DEVELOPMENT OF A SUPERSONIC TRANSPORT AIRCRAFT ENGINE - PHASE II-B.
Monthly progress rept. for Mar 65.
PRATT AND WHITNEY AIRCRAFT EAST HARTFORD CONN
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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
- Transport Aircraft
- Jet and Gas Turbine Engines