by National Aeronautics and Space Administration, Lewis Research Center, National Technical Information Service, distributor in Cleveland, Ohio, [Springfield, Va .
Written in English
|Statement||R.S. Nelson, J.F. Schoendorf, L.S. Lin|
|Series||NASA contractor report -- NASA CR-179550|
|Contributions||Schoendorf, J. F, Lin, L. S, United States. National Aeronautics and Space Administration|
|The Physical Object|
Creep fatigue life prediction for engine hot section materials (isotropic) By R. S. Nelson, G. W. Levan and J. F. Schoendorf. Abstract. A series of high temperature strain controlled fatigue tests have been completed to study the effects of thermomechanical fatigue, multiaxial loading, reactive environments, and imposed mean stresses. The. Generally, the existing creep-fatigue models shown in Section 3 present good ability of fatigue-life prediction in the field where they were derived. However, the accuracy reduces when these models are extended to other materials at multiple temperatures and cyclic : Dan Liu, Dirk John Pons. The activities performed during the first year of the NASA HOST Program, Creep Fatigue Life Prediction for Engine Hot Section Materials (Isotropic), being conducted by Pratt & Whitney Aircraft are summarized. Lifetime prediction in creep-fatigue environment base [40, 41], Cr-base [4, 42], Ti-base [43–45], and Al . In the series austen-itic stainless steels, such as , and L used.
Creep fatigue life prediction for engine hot section materials (isotropic) The Hot Section Technology (HOST) program, creep fatigue life prediction for engine hot section materials (isotropic), is reviewed. The program is aimed at improving the high temperature crack initiation life prediction technology for gas turbine hot section components. Takahashi, Y.() Evaluation of creep-fatigue life prediction methods for low-carbon nitrogen-added stainless steel”, J. Engineering Materials and Technology , – CrossRef Google Scholar. Creep fatigue life prediction for engine hot section materials (isotropic) The first two years of a two-phase program aimed at improving the high temperature crack initiation life prediction technology for gas turbine hot section components are discussed. In Phase 1 (baseline) effort, low cycle fatigue (LCF) models, using a data base generated for a cast nickel base gas turbine hot section. Endurance life of creep-fatigue experiments are calculated by Eq., corresponding fatigue life prediction results are calculated by Eq.. All fatigue life prediction results are located within scatter band of 2 as shown in Fig. (31) lg t th = + T lg σ T + lg σ 2 T lg σ 3 T (32) N f-p r e d i c t.
Creep fatigue life prediction for engine hot section materials (isotropic): Two year update. Requirements for increased durability of gas turbine hot section components have placed a greater degree of importance on accurate structural analysis and life prediction. Various life prediction approaches for high temperature applications were. Get this from a library! Creep fatigue life prediction for engine hot section materials (isotropic): interim report. [R S Nelson; J F Schoendorf; L S Lin; United States. National Aeronautics and . Life prediction for creep‐fatigue loading conditions should be related to creep damage mechanisms. In order to examine the effect of the creep damage mode on rupture life under creep‐fatigue loading, a “combined creep‐fatigue loading test” was carried out on stainless steel. Strain-controlled creep-fatigue tests were carried out at °C using a MTS model A/T testing system. All the creep-fatigue tests were conducted under fully reversed loading condition with a constant strain rate of s − temperature at the specimen surface for fatigue and creep-fatigue tests was monitored by using a R-type thermocouple attached to the middle of the specimen.