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 theref
2、rom, 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 2016 SAE InternationalAll rights reserved. No part of this publi
3、cation 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: +1 724-776-4970 (out
4、side USA)Fax: 724-776-0790Email: CustomerServicesae.orgSAE WEB ADDRESS: http:/www.sae.orgSAE values your input. To provide feedback on thisTechnical Report, please visithttp:/standards.sae.org/AIR4827BAEROSPACEINFORMATION REPORTAIR4827 REV. BIssued 1993-05Reaffirmed 1999-05Revised 2016-10Superseding
5、 AIR4827APhysical Modeling Techniques for Jet Engine Test Cell AerodynamicsRATIONALERevision based on the 5 year review. Document name is changed to more accurately reflect report subject. FOREWORDOne of the strongest motives for developing the scale modeling techniques to allow investigation of eng
6、ine test cell aerodynamics as described in this work 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 rema
7、ined a lack of appreciation for the fundamental importance 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
8、proper attention to scale modeling techniques, the aerodynamics 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 engi
9、nes indoors. A much improved understanding and heightened 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.ABSTRACTResearch studies focusing on jet engine test cell aerod
10、ynamics, acoustics, and cell flow characteristics as 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
11、demonstrated that simulators of low-bypass afterburning 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 p
12、ower. Specific components of a test cell such as inlets 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 mode
13、l testing and engine simulators and the methods which can be used to attack these problems are described.SAE INTERNATIONAL AIR4827B Page 2 of 28TABLE OF CONTENTS1. SCOPE41.1 Purpose.41.1.1 Provision of Guidelines .41.1.2 Discussion of Considerations42. REFERENCES42.1 Applicable Documents 42.2 Symbol
14、s and Abbreviations 62.2.1 Parameters62.2.2 Abbreviations 72.2.3 Subscripts .73. TECHNICAL BACKGROUND.83.1 Model Testing as a Tool114. ENGINE TEST CELLS124.1 Test Cell Design Considerations.124.2 Test Cell Performance Requirements.135. TEST CELL MODELING TECHNIQUES135.1 Selection of Scale Factor 135
15、.2 Model Hardware Requirements and Considerations 145.3 Model Test Cell Instrumentation Techniques .145.4 Model Data Acquisition and Reduction.186. ENGINE SIMULATION .196.1 Engine Simulator Requirements .196.2 Engine Simulator Design Considerations .217. TEST CELL AERODYNAMIC PARAMETERS TO BE OBTAIN
16、ED227.1 Front Cell Velocity Distortion.227.2 Front Cell Airflow.247.3 Bellmouth Total Pressure Distortion .247.4 Bellmouth Airflow 257.5 Vortex Strength and Location .267.6 Cell Bypass Ratio267.7 Cell Depression.278. CONCLUSIONS289. NOTES289.1 Revision Indicator28FIGURE 1 PHOTOGRAPH OF THE DAMAGE SU
17、STAINED BY A LARGE, HIGH-BYPASS TURBOFAN ENGINE AS A RESULT OF AN INCIDENT RELATED TO A SEVERE TEST CELL AERODYNAMIC PROBLEM. 9FIGURE 2 CLOSE-UP PHOTOGRAPH OF THE ENGINE DAMAGE SUSTAINED AS A RESULT OF AN INCIDENT RELATED TO A SEVERE TEST CELL AERODYNAMIC PROBLEM .10FIGURE 3 PHOTOGRAPH OF A STRONG,
18、WELL-DEFINED VORTEX BEING INGESTED BY AN ENGINE OPERATING IN A TEST CELL WITH A LOW CELL BYPASS RATIO 11FIGURE 4 GENERAL DESIGN CONCEPTS FOR AN ENGINE TEST CELL FOR A LARGE, HIGH-BYPASS TURBOFAN ENGINE 12FIGURE 5 TYPICAL LARGE TURBOFAN ENGINE TEST CELL SCALE MODEL, SIMILAR TO CONCEPTUAL DESIGN SHOWN
