SAE ARP 4865A-2013 Gas Turbine Engine Fuel Nozzle Test Procedures《燃气涡轮发动机的燃料喷嘴试验程序》.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/ARP4865AAEROSPACERECOMMENDED PRACTICEARP4865 REV. AIssued 1997-01 Reaffirmed 2007-1

5、1 Stabilized 2013-12 Superseding ARP4865 Gas Turbine Engine Fuel Nozzle Test Procedures 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 Facilities

6、and Equipment Committee 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

7、 reproduction or networking permitted without license from IHS-,-,-FOREWORDFuel nozzle performance requires measurement of fluid flow and pressure as well as the quality orform and symmetry of the spray. The spray produced by most nozzles is measurable and must meetcertain criteria. The test equipme

8、nt used for these measurements must meet specific accuracyrequirements for flow, pressure, and temperature. The test conditions, test fixturing for holding thenozzle, and the methods used to measure the various spray acceptance criteria must also becontrolled.There are two main categories of nozzle

9、design; pressure atomizer and air blast. The pressureatomizer uses fluid pressure as the main mechanism for breakup of the fluid into droplets. The outletorifice is small and a swirl device upstream of the outlet orifice establishes spray angle. This designprovides a very distinct spray angle and ai

10、r is introduced into this angle without causing distortions. Fluid pressure to the inlet of the nozzle nominally is between 25 to 550 psig. The air blast design usesthe air as the main mechanism for breakup of the fluid into droplets. The air is directed at the sheet offluid exiting from an internal

11、 prefilmer located at the exit of the nozzle. The spray angle is lessapparent and the fuel distribution is less concentrated. Fluid pressure to the inlet of the nozzlenominally is between 2 to 50 psig. Both designs may incorporate flow divider valves that can changethe inlet pressure versus outlet f

12、low curve. Flow divider valves are common on designs with a primaryand secondary flow channel. The valve secondary flow will begin at higher pressures after the enginestart sequence is completed.1. SCOPE:The intent of this SAE Aerospace Recommended Practice (ARP) is to define and recommend tothe Aer

13、ospace Industry standardized test procedures for establishing fuel nozzle operatingperformance including types of tests, controlled and measured parameters, and test configurations._SAE INTERNATIONAL ARP4865A Page 1 of 31Copyright SAE International Provided by IHS under license with SAENot for Resal

14、eNo reproduction or networking permitted without license from IHS-,-,-2. APPLICABLE DOCUMENTS:The following publications form a part of this document to the extent specified herein. The latestissue of SAE publications shall apply. The applicable issue of other publications shall be the issuein effec

15、t on the date of the purchase order. In the event of conflict between the text of thisdocument and references cited herein, the text of this document takes precedence. Nothing in thisdocument, however, supersedes applicable laws and regulations unless a specific exemption hasbeen obtained.2.1 SAE Pu

16、blications:Available from SAE, 400 Commonwealth Drive, Warrendale, PA 15096-0001.ARP598 The Determination of Particulate Contamination in Liquids by the Particle CountMethodARP785 Procedure for the Determination of Particulate Contamination in Hydraulic Fluids bythe Control Filter Gravimetric Proced

17、ure2.2 ANSI Publications: Available from ANSI, 11 West 42nd Street, New York, NY 10036-8002.ISO 4402 Hydraulic Fluid Power. Calibration of Liquid Automatic Particle-Count Instruments-Method Using Air Cleaner Fine Test Dust ContaminantISO 10012-1 Quality Assurance Requirements for Measuring Equipment

18、, Part 1: Meteorological Confirmation System for Measuring Equipment. This replaces thecancelled MIL-STD-45662A.2.3 U.S. Government Publications:Available from DODSSP, Subscription Services Desk, Building 4D, 700 Robbins Avenue,Philadelphia, PA 19111-5094.MIL-C-7024 Type II, Military Specification.

