AGMA-93FTM11-1993.pdf
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1、93FTM11 The RelativeNoise Levels of ParallelAxis Gear Sets with Various ContactRatiosand Gear Tooth Forms by: R. J. Drago, J. W. Lenski and R. H. Spencer, Boeing Defense and Space Group; M. Valco, Lewis ResearchCenter, U.S. Army; E Oswald, Lewis research Center, NASA AmericanGearManufacturersAssocia
2、tion II TECHNICALPAPER Copyright American Gear Manufacturers Association Provided by IHS under license with AGMA Licensee=IHS Employees/1111111001, User=Wing, Bernie Not for Resale, 04/18/2007 11:20:41 MDTNo reproduction or networking permitted without license from IHS -,-,- he Relative Noise Levels
3、 of Parallel Axis Gears Sets with Various Contact ratios and Gear Tooth Forms R. J. Drago, J. W. Lenski and R. H. Spencer, Boeing Defense and Space Group; M. Valeo, Lewis Research Center, U.S. Army; and F. Oswald, Lewis Research Center, NASA The statements andopinions contained herein arethose ofthe
4、 authorandshould notbe construed as anofficial action or opinion of the American Gear Manufacturers Association. ABSTRACT: The real noise reduction benefits which may be obtained through the useof one gear tooth form as compared to another is an important design parameter for any geared system, espe
5、cially for helicopters in which both weight and reliability are very important factors. This paper describes the design and testing of nine sets of gears which are as identical as possible except for their basic tooth geometry. Noise measurements were made atvarious combinations of load and speed fo
6、r each gear set so that direct comparisons could be made. The resultant datawas analyzed so that valid conclusions could be drawn and interpreted for design use. Copyright1993 American Gear ManufacturersAssociation 1500 King Street, Suite 201 Alexandria,Vtrginia, 22314 October, 1993 ISBN:1-55589-623
7、-5 Copyright American Gear Manufacturers Association Provided by IHS under license with AGMA Licensee=IHS Employees/1111111001, User=Wing, Bernie Not for Resale, 04/18/2007 11:20:41 MDTNo reproduction or networking permitted without license from IHS -,-,- The RelativeNoiseLevelsof ParallelAxisGear S
8、ets WithVariousContactRatiosandGear ToothForms By Raymond ,I.Drago,PE AssociateTechnicalFellow BoeingHelicopters RobertH.SpencerJosephW.Lenski,Jr. StaffEngineerAssociateTechnicalFellow BoeingHelicoptersBoeingHelicopters MarkJ. ValcoFredB. Oswald AerospaceEngineerResearch Engineer LewisResearchCenter
9、/U. S.ArmyLewisResearchCenterNASA I INTRODUCTIONmodifiedcontactratiosandthe geartoothform, separatelyand in combination,for spur and helical The problem of gear noise in helicopter transmissionsgears,on the noiselevelsproducedby otherwise is ever present.The main excitingforces whichidenticalspurand
10、helicalgears.Inorderto produce this noise are the meshingforces of the gearaccomplishthis objective, a program was defined to teeth in the transmission. While this is certainly andesignappropriategears(TableI),fabricatea oversimplification,sincemanyfactorsinfluencesufficient number of test specimens
11、,and conduct the transmissionnoise aside from the gear mesh forces,testing required. the simplefactrernain._ that if the basicexciting forcesare reducedand no amplifyingfactorsareWhile a wide range of specimens is shown, they were present, the overall noise level of the system will beall configured
12、as nearly alike as practical,within the reduced,limitations imposed by manufacturingconsiderations and the test stand. Testing was conducted in a single Amongthe severalwaysin whichthe gear toothmeshgear box undercontrolledconditionswhich meshingforcesmay be reduced,two of the mostweremaintainedasne
