1、Gas Turbine Aircraft EnginesPerformance Test CodesAN AMERICAN NATIONAL STANDARDASME PTC 55-2013ASME PTC 55-2013Gas TurbineAircraft EnginesPerformance Test CodesAN AMERICAN NATIONAL STANDARDTwo Park Avenue New York, NY 10016 USADate of Issuance: November 8, 2013This Code will be revised when the Soci
2、ety approves the issuance of a new edition. There will be noaddenda issued to PTC 55-2013.ASME issues written replies to inquiries concerning interpretations of technical aspects of thisdocument. Periodically certain actions of the ASME PTC Committee may be published as Code Cases.Code Cases and int
3、erpretations are published on the ASME Web site under the Committee Pages athttp:/cstools.asme.org/ as they are issued.Errata to codes and standards may be posted on the ASME Web site under the Committee Pages toprovide corrections to incorrectly published items, or to correct typographical or gramm
4、atical errorsin codes and standards. Such errata shall be used on the date posted.The Committee Pages can be found at http:/cstools.asme.org/. There is an option available toautomatically receive an e-mail notification when errata are posted to a particular code or standard.This option can be found
5、on the appropriate Committee Page after selecting “Errata” in the “PublicationInformation” section.ASME is the registered trademark of The American Society of Mechanical Engineers.This code or standard was developed under procedures accredited as meeting the criteria for American NationalStandards.
6、The Standards Committee that approved the code or standard was balanced to assure that individuals fromcompetent and concerned interests have had an opportunity to participate. The proposed code or standard was madeavailable for public review and comment that provides an opportunity for additional p
7、ublic input from industry, academia,regulatory agencies, and the public-at-large.ASME does not “approve,” “rate,” or “endorse” any item, construction, proprietary device, or activity.ASME does not take any position with respect to the validity of any patent rights asserted in connection with anyitem
8、s mentioned in this document, and does not undertake to insure anyone utilizing a standard against liability forinfringement of any applicable letters patent, nor assumes any such liability. Users of a code or standard are expresslyadvised that determination of the validity of any such patent rights
9、, and the risk of infringement of such rights, isentirely their own responsibility.Participation by federal agency representative(s) or person(s) affiliated with industry is not to be interpreted asgovernment or industry endorsement of this code or standard.ASME accepts responsibility for only those
10、 interpretations of this document issued in accordance with the establishedASME procedures and policies, which precludes the issuance of interpretations by individuals.No part of this document may be reproduced in any form,in an electronic retrieval system or otherwise,without the prior written perm
11、ission of the publisher.The American Society of Mechanical EngineersTwo Park Avenue, New York, NY 10016-5990Copyright 2013 byTHE AMERICAN SOCIETY OF MECHANICAL ENGINEERSAll rights reservedPrinted in U.S.A.CONTENTSNotice . vForeword viCommittee Roster . viiCorrespondence With the PTC Committee viiiIn
12、troduction . ixSection 1 Object and Scope . 11-1 Object . 11-2 Scope 11-3 Typical Overall Performance Uncertainty . 11-4 Units of Measurement 2Section 2 Definitions and Descriptions of Terms 32-1 Equipment Definitions . 32-2 Thrust and Power Definitions 32-3 Test Parameter Definitions . 42-4 Test Fa
13、cility Definitions 42-5 Nomenclature 4Section 3 Guiding Principles. 83-1 General Agreements Before Test 83-2 Preparation for Test 93-3 Operation of Test 93-4 Records 103-5 Test Cell Design . 11Section 4 Instruments and Methods of Measurement 174-1 Calibration of Instruments and Apparatus 174-2 Measu
14、rement of Scale Force 174-3 Determination of Shaft Power Output 174-4 Measurement of Gas Flows . 184-5 Fuel Flow 204-6 Measurement of Pressure . 234-7 Measurement of Temperature . 234-8 Measurement of Humidity . 244-9 Measurement of Vibration 24Section 5 Computation of Results 265-1 General Data Red
15、uction 265-2 Calculation of Fuel/Air Ratio 265-3 Calculation of High Pressure Turbine Inlet Temperature (T4.1) . 265-4 Computation of Thrust (Turbofan, Turbojet) From Scale Force . 265-5 Computation of Power (Turboprop, Turboshaft) . 285-6 Computation of Brake Specific Fuel Consumption 295-7 Correct
16、ion of Test Results to Specified or Standard Conditions 30Section 6 Test Report Requirements 316-1 Overview 316-2 Title Page 316-3 Table of Contents 316-4 Body 31iii6-5 Summary 326-6 Appendices 32Section 7 Uncertainty . 337-1 Validity of Results . 337-2 Reporting of Results . 337-3 Objectives . 337-
17、4 Definitions . 337-5 Uncertainty Calculations . 337-6 Uncertainty Limits . 33Figures2-5.1-1 Various Cross Sections of Turbofan Engines . 73-5.2.2.1-1 Test Cell Configuration: “L” Type 133-5.2.2.2-1 Test Cell Configuration: “U” Type 133-5.2.2.3-1 Test Cell Configuration: Folded Inlet Type 143-5.2.2.
