 19 6.
16、1 Engine Simulator Requirements . 19 6.2 Engine Simulator Design Considerations . 21 7. TEST CELL AERODYNAMIC PARAMETERS TO BE OBTAINED 22 7.1 Front Cell Velocity Distortion . 22 7.2 Front Cell Airflow . 24 7.3 Bellmouth Total Pressure Distortion . 24 7.4 Bellmouth Airflow 25 7.5 Vortex Strength and
17、 Location . 26 7.6 Cell Bypass Ratio 26 7.7 Cell Depression . 27 8. CONCLUSIONS 28 9. NOTES 28 FIGURE 1 PHOTOGRAPH OF THE DAMAGE SUSTAINED BY A LARGE, HIGH-BYPASS TURBOFAN ENGINE AS A RESULT OF AN INCIDENT RELATED TO A SEVERE TEST CELL AERODYNAMIC PROBLEM . 9 FIGURE 2 CLOSE-UP PHOTOGRAPH OF THE ENGI
18、NE DAMAGE SUSTAINED AS A RESULT OF AN INCIDENT RELATED TO A SEVERE TEST CELL AERODYNAMIC PROBLEM . 10 FIGURE 3 PHOTOGRAPH OF A STRONG, WELL-DEFINED VORTEX BEING INGESTED BY AN ENGINE OPERATING IN A TEST CELL WITH A LOW CELL BYPASS RATIO . 11 FIGURE 4 GENERAL DESIGN CONCEPTS FOR AN ENGINE TEST CELL F
19、OR A LARGE, HIGH-BYPASS TURBOFAN ENGINE 12 FIGURE 5 TYPICAL LARGE TURBOFAN ENGINE TEST CELL SCALE MODEL, SIMILAR TO CONCEPTUAL DESIGN SHOWN IN FIGURE 4, WITH CF6-80C2 ENGINE SIMULATOR INSTALLED 15 FIGURE 6 PHOTOGRAPH OF A TYPICAL INSTALLATION OF HOT FILM PROBES WITH TRAVERSING SYSTEM IN THE FRONT CE
20、LL REGION OF A MODEL TEST CELL . 17 FIGURE 7 PHOTOGRAPH OF A TYPICAL INSTALLATION OF THE EJECTOR DRIVE AIR SUPPLY STRUT FOR THE ENGINE SIMULATOR AND THE THRUST MEASURING SYSTEM USING A CONVENTIONAL LOAD CELL FOR THE FORCE MEASUREMENT . 18 FIGURE 8 ENGINE SIMULATOR AND EXTERIOR FLOW FEATURES 19 FIGUR
21、E 9 EJECTOR-POWERED ENGINE SIMULATOR INTERIOR FLOW FEATURES 21 FIGURE 10 COMBINED OUTLINE AND CUTAWAY SCHEMATIC OF CFM56-3 EJECTOR-POWERED ENGINE SIMULATOR 23 Copyright SAE International Provided by IHS under license with SAENot for ResaleNo reproduction or networking permitted without license from
22、IHS-,-,-SAE AIR4827A Page 3 of 28 FIGURE 11 PHOTOGRAPH OF A TYPICAL INSTALLATION SHOWING THE CF6-80C2 EJECTOR-POWERED ENGINEN SIMULATOR IN THE TEST CHAMBER OF A SCALE MODEL TEST CELL (FROM REFERENCE 2.1.3) . 23 FIGURE 12 BELLMOUTH-INGESTED VORTEX FORMATION RESULTS AS A FUNCTION OF CELL BYPASS RATIO
23、AS DETERMINED FROM VIDEO TAPE RECORDS OF FLOW VISUALIZATION (FROM REFERENCE 2.1.2) . 27 Copyright SAE International Provided by IHS under license with SAENot for ResaleNo reproduction or networking permitted without license from IHS-,-,-SAE AIR4827A Page 4 of 28 1. SCOPE This SAE Aerospace Informati
24、on Report (AIR) has been written for individuals associated with ground level testing of turbofan and turbojet engines and particularly for those who might be interested in investigating the performance characteristics of a new test cell design or of proposed modifications to an existing test cell b
25、y means of a scale model test. 1.1 Purpose The purpose of this information report is two-fold: 1.1.1 Provision of Guidelines One of the primary purposes of this report is to provide guidelines for performing a scale model test of new configurations of and/or proposed modifications to a ground level
26、enclosed test facility for turbofan and turbojet engine applications, i.e., a jet engine test cell. 1.1.2 Discussion of Considerations Another important purpose is to address the major considerations when performing such a model test in the two main areas of the engine test cell model and the simula
