Application of the Villari effect in a fatigue examination of nickel

Application of the Villari effect in a fatigue examination of nickel Fatigue of fracture mechanics Graphs. for HCF are described, 14 ref. and areas of research rec- Asbstracts Development of semi-elliptic biaxial loadine. fatigue cracks in AK6 aluminium alloy under ommended. photomicrographs. Basic issues in the mechanics of high cycle metal fatigue. McDow//. II./,. Intwr~rfrorml Jour~,~,l < H was (28 h at were of p-titanium performed uncharged introduced 482°C) annealed that loading. Under softening strain on the tensile and ctramcontrolled at.% alloy studied was were contact The results The liner line metahtahle 30. 45 and 55 min. the N content increased showed type was in the the gas and the liquid prersure the and the 0.67 atm. and fatigue effect tensile H-charged during treatment temperature 1723 K at a N increased, slightly alloy wa\ into the material completely Under tensile loading the last 8 h of an aging the reference results of the alloy strain cyclic and (uncharged) The of the strengths from the gas phase. whereas in vacuum. loading both increases the strength charged specimens hardness analysis M,,C N content ductility the M& decreased. formation type. of The mechanical tests indicate and in cyclic of H. \how effect initial total of H metallographic carbide\ carbides graph\. that the N content promoted ahead had little of the on the grain H slightly cyclic amplitude. in monotow decreases lifetime conditions increased, boundaries. the fracture state. The as a rewlt at a constant The uncharged tended to xcumulate along the grain Graphs, photomlcro- followed mechanical by a \aturation however, behaviour obwvations indlrect \iLe can that is not reduced reveal by the H charging. a H-induced change he interpreted and understood on the basis in the precipiwhich with leads to a slight over any 30 ref. of microstructural Coating induced life-reductions of single crystal superalloy gas turhine blade materials. Rrrssrrs, J.. Osr&s~ K. and Anrrro. M. Conf&wce: Elu~nted Trm/wcrture Corrrin~~c:S&we and Techrwb>,q\ II. Anah. eim. The The CA. effect\ results for USA (4-X Feb. 1996) of coating crystal a study as well SRR99 on the operational nickel-based which alloys the observed life of the aero ga\ investigated. of with a single (TMF) a nickel Different strain element\ under in the resulted and the the high fatigue coating. and life of the presence made of were cited tation state. This influence fraction Graph\. of H on the microstructure, in combination wwna diffraction of the o-phase. a reduction decrease direct intrwic of the mean H effect. of the u-precipitates. photomicrograph\, on the volume to dominate patterns. turbine crystal loading. aluminide TMF rattos blades single from blade were nickel-based diffusion types of wed superalloy coating with and ranges under thermo-mechanical as the protected overlay of 300°C blade a CoNiCrAlY temperature The influence of burnishing on the contact fatigue life of rings in rolling bearings. Stodolnik. B. Tribologio f PohrdJ( 1996) 27. 753-759 The the result inner of of research ring\ LHl5 on the influence including The physical NV206 were bearings velocity of passes were with MPa. HV,,, 50-120 rolling pressure The of burnishing and on some of The chosen stereolayer of metrical made meters: parameter\. steel. tribological, uperfinished. were constant. with after surface ring\ the uncoated and with 1050°C. thermal relevant life faster The cycle were a minimum a maximum temperature of a blade. out-of-phase coated of from crack graph>, the TMF 850°C with various minimum-to-maximum loads at critical blade service, particularly crack that for of rolling is presented. I' = 9.5 nl/min. used were parafwd plastic 3/Ih in. 4 to simulate caused which was number and mechanical to aero engine of SRR99 extension crack coating coated specimens The process At strain TMF life, the presence circumferential and number Parts of rings 63 HRC LT4. longitudinal Lubrication: the ball of both coating\ materials. high crack number 20 ref. the TMF wa\ due found to decrease, f= 0.04 mm/rev mm), i = cycling. rate of the major coalescence were events ` lubricant (4.62 Hertz from and been in burnished 20@1300 roughness layer to be responsible Porosity NiAl in the for the observed coating reduction hardness N and the corresponding burnishing burnished to the decreased rings the have were the surface the decrease life of ring\ bumlshdurability trihologlcal to multiple of the contact stress 4700-8800 denbities. observed in the CoNiCrAlY SRR99. R,$ 0. I2 to 0.06 pm. = deeper on the With depth In the surface of pm force of sliding martensitic transformation densities responsible Graphs, I.%2.5% use of microhardneaa in the distance > I200 on of 3 wrn from photomicro- proportionally Tests fi- force observed. The force In order further the burnithing was of N (8.550 MPa) contact fatigue compressive stresses results observed. fatigue durability and rolling in 4 ref. performed. investigations show of contact increase of out. Short fatigue crack growth hehaviour in Waspaloy at room and elevated temperatures. Smith. R.A.. Liu, Y. cm/ Gmbowski. L. Fatigue curd Frwturr of Et@wcvinR Mrrtwiols (vu/ Structure.s ( 1996) 19. 1505~1514 Short fatigue crack using computer the testing detected growth the tests have system been carried has been cracks out at room and elevated A fully for oscillatory ing with (38%). aspects superfinished to and rings then subjected significant the parameters carried to sliding F= 1200N investigations in the fatigue burnishing Graphs. optimalire are being temperatures automated controlling have with been the nickel-based and monitoring specimens. recorded behaviour long crack superalloy known as Waspaloy. initiated controlled developed of freely up to as small and employed as IO pm 700°C. of ref. of the growth temperatures surface in length made growth Effect of temper embrittlement and residual hydrogen on stage II fatigue crack growth in a low carbon martensitic stainless steel. Gourtkar. G. V.P. Trmsoctior~s of the Indim Institute of Metrr1.v ( 1996) 49. 6 17-620 Martensitic which Charpy lead\ stamleas steels are known of impact values, at prior and to be susceptible temperature has been promotes steels grain to temper embrittlement, temperature Temper mainly presence to of to lowering energy in transition and room attributed The reduce short crachs on smooth short crack propagation and Surface at and Anomalous were crack mechanical, was observed behaviour. effects on when Some the comparisons aspects fatigue I4 impact intergranular boundaries. fracture. corresponding of the material embrittlement phosphorus residual martensitic stainless microstructural behaviour environmental short segregation austenite are discussed. Photomicrographs, hydrogen in the material is expected to further the toughness http://www.deepdyve.com/assets/images/DeepDyve-Logo-lg.png International Journal of Fatigue Elsevier