19、 IN FIGURE 4, WITH CF6-80C2 ENGINE SIMULATOR INSTALLED 15SAE INTERNATIONAL AIR4827B Page 3 of 28FIGURE 6 PHOTOGRAPH OF A TYPICAL INSTALLATION OF HOT FILM PROBES WITH TRAVERSING SYSTEM IN THE FRONT CELL REGION OF A MODEL TEST CELL 17FIGURE 7 PHOTOGRAPH OF A TYPICAL INSTALLATION OF THE EJECTOR DRIVE A
20、IR SUPPLY STRUT FOR THE ENGINE SIMULATOR AND THE THRUST MEASURING SYSTEM USING A CONVENTIONAL LOAD CELL FOR THE FORCE MEASUREMENT .18FIGURE 8 ENGINE SIMULATOR AND EXTERIOR FLOW FEATURES 19FIGURE 9 EJECTOR-POWERED ENGINE SIMULATOR INTERIOR FLOW FEATURES 21FIGURE 10 COMBINED OUTLINE AND CUTAWAY SCHEMA
21、TIC OF CFM56-3 EJECTOR-POWERED ENGINE SIMULATOR 23FIGURE 11 PHOTOGRAPH OF A TYPICAL INSTALLATION SHOWING THE CF6-80C2 EJECTOR-POWERED ENGINE SIMULATOR IN THE TEST CHAMBER OF A SCALE MODEL TEST CELL (FROM REFERENCE 2.1.3) 23FIGURE 12 BELLMOUTH-INGESTED VORTEX FORMATION RESULTS AS A FUNCTION OF CELL B
22、YPASS RATIO AS DETERMINED FROM VIDEO TAPE RECORDS OF FLOW VISUALIZATION (FROM REFERENCE 2.1.2) 27SAE INTERNATIONAL AIR4827B Page 4 of 281. SCOPEThis SAE Aerospace Information Report (AIR) has been written for individuals associated with ground level testing of turbofan and turbojet engines and parti
23、cularly 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 by means of a scale model test.1.1 PurposeThe purpose of this information report is two-fold:1.1.1 Provision of GuidelinesOne of
24、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 enclosed test facility for turbofan and turbojet engine applications, i.e., a jet engine test cell.1.1.2 Discussion of Consideration
25、sAnother 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 simulation of the engine. Requirements for the scale model test cell hardware and the associated instrumentation are presented and discussed
26、. 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 systems are the motive power for the simulator.2. REFERENCESThe following publications form a part of this document to the extent spec
27、ified 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 theevent of conflict between the text of this document and references cited herein, the text of this document takes precedence
28、. Nothing in this document, however, supersedes applicable laws and regulations unless a specific exemption has been obtained.2.1 Applicable DocumentsThe following 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.:
29、 “The Uniform Engine Test Programme“, AGARD Advisory Report No. 248 (AGARD-AR-248), Advisory Group for Aerospace Research and Development, North Atlantic Treaty Organization, Neuilly Sur Seine, France.2.1.2 Freuler, R. J., and Dickman, R. A.: “Current Techniques for Jet Engine Test Cell Modeling“, A
30、IAA 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, 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. Disser
31、tation, The Ohio State University, Columbus, Ohio, December 1991.2.1.4 Karamanlis, A. I., Sokhey, J. S., Dunn, T. C., and Bellomy, D. C.: “Theoretical and Experimental Investigation of Test Cell Aerodynamics for Turbofan Applications“, AIAA Paper No. 86-1732, AIAA/ASME/SAE/ASEE 22nd Joint Propulsion
32、 Conference, Huntsville, Alabama, June 16-18, 1986.SAE INTERNATIONAL AIR4827B Page 5 of 282.1.5 Lee, J. D., and Freuler, R. J.: “Engine Simulator Techniques for Scaled Test Cell Studies“, AIAA Paper No. 85-1282, Paper presented to the AIAA/SAE/ASME/ASEE 21st Joint Propulsion Conference, Monterey, Ca
33、lifornia, July 1985.2.1.6 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.2.1.7 SAE International Aerospace Information Report, “Design Considerations for Encl
34、osed Turbofan/Turbojet Engine Test Cells,” SAE Standard AIR4869, Reaf. Sept. 2015.2.1.8 Karamanlis, A. I., Freuler, R. J., Lee, J. 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
