Advanced Turbine Engine Seal Design.

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Abstract:

Program objective was to determine film-cooling effectiveness, eta sub f and transpiration cooling effectiveness, eta sub T, on advanced shroud concepts tested in a single stage, high pressure ratio air turbine. Three film-cooled shroud segments, with varying film hole patterns, and one transpiration-cooled shroud segment, featuring a coarse matrix Poroloy shroud surface, were designed, manufactured and tested. Effectiveness data were obtained and analyzed. Distribution of gas recovery temperature and of gas stream static pressure along the shroud surface were also measured for use in applying the effectiveness data to the design of future cooled shroud systems. The program results show that high levels of eta sub f and eta sub T are achievable on air cooled turbine shrouds. Author

Author(s):
Koffel, William K. ; Meyer, Leonard J.
Author Organization(s):
GENERAL ELECTRIC CO CINCINNATI OHIO AIRCRAFT ENGINE GROUP
Descriptive Note:
Final rept. 30 Jun 72-31 Mar 73,
Pagination:
0247

Security Markings

DOCUMENT & CONTEXTUAL SUMMARY

Distribution:
Approved For Public Release

RECORD

Collection: TR
Identifying Numbers
Report Number(s):
R73AEG193, AFAPL-TR-73-46
Contract/Grant Number(s):
F33615-72-C-1775
Task Number(s):
306613
Project Number(s):
AF-3066
Monitor Series:
TR-73-46
 Subject Terms
Communities of Interest:
No COI(s) Identified
Descriptor(s):
*SEALS(STOPPERS), *SHROUD RINGS, GAS TURBINES, FILM COOLING, TEMPERATURE, STATICS, PRESSURE, POROUS MATERIALS, MEASUREMENT, HEAT TRANSFER, SWEAT COOLING
Field(s)/Group(s):
Adhesives, Seals and Binders, Jet and Gas Turbine Engines
Keyword(s):
*TURBINE SHROUDS, S L change 8323
Report Date:
1973 May 01