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Simulated Single Tooth Bending of High Temperature Alloys
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Author and Affiliation:
Handschuh, Robert, F.(NASA Goddard Space Flight Center, Greenbelt, MD, United States);
Burke, Christopher(ASRC Aerospace Corp., Cleveland, OH, United States)
Abstract: Future unmanned space missions will require mechanisms to operate at extreme conditions in order to be successful. In some of these mechanisms, very high gear reductions will be needed to permit very small motors to drive other components at low rotational speed with high output torque. Therefore gearing components are required that can meet the mission requirements. In mechanisms such as this, bending fatigue strength capacity of the gears is very important. The bending fatigue capacity of a high temperature, nickel-based alloy, typically used for turbine disks in gas turbine engines and two tool steel materials with high vanadium content, were compared to that of a typical aerospace alloy-AISI 9310. Test specimens were fabricated by electro-discharge machining without post machining processing. Tests were run at 24 and at 490 C. As test temperature increased from 24 to 490 C the bending fatigue strength was reduced by a factor of five.
Publication Date: Dec 01, 2012
Document ID:
20130000795
(Acquired Jan 11, 2013)
Subject Category: MECHANICAL ENGINEERING
Report/Patent Number: NASA/TM-2012-217805, E-18536
Document Type: Technical Report
Contract/Grant/Task Num: WBS 877868.02.07.03.01.01.01
Financial Sponsor: NASA Goddard Space Flight Center; Greenbelt, MD, United States
Organization Source: NASA Goddard Space Flight Center; Greenbelt, MD, United States
Description: 20p; In English; Original contains color illustrations
Distribution Limits: Unclassified; Publicly available; Unlimited
Rights: Copyright; Distribution as joint owner in the copyright
NASA Terms: BENDING FATIGUE; GAS TURBINE ENGINES; GEARS; HEAT RESISTANT ALLOYS; LOW SPEED; MISSION PLANNING; SPACE MISSIONS
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