SAE ARP 1839-2015 A Guide to Aircraft Turbine Engine Vibration Monitoring Systems.pdf

《SAE ARP 1839-2015 A Guide to Aircraft Turbine Engine Vibration Monitoring Systems.pdf》由会员分享，可在线阅读，更多相关《SAE ARP 1839-2015 A Guide to Aircraft Turbine Engine Vibration Monitoring Systems.pdf（46页珍藏版）》请在麦多课文档分享上搜索。

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 2015 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 feedbackon this Technical Report, please visithttp:/www.sae.org/technical/standards/ARP1839AEROSPACERECOMMENDED PRACTICEARP1839Issued 2015-12A Guide to Aircraft Turbine Engine V

5、ibration Monitoring SystemsRATIONALEThis edition updates content, includes appropriate content from AS8054 and raises AIR1839 to an ARP in accordance with E-32 committee decision.TABLE OF CONTENTS1. SCOPE 4 1.1 Purpose. 4 2. REFERENCES 4 2.1 Applicable Documents 4 2.1.1 SAE Publications. 4 2.1.2 FAR

6、 Publications. 4 2.2 Other Documents 5 2.3 Terminology and Abbreviations 5 3. INTRODUCTION. 6 4. HISTORY 9 5. EVM SYSTEM FUNCTIONALITY. 9 6. SYSTEM DESIGN. 10 6.1 Signal Source 11 6.1.1 Transducer Locations 11 6.1.2 Transducer Mounting 11 6.1.3 Transducer Characteristics . 12 6.2 Signal Transmission

7、 18 6.2.1 Transmission Line Check 18 6.2.2 System Partitioning . 19 6.2.3 Cabling Consideration. 20 6.3 Signal Processing . 22 6.3.1 Signal Conditioning . 22 6.3.2 Signal Integration 23 6.3.3 Bandwidth Selection 23 6.3.4 Output Formats . 25 6.3.5 Warning Functions 25 6.3.6 BITE/Self-Test. 25 SAE INT

8、ERNATIONAL ARP1839 Page 2 of 467. VIBRATION ANALYSIS TECHNIQUES (FOR MAINTENANCE PURPOSES) 25 7.1 Time Domain Analysis 25 7.1.1 Simple parameters:. 25 7.2 Frequency Domain Analysis . 26 7.2.1 Filter Techniques. 28 7.3 Pattern Matching . 29 8. ROTOR TRIM BALANCING . 30 8.1 Phase Reference 30 8.2 Phas

9、e Measurement Considerations 31 8.3 Data Collection 36 8.3.1 In Flight Data Collection 36 8.3.2 Ground Running 37 8.4 Balance Coefficients . 37 8.5 Balance Calculations. 39 8.6 Balance Implementation Example 39 9. RESPONSIBILITIES . 39 9.1 Participants . 40 9.1.1 The End User 40 9.1.2 The Airframe M

10、anufacturer . 40 9.1.3 The Engine (and/or Engine Accessory) Manufacturer 40 9.1.4 The EVM Equipment Supplier. 40 9.1.5 Considerations for EVM 40 10. REGULATORY REQUIREMENTS . 41 10.1 Civil 41 10.2 Military. 41 11. HUMAN FACTORS. 41 11.1 Display and Human Interface Considerations 41 12. THE ECONOMICS

11、 OF A VIBRATION MONITORING SYSTEM . 42 13. USAGE 42 13.1 Flight Crew 42 13.2 Maintenance Personnel 43 14. MAINTENANCE BENEFITS . 43 14.1 On Condition Maintenance . 43 14.2 Engine Trim Balance. 43 14.3 Detailed Diagnostics . 44 14.4 Predictive Analysis 44 15. SUMMARY 45 16. NOTES 46 16.1 Revision Ind

12、icator 46 Figure 1 A typical schematic of an engine vibration monitoring system (EVM) 7 Figure 2 Typical EVM system components. 8 Figure 3 Considerations for EVM 10 Figure 4 Relationship between displacement, velocity and acceleration at constant velocity of 1 inch/second. 13 Figure 5 Cross section

13、of a typical EVM compression type piezoelectric accelerometer. 14 Figure 6 Wide band output of a typical accelerometer 15 Figure 7 Surface mounted accelerometer with connector 16 Figure 8 Surface mounted accelerometer with integral cable. 17 Figure 9 Internal type accelerometer 17 Figure 10 Surface

14、mounted dual element accelerometer . 18 Figure 11 Typical differential measurement chain 20 Figure 12 Low noise cable 21 SAE INTERNATIONAL ARP1839 Page 3 of 46Figure 13 Typical vibration snapshot at an operating condition showing effect of measuring in Gs, IPS and MILS. 24 Figure 14 Transformation f

15、rom a time signal in the frequency domain. 27 Figure 15 Typical engine run up vibration spectrum cause and effects 28 Figure 16 Ideal tachometer pulse and vibration phase reference signals. 32 Figure 17 Tachometer signals illustrating rotor vibration induced ripple. 33 Figure 18 Phase relationships

