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Determination of Turbine Blade Life from Engine Field Data
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Author and Affiliation:
Zaretsky, Erwin V.(NASA Glenn Research Center, Cleveland, OH, United States);
Litt, Jonathan S.(NASA Glenn Research Center, Cleveland, OH, United States);
Hendricks, Robert C.(NASA Glenn Research Center, Cleveland, OH, United States);
Soditus, Sherry M.(United Airlines Maintenance, San Francisco, CA, United States)
Abstract: It is probable that no two engine companies determine the life of their engines or their components in the same way or apply the same experience and safety factors to their designs. Knowing the failure mode that is most likely to occur minimizes the amount of uncertainty and simplifies failure and life analysis. Available data regarding failure mode for aircraft engine blades, while favoring low-cycle, thermal-mechanical fatigue (TMF) as the controlling mode of failure, are not definitive. Sixteen high-pressure turbine (HPT) T-1 blade sets were removed from commercial aircraft engines that had been commercially flown by a single airline and inspected for damage. Each set contained 82 blades. The damage was cataloged into three categories related to their mode of failure: (1) TMF, (2) Oxidation/erosion (O/E), and (3) Other. From these field data, the turbine blade life was determined as well as the lives related to individual blade failure modes using Johnson-Weibull analysis. A simplified formula for calculating turbine blade life and reliability was formulated. The L10 blade life was calculated to be 2427 cycles (11 077 hr). The resulting blade life attributed to O/E equaled that attributed to TMF. The category that contributed most to blade failure was Other. If there were no blade failures attributed to O/E and TMF, the overall blade L(sub 10) life would increase approximately 11 to 17 percent.
Publication Date: Apr 01, 2013
Document ID:
20130013703
(Acquired Jun 20, 2013)
Subject Category: STRUCTURAL MECHANICS
Report/Patent Number: NASA/TP-2013-217030, E-15972-2
Document Type: Technical Report
Contract/Grant/Task Num: WBS 561581.02.08.03.16.03
Financial Sponsor: NASA Glenn Research Center; Cleveland, OH, United States
Organization Source: NASA Glenn Research Center; Cleveland, OH, United States
Description: 30p; In English; Original contains color and black and white illustrations
Distribution Limits: Unclassified; Publicly available; Unlimited
Rights: Copyright; Distribution as joint owner in the copyright
NASA Terms: CREEP ANALYSIS; CREEP RUPTURE STRENGTH; EROSION; FAILURE ANALYSIS; FAILURE MODES; FATIGUE LIFE; FRACTURE MECHANICS; FRACTURE STRENGTH; OXIDATION; SERVICE LIFE; THERMAL FATIGUE; TURBINE BLADES; WEIBULL DENSITY FUNCTIONS
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