19、Calibration fluid for Aircraft Fuel SystemsComponentsMIL-L-6081 Grade 1010, Military Specification. Preservative Oil2.4 Terminology:Use the following equalities for the purposes of this document, unless stated otherwise.MIL-C-7024 Type II = Characteristics of this test fluid simulates jet fuel with

20、less flammabilityhazard.PHR = Pounds Per Hour. Units for flow measurement. Recommended.PPH = Another designation for flow units still in use. Not recommended for newdocuments.PSIG = Pounds per Square Inch Gauge. Units for pressure measurement._SAE INTERNATIONAL ARP4865A Page 2 of 31Copyright SAE Int

21、ernational Provided by IHS under license with SAENot for ResaleNo reproduction or networking permitted without license from IHS-,-,-2.4 (Continued):QD = Quick Disconnect. This two part device allows for a single action hydraulicconnection and disconnection between the test stand and UUT. The firstpa

22、rt called, the inlet adapter, is attached to the UUT to protect the inletsupply section of the nozzle. The opposing end of inlet adapter theninserts into the companion portion of the QD that is attached to the testequipment.SCFM = Standard Cubic Feet per Minute. Volumetric rate of airflow.UUT = Unit

23、 Under Test or the nozzle under test.3. TEST CONDITIONS:3.1 Test Fluid:Standard test fluid for aerospace manufacturers is MIL-C-7024 Type II. This is also known asStoddard solvent. Experience has shown that MIL-C-7024 Type II purchased from a singlesupply source will maintain stable properties. Howe

24、ver, when purchased from multiple sources,these fluid properties can vary several percent. In comparing fuel property data taken fromdifferent sources, the differences must be taken into consideration. The flow measuringinstrument calibration must account for the correct density and viscosity for th

25、e MIL-C-7024Type II used or an equivalent fluid matching the MIL-C-7024 Type II properties.The use of test fluids other than MIL-C-7024 Type II, such as actual jet fuels, is notrecommended. The wide variance in fuel properties precludes convenient correlation of test datawith other testing facilitie

26、s. The use of jet fuels for fuel nozzle testing is also more hazardous,requiring more stringent safety considerations.3.2 Filtration:The minimum acceptance Beta ratio for MIL-C-7024-II filtration systems shall be as shown inEquation 1:6111522075/= (Eq.1)See Appendix A.3.3 Fuel Contamination Testing:

27、The acceptance level shall conform to the requirement MIL-C-7024 Type II fluid. Therecommended contaminant testing method is the International Standards Organization SolidContaminant Code (ISOSCC). The recommended ISOSCC rating acceptance level for all fuelnozzle test stands is 16/13 (see Appendix B

28、). It is recommended that the fluid contaminant levelbe checked at intervals of 60 days._SAE INTERNATIONAL ARP4865A Page 3 of 31Copyright SAE International Provided by IHS under license with SAENot for ResaleNo reproduction or networking permitted without license from IHS-,-,-3.4 Temperature:3.4.1 F

29、uel: The calibration fluid shall normally be maintained at a temperature of 80 F (26.7 C)2 F (1.1 C) measured at a point near as practical to the flow measurement device and notcloser than 10 diameters from the static pressure measuring tap. Deviation from this range isallowed only if the measuremen

30、t system contains corrections for the mass flow errors due tospecific gravity and viscosity variations with temperature.3.4.2 Air: The air shall be maintained at a temperature of 50 to 95 F (10 to 35 C) measured at apoint not closer than 10 diameters from the static pressure measuring tap. The air s

31、upply shallbe clean and dry with a dew point of 40 F (22 C) or less.4. EQUIPMENT ACCURACY:4.1 Pressure Measurement:The pressure measurement equipment shall be accurate to within 0.5% OF READING for theUUT (See Appendix C).4.2 Pressure Sensing:The pressure measuring taps shall indicate true static pr

32、essure at a point as close as practical tothe UUT inlet in a tube having a minimum internal diameter equal to the fitting to which it isattached. The pressure tap should be located within 6 in of parallel height from the pressuregauge reference plane. Establish the spray chamber height, with the UUT

33、 installed in the fixture.If this is not possible a calibration must be performed to allow for positive or negative headpressure.4.2.1 Measuring Sections: Static pressure can be measured with a pressure measuring sectiondesigned such that the pressure sensing passage is small relative to the diamete