16、among displacement, velocity, and acceleration 34 Figure 19 Phase lag versus phase lead 35 Table 1 Possible measurement relationships among displacement, velocity, and acceleration . 35 SAE INTERNATIONAL ARP1839 Page 4 of 461. SCOPEThis Aerospace Recommended Practice (ARP) is a general overview of t

17、ypical airborne engine vibration monitoring (EVM) systems applicable to fixed or rotary wing aircraft applications, with an emphasis on system design considerations.It describes EVM systems currently in use and future trends in EVM development. The broader scope of Health and Usage Monitoring System

18、s, (HUMS) is covered in SAE documents AS5391, AS5392, AS5393, AS5394, AS5395, AIR4174. This ARP also contains the essential elements of AS8054 which remain relevant and which have not been incorporated into Original Equipment Manufacturers (OEM) specifications.1.1 PurposeThe purpose of this ARP is t

19、o provide information and guidance for the selection, installation, and use of EVM systems and their elements. This ARP is not intended as a legal document but only as a technical guide.2. REFERENCES2.1 Applicable DocumentsThe following publications form a part of this document to the extent specifi

20、ed 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. N

21、othing in this document, however, supersedes applicable laws and regulations unless a specific exemption has been obtained.2.1.1 SAE PublicationsAvailable from SAE International, 400 Commonwealth Drive, Warrendale, PA 15096-0001, Tel: 877-606-7323 (inside USA and Canada) or +1 724-776-4970 (outside

22、USA), www.sae.org.ARP1587 Aircraft Gas Turbine Engine Health Management System GuideAIR1828 Guide to Engine Lubrication System MonitoringAIR1871 Lessons Learned from Developing, Implementing, and Operating a Health Management System for Propulsion and Drive Train SystemsAIR4061 Guidelines for Integr

23、ating Typical Engine Health Management Functions within Aircraft SystemsAIR4174 A Guide to Aircraft Power Train MonitoringAIR4175 A Guide to the Development of a Ground Station for Engine Condition MonitoringARP4176 Determination of Costs and Benefits from Implementing an Engine Health Management Sy

24、stemAS5391 Health and Usage Monitoring System Accelerometer Interface SpecificationAS8054 Airborne Engine Vibration Monitoring (EVM) System, Guidelines for Performance Standard For (This document has been cancelled. Remaining valid content has been included in this ARP, OEM specifications and indust

25、ry standards)2.1.2 FAR PublicationsAvailable from www.acquisition.gov/far.FAR 14 CFR 25.1305 (d) (3) Airworthiness Standards: Transport Category Airplanes - Powerplant InstrumentsSAE INTERNATIONAL ARP1839 Page 5 of 462.2 Other Documents AISI321, Stainless SteelANSI S2.41-1985, Mechanical Vibration o

26、f Large Rotating Machines with Speed Range from 10 - 200 RPSASME PTC 19.1-2005, Test UncertaintyAV-E-8593H, Engine Performance SpecificationHewlett Packard Application Note 243, The Fundamentals of Signal AnalysisISO 7919: Evaluation of Machine Vibration on Rotating PartsISO 10816-1; Mechanical vibr

27、ation - Evaluation of Machine Vibration by Measurements on non-rotating PartsRTCA DO-160 (latest revision), Environmental Conditions and Test Procedures for Airborne EquipmentRTCA DO-178 (latest revision), Software Consideration in Airborne Systems and Equipment CertificationRTCA DO-254 (latest revi

28、sion), Design Assurance Guidance for Airborne Electronic Hardware2.3 Terminology and AbbreviationsACARS: Aircraft Communications Addressing and Reporting SystemsACCELERATION, VIBRATION: The response of a mass to an applied force, usually stated as a ratio, g, of the acceleration with respect to G, t

29、he acceleration due to gravity. The first integral of acceleration with respect to time is velocity and the second integral yields displacement. Vibration amplitude may be expressed in units of acceleration, velocity, or displacement.ACCELEROMETER: A device for measuring acceleration. Most accelerom

30、eters used for EVM employ piezoelectric sensing elements, which generate an electrical charge signal proportional in amplitude, frequency, and phase to the applied acceleration. Devices with internal signal conditioning are also available. These provide voltage or current outputs proportional to acc

31、eleration or velocity.DAL: Design Assurance LevelDATA BUS: A means of transferring information in digital format. Various data bus standards such as ARINC 429 and RS-232 are widely used in monitoring systems. If the EVM is engine mounted then many other bus standards may be used both for transfer of

32、 data to the EEC and to the airframe system. AFDX, and CAN are two examples.DISPLACEMENT, VIBRATION: Vibration amplitude may be expressed in units of displacement: inches, millimeters, or mils (0.001 inch). Displacement is the second integral of acceleration with respect to time. Both peak and zero-

