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Thermal survey for the 1st and 2nd stage discs of the J85-CAN-40 gas turbine engine

From National Research Council Canada

DOIResolve DOI: https://doi.org/10.4224/40003714
AuthorSearch for: 1; Search for: 1; Search for: 1
Affiliation
  1. National Research Council Canada. NRC Institute for Aerospace Research
FormatText, Technical Report
Physical description22 p.
Subjectgas turbine engine; disc; temperature distribution
Abstract
To support an international program to benchmark stress analysis and life prediction methods for gas turbine disks, a test program was conducted on a small turbojet engine. Temperature measurements were required at specific locations on the first and second stage disk to identify thermo-mechanical effects. This report provides the details of the test planning and the test results.
Publication date
PublisherNational Research Council Canada
Series
  • Laboratory Technical Report (National Research Council Canada. Institute for Aerospace Research. Structures, Materials and Propulsion Laboratory), no. LTR-SMPL-02-0073 (15 May 2002).
NoteThe content is temporarily unavailable
LanguageEnglish
Peer reviewedNo
NPARC number8929028
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Record identifier1529f98d-9ffe-4e95-a451-1abf7aa90318
Record created2009-04-23
Record modified2025-11-26
Date modified: