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

1978-04-20

1980-07-29

Powell, Jr., Everette A.

Rotary kinetic fluid motors or pumps

With passage in blade, vane, shaft or rotary distributor...

415159, F01D 518, F01D 904

Patent

active

042148510

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 commumnicate 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.

REFERENCES:
patent: 2862654 (1958-12-01), Gardiner
patent: 2896906 (1959-07-01), Durkin
patent: 3123283 (1964-03-01), Leis
patent: 3558237 (1971-01-01), Wall
patent: 3800864 (1974-04-01), Hauser et al.
patent: 3850544 (1974-11-01), Ciokajlo
patent: 3966354 (1976-06-01), Patterson
patent: 3975901 (1976-08-01), Hallinger et al.

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