27、tion of the engine. Requirements for the scale model test cell hardware and the associated instrumentation are presented and discussed. The requirements and considerations for the simulation of the engine are given, along with some of the special considerations which should be made when air ejector
28、systems are the motive power for the simulator. 2. REFERENCES The following publications for a part of this document to the extent specified herein. The latest issue of SAE publications shall apply. The applicable issue of the other publications shall be the issue in effect on the date of the purcha
29、se order. 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 applicable laws and regulations unless a specific exemption has been obtained. 2.1 Applicable Documents The foll
30、owing is a list of some applicable references and documents used in the preparation of this report: 2.1.1 Ashwood, P. F., and Mitchell, J. J.: “The Uniform Engine Test Programme“, AGARD Advisory Report No. 248 (AGARD-AR-248), Advisory Group for Aerospace Research and Development, North Atlantic Trea
31、ty Organization, Neuilly Sur Seine, France, February 1990 2.1.2 Freuler, R. J., and Dickman, R. A.: “Current Techniques for Jet Engine Test Cell Modeling“, AIAA Paper No. 82-1272, Paper presented to the AIAA/SAE/ASME 18th Joint Propulsion Conference, Cleveland, Ohio, June 21-23, 1982 2.1.3 Freuler,
32、R. J.: “An Investigation of Jet Engine Test Cell Aerodynamics by Means of Scale Model Test Studies with Comparisons to Full-Scale Test Results“, Ph.D. Dissertation, The Ohio State University, Columbus, Ohio, December 1991 2.1.4 Karamanlis, A. I., Sokhey, J. S., Dunn, T. C., and Bellomy, D. C.: “Theo
33、retical and Experimental Investigation of Test Cell Aerodynamics for Turbofan Applications“, AIAA Paper No. 86-1732, AIAA/ASME/SAE/ASEE 22nd Joint Propulsion Conference, Huntsville, Alabama, June 16-18, 1986 2.1.5 Lee, J. D., and Freuler, R. J.: “Engine Simulator Techniques for Scaled Test Cell Stud
34、ies“, AIAA Paper No. 85-1282, Paper presented to the AIAA/SAE/ASME/ASEE 21st Joint Propulsion Conference, Monterey, California, July 1985 Copyright SAE International Provided by IHS under license with SAENot for ResaleNo reproduction or networking permitted without license from IHS-,-,-SAE AIR4827A
35、Page 5 of 28 2.1.6 MacLeod, J. D.: “A Derivation of Gross Thrust for a Sea-Level Jet Engine Test Cell“, Division of Mechanical Engineering Report No. DM-009, National Research Council Canada, Ottawa, Ontario, 1988 2.1.7 SAE Committee EG-1, Aerospace Propulsion Systems Support Equipment: “Design Cons
36、iderations for Enclosed Turbofan/Turbojet Engine Test Cells“, Subcommittee EG-1E, Gas Turbine Engine Test Facilities and Equipment, SAE Project Number EG-1-E87-3, Society of Automotive Engineers, Warrendale, Pennsylvania, Draft AIR dated September 1990 2.1.8 Karamanlis, A. I., Freuler, R. J., Lee, J
37、. D., Hoelmer, W., and Bellomy, D. C.: “A Universal Turboshaft Engine Test Cell - Design Considerations and Model Test Results“, AIAA Paper No. 85-0382, Paper presented to the AIAA 23rd Aerospace Sciences Meeting, Reno, Nevada, January 1985 2.1.9 Dickman, R. A., Hoelmer, W., Freuler, R. J., and Hehm
38、ann, H. W.: A Solution for Aero-Acoustic Induced Vibrations Originating in a Turbofan Engine Test Cell“, AIAA Paper No. 84-0594, Paper presented to the AIAA 13th Aerodynamic Testing Conference, San Diego, California, AIAA Conference Proceedings CP841, March 1984, pp. 99-108 2.1.10 Kromer-Oehler, S.