34、r of the flowpassage and the pressure is sensed in the boundary layer of the fluid during normal operation. The internal diameter must be large enough to assure a maximum velocity of no more than20 ft/s (6.096 m/s) at the flow condition for fuel or Mach 0.2 for air such that the dynamicpressure comp

35、onent is minimized. The pressure tap is placed a minimum of 10 diametersdownstream from the supply fitting connection and 2 diameters upstream from the exit. SeeFigure 1 for fuel flow and Figure 2 for airflow.4.2.2 Quick Disconnects (QD): If a QD is used during performance testing, the center check

36、valveshould be removed. The inlet adapter must have at least the same internal diameter as theUUT fitting. Periodic leakage checks should be performed on the inlet adapter and QD.4.2.3 Calibration of QDs: If the test setup does not allow removal of the center check valve, then acalibration must be p

37、erformed to establish a correlation between pressure drop and flow rate._SAE INTERNATIONAL ARP4865A Page 4 of 31Copyright SAE International Provided by IHS under license with SAENot for ResaleNo reproduction or networking permitted without license from IHS-,-,-FIGURE 1 - Typical Fuel Flow Measuring

38、Section_SAE INTERNATIONAL ARP4865A Page 5 of 31Copyright SAE International Provided by IHS under license with SAENot for ResaleNo reproduction or networking permitted without license from IHS-,-,-FIGURE 2 - Typical Airflow Measuring Section_SAE INTERNATIONAL ARP4865A Page 6 of 31Copyright SAE Intern

39、ational Provided by IHS under license with SAENot for ResaleNo reproduction or networking permitted without license from IHS-,-,-4.2.4 Plenum Measurement (AIR): Static pressure can be measured in a Plenum chamber whichprovides the working fluid to the test article. This is done with a small pressure

40、 sensing passageat the periphery of the chamber. The internal volume must be large enough to assure a Plenumfeed of the test fluid to the test article. The maximum velocity at the inlet of the Plenum shouldbe no more than Mach 0.2 at the flow condition and no portion of the Plenum cross section shal

41、lbe smaller than the inlet. See Figure 3. The general shape of the air box is not critical if theserequirements are met.4.3 Pressure or Flow Setting:Pressure setting shall be within 1% OF READING at all test points of the UUT. Whenapplicable, flow setting shall be within 2.0% OF READING.4.4 Fuel Flo

42、w Measurement:The flow measurement shall be accurate to within 0.5% OF READING at all test points of theUUT.4.5 Airflow Measurement:The flow measurement equipment shall be accurate to within 1.0% OF READING at all testpoints.4.6 Spray Angle Measurements:The angle measuring device shall be accurate t

43、o within 1 OF READING for overall angle and/or1% OF READING for linear width. The majority of sprays are conical in nature as they exit theorifice of the UUT. The spray angle is measured at a point specified by the engine and nozzlemanufacturer. The spray cone is viewed as a two dimensional plane us

44、ing simple fixturing andmeasuring devices. The measured data can be either an angle and skew or linear dimensionsfrom centerline.4.6.1 Spray Angle Test Fixturing: Test fixturing is normally mounted on or integral to spray chamberswhich collect the spray dispensed, evacuate the fumes, and return the

45、test fluid to the teststand. The spray chamber and fixturing allow the spray to exit downward in a vertical plane andis viewed by the operator through a transparent, nondistorting viewing aperture. Where sprayangle measurement or patternation is required, the UUT shall be mounted in a suitable fixtu

46、resuch that, when installed in the measuring device, the UUT tip center-line is held within0.025 in (0.635 mm) of the angle device or patternator centerline. See Figures 4 and 5. Thetheoretical spray cone apex, as defined by the appropriate control document, shall also beplaced at the measurement device reference plane, as defined by the device assemblydrawing, within 0.025 in (0.635 mm). It is essential to establish the theoretical spray coneapex and ensure the fixture dimensions are correct when installed in the spray angle devicebeing us