Structural cooling air manifold for a gas turbine engine

Details Structural cooling air manifold for a gas turbine engine Structural cooling air manifold for a gas turbine engine

F - Mech Eng,Light,Heat,Weapons

02

C

60/133, 170/67

F02C 7/12 (2006.01) F01D 5/18 (2006.01) F01D 17/16 (2006.01) F01D 25/14 (2006.01)

Patent

CA 1119523

Abstract An integrally cast structural cooling air manifold for a gas turbine engine being of generally annular shape and having two concentric thin walls defining a plenum therebetween. Each of the walls is provided with embossments through which aligned radial holes are bored to furnish support for a stage of rotatable vane trunnions. A series of circumferentially spaced inlet ports on the outer wall distribute cooling air into the plenum, from which it is routed to the vane airfoil portions to perform cooling functions by means of passages which communicate with the plenum via openings in the vane trunnions. Thus, the manifold performs the dual functions of distributing coolant to the vanes and supporting the vane trunnions In the manner of a turbine frame.

325060

Affiliated with

Also associated with

Rating

Structural cooling air manifold 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 Structural cooling air manifold for a gas turbine engine, we encourage you to share that experience with our LandOfFree.com community. Your opinion is very important and Structural cooling air manifold for a gas turbine engine will most certainly appreciate the feedback.

Rate now

Comments { 0 }

Profile ID: LFCA-PAI-O-414065