13、arlyidenticalaspossible. directly applicableto helicopter transmissionsare theAcoustic intensity measurementswere taken with the form of the teeth and the overall contact ratio. Bothaid of a robot to insure repeatabilityof measurement approachesarequiteattractiveforanaerospacebetween gear sets and t
14、o minimize human technique applicationsince, unlikeother “treatment“methods,influence. whichare appliedwithpenaltiesto eithersystem weightor performance,theseapproacheshavethe potentialfor reducingnoise withoutcausinganyTESTGEAR DESIGN increaseinoverallsystemweightorreducing performance. In fact, bo
15、th approaches also offer theEight (8) sets of gears, four (4) spur and four (4) possibilityof.actuallyprovidingimprovedgearhelicalas listedin TableI, compatiblewith the performancein termsof longerlife,higherloadNASA Lewis gear noise test rig, were designed.Of capacity,improvedreliability,and reduce
16、dweightthe four sets of spur gears, two sets have an involute while simultaneouslyreducingnoise levels,tooth form and two utilizea nouinvolute,constant radiusofcurvaturetoothform.Allgearswere Theobjectiveof thisprogramwas to define,bydesignedinaccordancewithnormalBoeing controlled testing and actual
17、 noise measurements,theHelicopterspractice so that, except for size, they are effect of changesin the profile, face, andrepresentativeof typical helicoptergears. Copyright American Gear Manufacturers Association Provided by IHS under license with AGMA Licensee=IHS Employees/1111111001, User=Wing, Be
18、rnie Not for Resale, 04/18/2007 11:20:41 MDTNo reproduction or networking permitted without license from IHS -,-,- TableI Gear NoiseTest Matrix Contact Ratios ConfigurationToothFormTvlae ProfileFaceModifie.d 1.ConventionalInvoluteSpur1.250.001.25 Spur Baseline 2.HCR-INVInvoluteSpur2.150.002.15 3.Con
19、ventionalInvoluteHelical1.251.251.77 SingleHelicalBaseline 4.DoubleHelicalInvoluteHelical1.251.251.77 5.HCR-INVInvoluteHelical1.251.752.15 6.HCR-INVInvoluteHelical2.152.253.11 7.NIF BaselineNonInvoluteSpur1.250.01.25 8.NIF-HCRNonInvoluteSpur2.150.02.15 Figure 1 - Test Gears Copyright American Gear M
20、anufacturers Association Provided by IHS under license with AGMA Licensee=IHS Employees/1111111001, User=Wing, Bernie Not for Resale, 04/18/2007 11:20:41 MDTNo reproduction or networking permitted without license from IHS -,-,- Table II - Basic Test Gear Configuration II PinionGear Number of Teeth25
21、31 DiametralPitch, Transverse8. Center Distance3.50 Pressure Angle, Transverse25 (Std Profile Contact Ratio) 20 (High ProfileContact Ratio) Face Width (Spur recorded acoustic intensity spectra in theanalyzerfor eachnodeof thegrid;and transmitted the spectra to the computerfor storage on _disk. The a
22、constieintensityprobeconsistsof a pair of aEAr_ NmSE at_phase-matched6 mm microphonesmounted face-to- face with a 6 mm spacer. The probe has a frequency range (1 dB) of 300-10,000I-Iz.Measurementswere Figure 2 - Nasa Gear Test Rigmade at a distance of 60 mm betweenthe acoustic center of the micropho
23、nesand the gearbox top. A 20 node measurementgrid was drawn on the topThe 20 intensityspectra collectedat each operating cover of the gear box and used to insure repeatabilityconditionwereaveraged,thenmultipliedby the of the noise measurementsand to aid in avoidingradiationarea to compute an 800 lin
24、e sound power operator induced errors. The grid covers an area 228spectrum. The radiationarea was assumed to be the x 304 mm (9 x 12 in) centered on the 286 x 362 mmarea of the grid plus one additionalrow and column (11.25 x 14.25 in) top. A cutaway section of the testof elements or 0.0910 m2.The ae
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