SAE-AIR-5306-2000-R2007.pdf
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1、AEROSPACE INFORMATION REPORT AIR5306 Issued2000-07 Inlet Airflow Ramps for Gas Turbine Engine Test Cells TABLE OF CONTENTS 1.SCOPE .2 1.1Purpose .2 2.REFERENCES .2 2.1Applicable Documents.2 2.2Symbols and Abbreviations .3 2.2.1 Parameters3 2.2.2 Abbreviations.3 2.2.3 Subscripts3 3.TECHNICAL BACKGROU
2、ND.4 3.1Cell Bypass Ratio 5 4.INLET RAMPS7 4.1Description.7 4.2Application.8 4.3Engine Room Requirements8 4.4Ejector Tube Requirements.9 4.5Model Test Results10 5.CONCLUSIONS .12 6.NOTES .12 6.1Patent Information .12 6.2Key Words .12 SAE Technical Standards Board Rules provide that: “This report is
3、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 therefrom, is the sole responsibility of the user.” SAE reviews each tech
4、nical report at least every five years at which time it may be reaffirmed, revised, or cancelled. SAE invites your written comments and suggestions. Copyright 2007 SAE International All rights reserved. No part of this publication may be reproduced, stored in a retrieval system or transmitted, in an
5、y 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) Fax: 724-776-0790 Email: CustomerServicesae.org SAE WEB ADDRESS: ht
6、tp:/www.sae.org Reaffirmed 2007-11 Copyright SAE International Provided by IHS under license with SAELicensee=Defense Supply Ctr/5913977001 Not for Resale, 12/04/2007 19:52:03 MSTNo reproduction or networking permitted without license from IHS -,-,- SAE AIR5306 - 2 - 1.SCOPE: This SAE Aerospace Info
7、rmation 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 existing engine test facility to meet the airflow requirements for higher thrust engine models. The intellectual
8、 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, Connecticut, USA. Any individual, or organization, attempting to use the system described in this document should get a
9、clearance from United Technologies Corporation, to avoid any potential liability arising from patent infringement. 1.1Purpose: To provide guidelines for inlet airflow ramps for gas turbine engine test cells. 2.REFERENCES: 2.1Applicable Documents: The following is a list of some applicable references
10、 and documents used in the preparation of this report: 2.1.1Freuler, R.J., Dickman, R.A., Current Techniques for Jet Engine Test Cell Modeling. AIAA-82- 1272, Presented at the 18th Joint Propulsion Conference, June 21-23, 1982, Cleveland, Ohio. 2.1.2De Siervi, F., Viguier, H.C., Greitzer, E.M., Tan,
11、 C.S., Mechanisms of Inlet-Vortex Formation, Journal of Fluid Mechanics, 1982, volume 124, pp. 173-207. 2.1.3Glenny, D.E., Pyestock, N.G.T.E., Ingestion of Debris into Intakes by Vortex Action, Ministry of Technology, 1970, Aeronautical Research Council, C.P. no. 1114. 2.1.4Clark, T., Peszko, M., Ro
12、berts, 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 Enclosed Turbofan/Turbojet Engine Test Cell“, SAE Aerospace Information Report AIR4869, Society of Automotive
13、 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 Engineers, Warrendale, Pennsylvania, Issued May 1993. 2.1.7“Test Cell Instrumentation“, SAE Aerospace Informati
14、on Report AIR5026, Society of Automotive Engineers, Warrendale, Pennsylvania, Issued November 1996. Copyright SAE International Provided by IHS under license with SAELicensee=Defense Supply Ctr/5913977001 Not for Resale, 12/04/2007 19:52:03 MSTNo reproduction or networking permitted without license
15、from IHS -,-,- SAE AIR5306 - 3 - 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, 1993. 2.2Symbols and Abbreviations: The following parameters, abbr
16、eviations, and subscript notations are used in this report: 2.2.1Parameters: LOSSpressure loss at vortex center Pttotal pressure Qdynamic pressure (1/2 V2) Vvelocity Wairflow rate Ptpressure difference between inlet Pt and vortex core Pt cell bypass ratio air density 2.2.2Abbreviations: Dinlet diame
17、ter FCfront cell ftfeet ft/sfeet per second Hengine centerline height kg/skilograms per second kNkiloNewtons lbm/spounds-mass per second mmeters SAESociety of Automotive Engineers 2.2.3Subscripts: BYPASScell bypass flow ENGengine ENGINEengine FCfront cell VORTEXinlet vortex Copyright SAE Internation
18、al Provided by IHS under license with SAELicensee=Defense Supply Ctr/5913977001 Not for Resale, 12/04/2007 19:52:03 MSTNo reproduction or networking permitted without license from IHS -,-,- SAE AIR5306 - 4 - 3.TECHNICAL BACKGROUND: Due to the introduction of a new generation of high thrust turbofans
19、, 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 deceleration in airflow caus
20、es 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 engine inlet plan
21、e 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 compressor surge or
22、stall and, therefore, it is unacceptable to operate an engine for testing under conditions that permit this event to occur. Experiments conducted by Freuler and Dickman for jet engine test cell modeling concluded that inlet vortices can be suppressed by test cell operation at a bypass ratio (see 3.1
23、) of 0.8 or greater (2.1.1). Vortex formation from the cell floor has also been generally characterized to be a function of engine centerline height to inlet diameter (H/D) as described in references 2.1.2 and 2.1.3. The potential for vortex formation as a function of distance to engine room surface
24、s and inlet diameter applies to the adjacent walls and ceiling as well. Decreasing this ratio with the engine inlet bellmouth closer to the adjacent ceiling, floor or wall surfaces increases the potential for a vortex to form. Traditional test cell design practices recommend that an engine test cell
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