Behavior of forged S-816 turbine blades in steady-state operation of J33-9 turbojet engine with stress-rupture and metallographic evaluations / By F. B.Garrett, C. A. Gyorgak, and J. W. Weeton

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An investigation was conducted to determine the behavior of recently produced, forged S-816 turbine blades in a full-scale turbojet engine, and in particular, the scatter in performance of the alloy. The turbine blades were operated as continuously as possible at a temperature of 1500 degrees F and a centrifugal stress of 21,500 pounds per square inch. The operating lives of the turbine blades varied from 181 to 539 hours, a range of 358 hours. Stress-rupture properties of specimens cut from blade airfoils also varied considerably, as much as 1257 hours at 20,000 pounds per square inch and 1500 degrees F. ... continued below

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Garrett, Floyd B; Gyorgak, Charles A & Weeton, John Waldemar February 12, 1953.

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  • Main Title: Behavior of forged S-816 turbine blades in steady-state operation of J33-9 turbojet engine with stress-rupture and metallographic evaluations / By F. B.Garrett, C. A. Gyorgak, and J. W. Weeton
  • Series Title: NACA Research Memorandums

Description

An investigation was conducted to determine the behavior of recently produced, forged S-816 turbine blades in a full-scale turbojet engine, and in particular, the scatter in performance of the alloy. The turbine blades were operated as continuously as possible at a temperature of 1500 degrees F and a centrifugal stress of 21,500 pounds per square inch. The operating lives of the turbine blades varied from 181 to 539 hours, a range of 358 hours. Stress-rupture properties of specimens cut from blade airfoils also varied considerably, as much as 1257 hours at 20,000 pounds per square inch and 1500 degrees F. Since the variability of scatter of stress-rupture data is greater than that of blade performance, the scatter is probably caused by variations in the properties of the forged blades rather than by variations caused by engine operation or installation of the blades. Metallographic examinations were made to determine possible causes of the scatter and although numerous differences in microstructures of blades were found, no consistent tendencies were observed and the findings did not permit an explanation of the scatter of blade performance. The results of the metallographic examinations and of the physical tests indirectly indicated variables in the fabricating method caused the scatter in properties.

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  • : 93R16715
  • URL: http://hdl.handle.net/2060/19930087425 External Link
  • Report No.: NACA-RM-E52L17
  • Center for AeroSpace Information Number: 19930087425
  • Archival Resource Key: ark:/67531/metadc59486

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National Advisory Committee for Aeronautics Collection

The National Advisory Committee for Aeronautics (NACA) was a U.S. federal agency founded on March 3, 1915 to undertake, promote, and institutionalize aeronautical research. On October 1, 1958 the agency was dissolved, and its assets and personnel transferred to the newly created National Aeronautics and Space Administration (NASA).

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  • February 12, 1953

Added to The UNT Digital Library

  • Nov. 17, 2011, 10:13 p.m.

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  • Jan. 27, 2017, 3:05 p.m.

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Garrett, Floyd B; Gyorgak, Charles A & Weeton, John Waldemar. Behavior of forged S-816 turbine blades in steady-state operation of J33-9 turbojet engine with stress-rupture and metallographic evaluations / By F. B.Garrett, C. A. Gyorgak, and J. W. Weeton, report, February 12, 1953; (digital.library.unt.edu/ark:/67531/metadc59486/: accessed December 11, 2017), University of North Texas Libraries, Digital Library, digital.library.unt.edu; crediting UNT Libraries Government Documents Department.