39、L. and Dietrich, D. A.: “Computational Analysis of the Flow Field in an Engine Test Cell“, AIAA Paper No. 84-0285, paper presented to the AIAA 22nd Aerospace Sciences Meeting, Reno, Nevada, January 9-12, 1984 2.1.11 Barton, J. M.: “The Role of Computational Fluid Dynamics in Aeropropulsion Ground Te
40、sting“, Journal of Aircraft, Vol. 10, October 1984, pp. 745-750 2.1.12 Freuler, R. J. and Montgomery, K. A.: “Allison Gas Turbine Division Model AG9130/DDG-51 Ship Service Gas Turbine Generator Air Intakes Scale Model Test Report“, Allison Gas Turbine Division Report No. EDR 14737, Allison Gas Turbi
41、ne Division, Indianapolis, Indiana, September 20, 1990 2.1.13 Smith, T. E.: “LM1600 Bravo-Romeo Project - Wind Tunnel Test to Determine Engine Inlet Flow Quality“, General Electric Technical Memorandum, TM No. 90-460, GE Aircraft Engines, Cincinnati, Ohio, November 1990 2.1.14 Eckert, D., van Ditshu
42、izen, J. C. A., Munniksma, B., and Burgsmuller, W.: “Low Speed Twin Engine Simulation on a Large Scale Transport Aircraft Model in the DNW“, ICAS Paper No. 84-2.10.4, Proceedings of the 14th Congress of the International Council of the Aeronautical Sciences, Vol. 2, Toulouse, France, September 10-14
43、, 1984 2.1.15 Harris, A. E. and Paliwal, K. C.: “Civil Turbofan Propulsion System Integration Studies Using Powered Testing Techniques at ARA, Bedford“, AIAA paper No. 84-0593, Proceedings of the AIAA 13th Aerodynamic Testing Conference, San Diego, California, AIAA Conference Proceedings CP841, Marc
44、h 1984, pp. 74-98 2.1.16 Wagenknecht, C. D., Hoff, G. E., and Norbut, T. J.: “Performance Calibration Results for a Compact Multimission Aircraft Propulsion Simulator“, AIAA Paper No. 82-0254, Paper presented to the AIAA 20th Aerospace Sciences Meeting, Orlando, Florida, January 11-14, 1982 2.1.17 S
45、mith, G. D., Matz, R. J., and Bauer, R. C.: “Analytical and Experimental Investigation of Ejector- Powered Engine Simulators for Wind Tunnel Models“, AEDC-TR-76-128, Arnold Engineering Development Center, Arnold Air Force Station, Tennessee, January 1977 2.1.18 Hoelmer, W. and Freuler, R. J.: “Lufth
46、ansa German Airlines, Frankfurt Test Cell Aero Evaluation, Scale Model Test Program“, International Engine Support Operations Memorandum Report, GE Aircraft Engines, Cincinnati, Ohio, June 10, 1988 2.1.19 Minardi, J. E. and Von Ohain, H. P.: “Thrust Augmentation Study of High Performance Ejectors“,
47、AFWAL-TR-83-3087, Flight Dynamics Laboratory, Air Force Wright Aeronautical Laboratories, Wright-Patterson Air Force Base, Ohio, November 1983 Copyright SAE International Provided by IHS under license with SAENot for ResaleNo reproduction or networking permitted without license from IHS-,-,-SAE AIR4
48、827A Page 6 of 28 2.1.20 Lau, J. C.: “Effects of Exit Mach Number and Temperature on Mean-Flow and Turbulence Characteristics in Round Jets“, Journal of Fluid Mechanics, Vol. 105, 1981, pp. 193-218 2.1.21 Quinn, B.: “Ejector Performance at High Temperatures and Pressures“, Journal of Aircraft, Vol.
49、13, December 1976, pp. 948-954 2.2.22 SAE Committee EG-1E, “ Inlet Air Flow Ramps for Gas Turbine Test Cells”, AIR 5306, May 2000. 2.2 Symbols and Abbreviations The following parameters, abbreviations, and subscript notations are used in this report: 2.2.1 Parameters A cross-sectional area, square i