35、 the AIAA 23rd Aerospace Sciences Meeting, Reno, Nevada, January 1985.2.1.9 Dickman, R. A., Hoelmer, W., Freuler, R. J., and Hehmann, 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 Aerodynam
36、ic Testing Conference, San Diego, California, AIAA Conference Proceedings CP841, March 1984, pp. 99-108.2.1.10 Kromer-Oehler, S. 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 Meet
37、ing, Reno, Nevada, January 9-12, 1984.2.1.11 Barton, J. M.: “The Role of Computational Fluid Dynamics in Aeropropulsion Ground Testing“, 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
38、 Gas Turbine Generator Air Intakes Scale Model Test Report“, Allison Gas Turbine Division Report No. EDR 14737, Allison Gas Turbine Division, Indianapolis, Indiana.2.1.13 Smith, T. E.: “LM1600 Bravo-Romeo Project - Wind Tunnel Test to Determine Engine Inlet Flow Quality“, General Electric Technical
39、Memorandum, TM No. 90-460, GE Aircraft Engines, Cincinnati, Ohio.2.1.14 Eckert, D., van Ditshuizen, 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
40、 International Council of the Aeronautical Sciences, Vol. 2, Toulouse, France, September 10-14, 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
41、Aerodynamic Testing Conference, San Diego, California, AIAA Conference Proceedings CP841, March 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 present
42、ed to the AIAA 20th Aerospace Sciences Meeting, Orlando, Florida, January 11-14, 1982.SAE INTERNATIONAL AIR4827B Page 6 of 282.1.17 Smith, 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, A
43、rnold Engineering Development Center, Arnold Air Force Station, Tennessee.2.1.18 Hoelmer, W. and Freuler, R. J.: “Lufthansa German Airlines, Frankfurt Test Cell Aero Evaluation, Scale Model Test Program“, International Engine Support Operations Memorandum Report, GE Aircraft Engines, Cincinnati, Ohi
44、o.2.1.19 Minardi, J. E. and Von Ohain, H. P.: “Thrust Augmentation Study of High Performance Ejectors“, AFWAL-TR-83-3087, Flight Dynamics Laboratory, Air Force Wright Aeronautical Laboratories, Wright-Patterson Air Force Base, Ohio.2.1.20 Lau, J. C.: “Effects of Exit Mach Number and Temperature on M
45、ean-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. 13, December 1976, pp. 948-954.2.1.22 SAE International Aerospace Information Report,
46、“Inlet Airflow Ramps for Gas Turbine Engine Test Cells,” SAE Standard AIR5306, Stab. Dec. 2013.2.1.23 SAE International Aerospace Information Report, “Design Considerations for Enclosed Turboshaft Engine Test Cells,” SAE Standard AIR4989, Rev. Sept. 2013.2.2 Symbols and AbbreviationsThe following pa
47、rameters, abbreviations, and subscript notations are used in this report:2.2.1 ParametersParameter units throughout this report are dual dimensioned primarily in SI Units with US Customary Units in brackets.A cross-sectional area, square centimeter square inches or square meters square feetCd flow c
48、oefficient, non-dimensionalg gravitational constant, meters per second per second feet per second per secondmmass flow rate, kilograms per second slugs per secondM Mach number, non-dimensionalp pressure, Pascal pounds per square inch, pounds per square foot, or inches of waterR gas constant, joules
49、per kilogram kevlin square feet per square seconds-degrees RankineRe Reynolds number, non-dimensionalT temperature, degrees kelvin degrees RankineV velocity, meters per second feet per secondW airflow rate, kilograms per second pounds (mass) per second= cell bypass ratio, non-dimensional ratio of specific heats, non-dimensionalO density, kilograms per cubic meter slugs per cubic footSAE INTERNATIONAL AIR4827B Pa
