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Advanced blade tip seal system, volume 2The results of the endurance and performance engine tests conducted on monocrystal/abrasive-tipped CF6-50 Stage 1 HPT blades fabricated in Task VII of MATE Project 3 are presented. Two engine tests are conducted. The endurance engine test is conducted for 1000 C cycles. The performance engine test is conducted on a variable cycle core engine. Posttest evaluation and analyses of the blades and shrouds included visual, dimensional, and destructive evaluations.
Document ID
19850002691
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Zelahy, J. W.
(General Electric Co. Cincinnati, OH, United States)
Fairbanks, N. P.
(General Electric Co. Cincinnati, OH, United States)
Date Acquired
September 5, 2013
Publication Date
February 1, 1982
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
TIS-R82AEB403-VOL-2
NASA-CR-167851
NAS 1.26:167851
Report Number: TIS-R82AEB403-VOL-2
Report Number: NASA-CR-167851
Report Number: NAS 1.26:167851
Accession Number
85N10999
Funding Number(s)
CONTRACT_GRANT: NAS3-20074
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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