Application of the Villari effect in a fatigue examination of nickel

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Elsevier
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Copyright © 1998 Elsevier Science Ltd. All rights reserved
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0142-1123
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1879-3452
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10.1016/S0142-1123(98)91122-7
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Abstract

Fatigue of fracture mechanics Graphs. for HCF are described, 14 ref. and areas of research rec- Asbstracts Development of semi-elliptic biaxial loadine. fatigue cracks in AK6 aluminium alloy under ommended. photomicrographs. Basic issues in the mechanics of high cycle metal fatigue. McDow//. II./,. Intwr~rfrorml Jour~,~,l < H was (28 h at were of p-titanium performed uncharged introduced 482°C) annealed that loading. Under softening strain on the tensile and ctramcontrolled at.% alloy studied was were contact The results The liner line metahtahle 30. 45 and 55 min. the N content increased showed type was in the the gas and the liquid prersure the and the 0.67 atm. and fatigue effect tensile H-charged during treatment temperature 1723 K at a N increased, slightly alloy wa\ into the material completely Under tensile loading the last 8 h of an aging the reference results of the alloy strain cyclic and (uncharged) The of the strengths from the gas phase. whereas in vacuum. loading both increases the strength charged specimens hardness analysis M,,C N content ductility the M& decreased. formation type. of The mechanical tests indicate and in cyclic of H. \how effect initial total of H metallographic carbide\ carbides graph\. that the N content promoted ahead had little of the on the grain H slightly cyclic amplitude. in monotow decreases lifetime conditions increased, boundaries. the fracture state. The as a rewlt at a constant The uncharged tended to xcumulate along the grain Graphs, photomlcro- followed mechanical by a \aturation however, behaviour obwvations indlrect \iLe can that is not reduced reveal by the H charging. a H-induced change he interpreted and understood on the basis in the precipiwhich with leads to a slight over any 30 ref. of microstructural Coating induced life-reductions of single crystal superalloy gas turhine blade materials. Rrrssrrs, J.. Osr&s~ K. and Anrrro. M. Conf&wce: Elu~nted Trm/wcrture Corrrin~~c:S&we and Techrwb>,q\ II. Anah. eim. The The CA. effect\ results for USA (4-X Feb. 1996) of coating crystal a study as well SRR99 on the operational nickel-based which alloys the observed life of the aero ga\ investigated. of with a single (TMF) a nickel Different strain element\ under in the resulted and the the high fatigue coating. and life of the presence made of were cited tation state. This influence fraction Graph\. of H on the microstructure, in combination wwna diffraction of the o-phase. a reduction decrease direct intrwic of the mean H effect. of the u-precipitates. photomicrograph\, on the volume to dominate patterns. turbine crystal loading. aluminide TMF rattos blades single from blade were nickel-based diffusion types of wed superalloy coating with and ranges under thermo-mechanical as the protected overlay of 300°C blade a CoNiCrAlY temperature The influence of burnishing on the contact fatigue life of rings in rolling bearings. Stodolnik. B. Tribologio f PohrdJ( 1996) 27. 753-759 The the result inner of of research ring\ LHl5 on the influence including The physical NV206 were bearings velocity of passes were with MPa. HV,,, 50-120 rolling pressure The of burnishing and on some of The chosen stereolayer of metrical made meters: parameter\. steel. tribological, uperfinished. were constant. with after surface ring\ the uncoated and with 1050°C. thermal relevant life faster The cycle were a minimum a maximum temperature of a blade. out-of-phase coated of from crack graph>, the TMF 850°C with various minimum-to-maximum loads at critical blade service, particularly crack that for of rolling is presented. I' = 9.5 nl/min. used were parafwd plastic 3/Ih in. 4 to simulate caused which was number and mechanical to aero engine of SRR99 extension crack coating coated specimens The process At strain TMF life, the presence circumferential and number Parts of rings 63 HRC LT4. longitudinal Lubrication: the ball of both coating\ materials. high crack number 20 ref. the TMF wa\ due found to decrease, f= 0.04 mm/rev mm), i = cycling. rate of the major coalescence were events ` lubricant (4.62 Hertz from and been in burnished 20@1300 roughness layer to be responsible Porosity NiAl in the for the observed coating reduction hardness N and the corresponding burnishing burnished to the decreased rings the have were the surface the decrease life of ring\ bumlshdurability trihologlcal to multiple of the contact stress 4700-8800 denbities. observed in the CoNiCrAlY SRR99. R,$ 0. I2 to 0.06 pm. = deeper on the With depth In the surface of pm force of sliding martensitic transformation densities responsible Graphs, I.%2.5% use of microhardneaa in the distance > I200 on of 3 wrn from photomicro- proportionally Tests fi- force observed. The force In order further the burnithing was of N (8.550 MPa) contact fatigue compressive stresses results observed. fatigue durability and rolling in 4 ref. performed. investigations show of contact increase of out. Short fatigue crack growth hehaviour in Waspaloy at room and elevated temperatures. Smith. R.A.. Liu, Y. cm/ Gmbowski. L. Fatigue curd Frwturr of Et@wcvinR Mrrtwiols (vu/ Structure.s ( 1996) 19. 1505~1514 Short fatigue crack using computer the testing detected growth the tests have system been carried has been cracks out at room and elevated A fully for oscillatory ing with (38%). aspects superfinished to and rings then subjected significant the parameters carried to sliding F= 1200N investigations in the fatigue burnishing Graphs. optimalire are being temperatures automated controlling have with been the nickel-based and monitoring specimens. recorded behaviour long crack superalloy known as Waspaloy. initiated controlled developed of freely up to as small and employed as IO pm 700°C. of ref. of the growth temperatures surface in length made growth Effect of temper embrittlement and residual hydrogen on stage II fatigue crack growth in a low carbon martensitic stainless steel. Gourtkar. G. V.P. Trmsoctior~s of the Indim Institute of Metrr1.v ( 1996) 49. 6 17-620 Martensitic which Charpy lead\ stamleas steels are known of impact values, at prior and to be susceptible temperature has been promotes steels grain to temper embrittlement, temperature Temper mainly presence to of to lowering energy in transition and room attributed The reduce short crachs on smooth short crack propagation and Surface at and Anomalous were crack mechanical, was observed behaviour. effects on when Some the comparisons aspects fatigue I4 impact intergranular boundaries. fracture. corresponding of the material embrittlement phosphorus residual martensitic stainless microstructural behaviour environmental short segregation austenite are discussed. Photomicrographs, hydrogen in the material is expected to further the toughness

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International Journal of FatigueElsevier

Published: Jan 1, 1998

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