SAE AIR 5306A-2013 Inlet Airflow Ramps for Gas Turbine Engine Test Cells《燃气涡轮发动机试验电池用进气道气流斜道》.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 2013 SAE International All rights reserved. No part of this pu
3、blication 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
4、 (outside USA) Fax: 724-776-0790 Email: CustomerServicesae.org SAE WEB ADDRESS: http:/www.sae.orgSAE values your input. To provide feedback on this Technical Report, please visit http:/www.sae.org/technical/standards/AIR5306AAEROSPACEINFORMATION REPORT AIR5306 REV. AIssued 2000-07 Reaffirmed 2007-11
5、 Stabilized 2013-12 Superseding AIR5306 Inlet Airflow Ramps for Gas Turbine Engine Test Cells RATIONALEThis document has been determined to contain stable technology which is not dynamic in nature. STABILIZED NOTICE This document has been declared “Stabilized“ by the SAE EG-1E Gas Turbine Test Facil
6、ities and Equipment and will no longer be subjected to periodic reviews for currency. Users are responsible for verifying references and continued suitability of technical requirements. Newer technology may exist. Copyright SAE International Provided by IHS under license with SAENot for ResaleNo rep
7、roduction or networking permitted without license from IHS-,-,-TABLE OF CONTENTS1. SCOPE .21.1 Purpose .22. REFERENCES .22.1 Applicable Documents.22.2 Symbols and Abbreviations .32.2.1 Parameters 32.2.2 Abbreviations.32.2.3 Subscripts33. TECHNICAL BACKGROUND.43.1 Cell Bypass Ratio 54. INLET RAMPS74.
8、1 Description.74.2 Application .84.3 Engine Room Requirements84.4 Ejector Tube Requirements.94.5 Model Test Results105. CONCLUSIONS .126. NOTES .126.1 Patent Information .126.2 Key Words .12SAE INTERNATIONAL AIR5306A Page 1 of 12_Copyright SAE International Provided by IHS under license with SAENot
9、for ResaleNo reproduction or networking permitted without license from IHS-,-,-1. SCOPE:This SAE Aerospace Information Report (AIR) has been written for individuals associated with the ground-level testing of gas turbine engines and particularly for those who might be interested in upgrading their e
10、xisting engine test facility to meet the airflow requirements for higher thrust engine models. The intellectual property rights on the material contained in this document are protected by US Patent Number 5,293,775 dated March 15, 1994 assigned to United Technologies Corporation, Hartford, Connectic
11、ut, USA. Any individual, or organization, attempting to use the system described in this document should get a clearance from United Technologies Corporation, to avoid any potential liability arising from patent infringement.1.1 Purpose:To provide guidelines for inlet airflow ramps for gas turbine e
12、ngine test cells.2. REFERENCES:2.1 Applicable Documents:The following is a list of some applicable references and documents used in the preparation of this report:2.1.1 Freuler, R.J., Dickman, R.A., Current Techniques for Jet Engine Test Cell Modeling. AIAA-82-1272, Presented at the 18th Joint Propu
13、lsion Conference, June 21-23, 1982, Cleveland, Ohio.2.1.2 De Siervi, F., Viguier, H.C., Greitzer, E.M., Tan, C.S., Mechanisms of Inlet-Vortex Formation, Journal of Fluid Mechanics, 1982, volume 124, pp. 173-207.2.1.3 Glenny, D.E., Pyestock, N.G.T.E., Ingestion of Debris into Intakes by Vortex Action
14、, Ministry of Technology, 1970, Aeronautical Research Council, C.P. no. 1114.2.1.4 Clark, T., Peszko, M., Roberts, J., Muller, G., Nikkanen, J., United States Patent, Patent Number 5,293,775, March 15, 1994, Assignee: United Technologies Corporation, Hartford, Conn.2.1.5 “Design Considerations for E
15、nclosed Turbofan/Turbojet Engine Test Cell“, SAE Aerospace Information Report AIR4869, Society of Automotive Engineers, Warrendale, Pennsylvania, Issued October 1995.2.1.6 “Modeling Techniques for Jet Engine Test Cell Aerodynamics“, SAE Aerospace Information Report AIR4827, Society of Automotive Eng
16、ineers, Warrendale, Pennsylvania, Issued May 1993.2.1.7 “Test Cell Instrumentation“, SAE Aerospace Information Report AIR5026, Society of Automotive Engineers, Warrendale, Pennsylvania, Issued November 1996.SAE INTERNATIONAL AIR5306A Page 2 of 12_Copyright SAE International Provided by IHS under lic
17、ense with SAENot for ResaleNo reproduction or networking permitted without license from IHS-,-,-2.1.8 “Turbofan and Turbojet Gas Turbine Engine Test Cell Correlation“, SAE Aerospace Recommended Practice ARP741 Rev. A, Society of Automotive Engineers, Warrendale, Pennsylvania, Revised September 1, 19
18、93.2.2 Symbols and Abbreviations:The following parameters, abbreviations, and subscript notations are used in this report:2.2.1 Parameters:LOSS pressure loss at vortex centerPt total pressureQ dynamic pressure (1/2 V2)V velocityW airflow ratePt pressure difference between inlet Pt and vortex core Pt
19、 cell bypass ratio air density2.2.2 Abbreviations:D inlet diameterFC front cellft feetft/s feet per secondH engine centerline heightkg/s kilograms per secondkN kiloNewtonslbm/s pounds-mass per secondm metersSAE Society of Automotive Engineers2.2.3 Subscripts:BYPASS cell bypass flowENG engineENGINE e
20、ngineFC front cellVORTEX inlet vortexSAE INTERNATIONAL AIR5306A Page 3 of 12_Copyright SAE International Provided by IHS under license with SAENot for ResaleNo reproduction or networking permitted without license from IHS-,-,-3. TECHNICAL BACKGROUND:Due to the introduction of a new generation of hig
21、h thrust turbofans, stability and stall problems can be encountered when larger and more powerful engines are operated in an engine test facility. This is generally due to the momentary or steady formation of an inlet vortex. Inlet vortices form near the engine inlet bellmouth where local decelerati
22、on in airflow causes an adverse pressure gradient resulting in flow separation along the adjacent surfaces of ceiling, floor, or walls. An inlet vortex is formed when a stagnation point, due to velocity shear, exists in the vicinity of the engine inlet. Severe velocity and pressure distortion at the
23、 engine inlet plane will result where conditions are present that permit inlet vortex formation. Vortex ingestion by the fan can cause noise and small performance shifts while a vortex that enters the engine core is likely to cause compressor surge or stall. Severe engine damage can result from a co
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