Accession Number:
AD0367974
Title:
DEVELOPMENT OF A SUPERSONIC TRANSPORT AIRCRAFT ENGINE - PHASE II-B.
Descriptive Note:
Monthly progress rept. for Mar 65.
Corporate Author:
PRATT AND WHITNEY AIRCRAFT EAST HARTFORD CONN
Personal Author(s):
Report Date:
1965-04-15
Pagination or Media Count:
20.0
Abstract:
The basic design airflow of the STF-219 engine was changed to 650 lbssec. New ejector and installation concepts aimed at reducing drag and improving the over-all installation were examined. The effect of changing the engine from a 700 lbsec to a 650 lbsec size was discussed. Endurance testing of full-size air-cooled blades was resumed in the JT4 high spool engine. Twenty-five hours of endurance testing were completed on a set of unshrouded convectively-cooled blades at a turbine inlet temperature of 2300 F and a blade cooling air temperature of 1200 F. A blow-in-door-ejector nozzle was being fabricated in preparation for ground tests on a J57 afterburning engine to determine the effect of this nozzle configuration on exhaust noise radiation. Fabrication of parts for the two-stage fan rig was started and proceeding on schedule. Author
Descriptors:
Subject Categories:
- Transport Aircraft
- Jet and Gas Turbine Engines