33、to-peak-to-peak amplitude units are in use.EEC: Electronic Engine Control: An avionics unit used to control the engine (see also FADEC)EHM: Engine Health Monitoring (Management) EMI: Electro-Magnetic Interference EVM: Engine Vibration MonitoringEVMS: Engine Vibration Monitoring SystemFADEC: Full Aut

34、hority Digital Engine Control: An avionics unit used to control the engine (see also EEC).SAE INTERNATIONAL ARP1839 Page 6 of 46FAR: Federal Aviation RequirementFREQUENCY RESPONSE: The amplitude response of a spring-mass system as a function of response frequency.NATURAL FREQUENCY: The natural frequ

35、ency of a spring-mass system is proportional to the square root of the ratio of the spring constant to the mass for a single degree of freedom system.OCM: On-Condition Maintenance: Maintenance only carried out when the condition of the engine (equipment) requires it as opposed to hard-time where mai

36、ntenance is carried out at predetermined intervals. The intervals are typically in terms of time (e.g., flight hours, elapsed calendar time) or flight cycles.ONCE-PER-REV: A colloquial expression meaning either a signal that is provided once per engine rotor revolution or the rotational speed of a p

37、articular engine rotor.PHASE REFERENCE SIGNAL: A signal, usually electrical, provided on some engines, which indicates when a particular point on the rotor passes a reference point on the engine case. The reference signal, which is often superimposed on the tachometer signal, is useful for dynamical

38、ly balancing the rotor.RCC: Remote Charge ConverterRESONANCE, MECHANICAL: The condition that occurs when the frequency of an exciting force is synchronous with a natural frequency of a spring-mass system.RMS: Root Mean Square: An average of a set of values that is obtained by taking the square root

39、of the arithmetic mean of the squares of the individual values. Vibration amplitude expressed as rms is proportional to the total vibration energy in the frequency band of interest but independent of the frequency distribution within that band.ROTOR ORDERS: The rotational speed of the lowest speed e

40、ngine rotor is conventionally identified as N1, the next highest as N2, and the next highest, if present, as N3.SPECTRUM: An array of the frequency component amplitudes of a signal arranged in order of frequency.VELOCITY, VIBRATION: Vibration amplitude may be expressed in units of velocity; inches p

41、er second or millimeters per second. Velocity is the first integral of acceleration with respect to time.ZERO-TO-PEAK and PEAK-TO-PEAK: Vibration amplitude measurement that has a precise meaning only for simple harmonic motion, i.e., single frequency, vibration. Peak is the maximum amplitude of a si

42、nusoidal function with respect to a zero reference; peak-to-peak is the total amplitude measured from maximum to minimum.3. INTRODUCTIONA complete Engine Vibration Monitoring (EVM) system includes all the equipment, data, and procedures used for monitoring and analyzing aircraft turbine engine vibra

43、tion and engine driven equipment. A complete comprehensive EVM system is shown in Figure 1 and its component parts in Figure 2. EVM may be one part of an engine condition monitoring system that monitors a number of engine parameters, or it may be a stand-alone system. A distinction is usually made b

44、etween that part of the system dedicated to monitoring engine functions on board an aircraft and that part used for ground based analysis and monitoring. The on-board portion is commonly called an airborne engine vibration monitoring (EVM) system, and it is this part of the complete system that is d

45、escribed in this Aerospace Recommended Practice (ARP). The ground based portion is described in SAE document AIR4175.The primary moving parts of all turbine engines are the rotors, shafts and their bearings. When operating, the engine rotors spin at relatively high speed within the engine case. Elem

46、ents of these rotors, particularly fan, compressor, and turbine blades, are subject to wear and damage, some types of which may unbalance the affected rotor. Increased rotor unbalance causes increased cyclic stress on the structure and on the associated rotor bearings. In addition, the cyclic forces

47、 due to unbalance may induce destructive vibration in other engine parts and accessories. Small amounts of rotor unbalance are always present; large amounts usually cannot be tolerated for extended periods of operation without risk of fatigue by certain engine components. In extreme unbalance events

48、, continued operation may not be safely possible.SAE INTERNATIONAL ARP1839 Page 7 of 46EngineGround based- Trending- Analysis- Diagnostics- Prognostics- MaintenanceFlight DataRecorderCentralMaintenanceComputerCockpitDisplay /AnnunciationFADECAircraft to GroundCommunicationsSystemsSignal ProcessingPr

49、ogram StorageData StorageCommunicationsVibration Transducer(s) Shaft Azimuth SensorsNOTE: A complete system includes human interaction in the loop and therefore human factors must be considered insystem design.Figure 1 - A typical schematic of an engine vibration monitoring system (EVM)SAE INTERNATIONAL ARP1839 Page 8 of 46EECEMUEECEECEVMRCCEVM1 System per Engine1 System per Engineor1 System per 2 Engines1 System per Engineor1