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

Subject Categories:

  • Transport Aircraft
  • Jet and Gas Turbine Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE