Aircraft gas turbine engine turbine blade cooling

Details Aircraft gas turbine engine turbine blade cooling Aircraft gas turbine engine turbine blade cooling

1974-11-08

1976-04-13

Husar, C. J.

Power plants

Reaction motor

Interrelated reaction motors

60229, 60 3923, 60 3966, F02K 302, F02C 306, F02C 718

Patent

active

039495493

ABSTRACT:
An axial flow gas turbine engine, for use in a V/STOL aircraft, of the type having a rotatable nozzle for vectoring the direction of exhausting gas and a tapping for bleeding high pressure compressor outlet gas for use in an aircraft stabilising system, has controllable means for supplying compressor outlet gas to the turbine blades. The same valve is used for controlling supply of gas to the turbine blades and to the stabilising system.

REFERENCES:
patent: 2677932 (1954-05-01), Forsling
patent: 2783965 (1957-03-01), Birmann
patent: 2940257 (1960-06-01), Eckert et al.
patent: 3263416 (1966-08-01), Bill et al.
patent: 3482804 (1969-12-01), Pyptiuk
patent: 3677501 (1972-07-01), Denning

Affiliated with

Also associated with

Rating

Aircraft gas turbine engine turbine blade cooling does not yet have a rating. At this time, there are no reviews or comments for this patent.

If you have personal experience with Aircraft gas turbine engine turbine blade cooling, we encourage you to share that experience with our LandOfFree.com community. Your opinion is very important and Aircraft gas turbine engine turbine blade cooling will most certainly appreciate the feedback.

Rate now

Comments { 0 }

Profile ID: LFUS-PAI-O-745000