Cooled aerofoil blade for vane for a gas turbine engine

Details Cooled aerofoil blade for vane for a gas turbine engine Cooled aerofoil blade for vane for a gas turbine engine

1986-09-04

1993-11-23

Walsh, Donald P.

Fluid reaction surfaces (i.e., impellers)

With heating, cooling or thermal insulation means

Changing state mass within or fluid flow through working...

60266, 415115, 416 96R, B63H 114

Patent

active

052638200

ABSTRACT:
A cooled aerofoil blade for a gas turbine engine has a hollow trailing edge region in which bridging members interconnect the convex and concave flanks of the blade. The bridging members are each provided with angled cooling passages which are in operation exposed to a cooling air flow and direct that flow onto the internal surfaces of the convex and concave flanks so as to provide impingement cooling thereof.

REFERENCES:
patent: 3819295 (1974-06-01), Hauser

Affiliated with

Also associated with

Rating

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

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

Rate now

Comments { 0 }

Profile ID: LFUS-PAI-O-1843607