18、4-1 Outdoor Test Cell 143-5.2.2.5-1 Typical Altitude Test Cell 153-5.2.2.6-1 Typical Ram Test Cell 163-5.3.1-1 Typical Turboshaft Test Cell Setup 164-4.2.1-1 Cross Section of Bypass Gas Turbine . 204-6.1-1 Combo Rake Pressure Rakes . 235-4.3.5-1 Thrust Control Volume . 29Tables1-3-1 Overall Uncertai
19、nty 22-5-1 Symbols and Definitions . 53-3.2.1-1 Maximum Indicated Variation in Test Conditions . 104-5.1.2-1 ARP 4990 References . 224-9.4-1 Vibration Limits . 257-5-1 Maximum Permissible Overall Uncertainty at Test Conditions . 33Mandatory AppendixI Orifice Meters Installed in Pipes 2 in. (51 mm) I
20、nside Diameter (I.D.)or Less 35Nonmandatory AppendicesA Conversion Factors . 41B Sample Core Flow Calculations 43C Sample Liquid Fuel Calculations . 45D Energy Transfer 48E Uncertainty Analysis Calculations 51F Measurement of Emission 56G Transient Testing . 61H Bibliography . 62ivNOTICEAll Performa
21、nce Test Codes must adhere to the requirements of ASME PTC 1, GeneralInstructions. The following information is based on that document and is included here foremphasis and for the convenience of the user of the Code. It is expected that the Code user isfully cognizant of Sections 1 and 3 of ASME PTC
22、 1 and has read them prior to applying thisCode.ASME Performance Test Codes provide test procedures that yield results of the highest levelof accuracy consistent with the best engineering knowledge and practice currently available.They were developed by balanced committees representing all concerned
23、 interests and specifyprocedures, instrumentation, equipment-operating requirements, calculation methods, and uncer-tainty analysis.When tests are run in accordance with a Code, the test results themselves, without adjustmentfor uncertainty, yield the best available indication of the actual performa
24、nce of the tested equip-ment. ASME Performance Test Codes do not specify means to compare those results to contractualguarantees. Therefore, it is recommended that the parties to a commercial test agree before startingthe test and preferably before signing the contract on the method to be used for c
25、omparing thetest results to the contractual guarantees. It is beyond the scope of any Code to determine orinterpret how such comparisons shall be made.vFOREWORDThe Performance Test Code Committee No. 55 was established to develop a test code on gasturbine aircraft engines. This Code was published in
26、 2013.The Committee consists of manufacturers, consultants, users such as members of the U.S. ArmedForces, and other governmental agencies involved both in the development of specifications ofgas turbines and testing of these engines, airlines, and other aviation companies involved inaviation gas tu
27、rbines. These groups of gas turbine engineers have taken into account the develop-ment of the many different technologies that are involved in aircraft gas turbine technology. ThePTC 55 Code addresses the increasingly important topic of aircraft emissions and the need forhigh speed measurements to d
28、ocument dynamic phenomena such as combustion instability,forced vibrations, and aerodynamic flutter. The importance of understanding and documentingthe uncertainty of the measurements used to characterize gas turbine performance is alsoaddressed.This Code was approved as an American National Standar
29、d, by the ANSI Board of StandardsReview, on July 29, 2013.viASME PTC COMMITTEEPerformance Test Codes(The following is the roster of the Committee at the time of approval of this Code.)STANDARDS COMMITTEE OFFICERSJ. R. Friedman, ChairJ. W. Milton, Vice ChairJ. H. Karian, SecretarySTANDARDS COMMITTEE
30、PERSONNELP. G. Albert, General Electric Co.R. P. Allen, ConsultantJ. M. Burns, Burns EngineeringW. C. Campbell, Southern Company ServicesM. J. Dooley, Sigma Energy Solutions, Inc.J. R. Friedman, Siemens Energy, Inc.G. J. Gerber, ConsultantP. M. Gerhart, University of EvansvilleT. C. Heil, The Babcoc
31、k however, they shouldnot contain proprietary names or information.Requests that are not in this format will be rewritten in this format by the Committee priorto being answered, which may inadvertently change the intent of the original request.ASME procedures provide for reconsideration of any inter
32、pretation when or if additionalinformation that might affect an interpretation is available. Further, persons aggrieved by aninterpretation may appeal to the cognizant ASME Committee or Subcommittee. ASME does not“approve,” “certify,” “rate,” or “endorse” any item, construction, proprietary device,
33、or activity.Attending Committee Meetings. The PTC Standards Committee and PTC Committees holdmeetings regularly, which are open to the public. Persons wishing to attend any meeting shouldcontact the Secretary of the PTC Committee.viiiINTRODUCTIONThis Test Code provides direction and rules for the co
34、nduct and reporting of test(s) results forpropulsion gas turbines, hereafter referred to as gas turbine aircraft engines. This Code providesa common set of test procedures that will yield results of the highest level of accuracy and fidelity,consistent with the best engineering knowledge and practic
35、e in the gas turbine industry.ASME PTC 1, General Instructions; ASME PTC 2, Definitions and Values; ASME B133.1, GasTurbine Terminology; and ASME PTC 22, Performance Test Code on Gas Turbines were used asguides in the preparation of this Code and are recommended as references when using this Code.Th
36、e performance testing of a gas turbine aircraft engine is complicated because they come inall sorts of configurations from turbines with single spools to turbines with three spools. It isimportant in every case to determine the type of engine from a pure-jet, to a fan-jet, to a prop-jet.In addition,
37、 the wide range of test missions from standard production, sea level acceptancetesting to heavily instrumented altitude tank development testing of new designs require theuse of different test cells that are described in this Performance Test Code. The test data in virtuallyevery case needs correcti
38、on for the differences between the test and specified conditions. Thetechniques used to do so are based upon the rules of fluid-dynamic similarity. Some familiaritywith this fundamental technique will be a significant aid to the users of PTC 55.Uncertainty analysis plays a very important role in gas
39、 turbine engine testing, from the designof the test to interpretation of the test reslults. In all but the very simplest of cases the developmentof an analytical formulation, i.e., in simple equation form, for overall uncertainty computationis formidable. The test uncertainty will always be increasi
40、ngly more complex to evaluate withthe complexity of the gas turbine configuration, and by the very nature of the test will be afunction of engine thermodynamic cycle and model employed to calculate the engine performance.ixINTENTIONALLY LEFT BLANKxASME PTC 55-2013GAS TURBINE AIRCRAFT ENGINESSection
41、1Object and Scope1-1 OBJECTThe objective of this Code is to recommend the meth-odology for determining the performance of thrust andpower-producing gas turbine aircraft engines at test con-ditions and to correct these results to standard or speci-fied operating conditions. In order to meet the state
42、dobjective the Code will define and standardize the meth-ods used for conducting the tests, calculating the results,and making the corrections.1-2 SCOPEThis Code covers the performance testing of gas tur-bine aircraft engines at steady-state conditions. ThisCode applies to turbojet, turbofan, turbos
43、haft, andturboprop engines. Additionally, the Code will encom-pass ram and/or altitude test conditions, including sealevel static test conditions.The primary test results include(a) Thrust or Power(b) Engine Component Performance (operating lines,stall margin, efficiency)(c) Auxiliary Power Extracti
44、on(d) Core Fuel Flow(e) Specific Fuel Consumption(f) Total Engine Airflow(g) Core Airflow(h) Bypass Airflow(i) Bleed Airflow(j) Vibration LevelsIn addition, oftentimes military and commercial con-tracts include specifications for the following secondaryparameters:(k) Pressures and Temperatures(l) Hu
45、midity(m) Rotor Speeds(n) Engine Pressure Ratio(o) Oil Flow(p) Variable Geometry Settings1(q) Noise and Emissions(r) Engine Control SignalsBrief guidance, procedures, and recommendations areincluded to address the measurement of these parame-ters. More detailed procedures and regulations for thesear
46、e found elsewhere.This Code is only applicable to measuring perform-ance when the engine is installed in a test facility. ThisCode is not applicable to measuring performance whenthe engine is installed in an aircraft, and it does notaddress engine-specific limits and margins. The Codedoes not cover
47、ground-based mechanical or electricalpower-generating gas turbines, which is the subject ofPTC 22. This Code is not sufficient for certification orqualification of engines under development, nor is itintended for determination of research data. While thisCode does not cover the requirements for tran
48、sient test-ing, it is recognized that transient testing may berequired to meet some limited contractual requirements.Information on transient testing is provided herein tosupport a comprehensive test program.1-3 TYPICAL OVERALL PERFORMANCEUNCERTAINTYTest uncertainty is an estimate of the limit of er
49、ror ofa tests result. It is the interval about a result that containsthe true value within a given probability, or level ofconfidence. It is based on calculations utilizing statistics,instrumentation information, calculation procedure, andactual test data. PTC 19.1 is the Performance Test CodeSupplement that covers general procedures for calcula-tion of test uncertainty. Performance Test Codes main-tain a 95% level of confidence for which uncertaintyis calculated as their standard. This confidence leveltherefore represents a 95% chance that the uncertaintyinterval contains the true
