General Electric Company

United States of America As Represented by the Secretary of the Air Force

The United States of America As Represented by the Administrator of the

Eugene N Tuley

Delmer H Landis, Jr

Edward C McDonough

Paul W Lozier

Robert Alan Frederick

Richard E Stenger

Charles H Gay, Jr

William K Koffel

Albert P Sterman, Deceased

Madeleine Elise Fessler

Kenneth E Monson

Raymond E Troeger

A double annular combustor having concentrically disposed inner and outer annular combustors is provided with inner and outer domes. A centerbody is disposed between the inner and outer domes and is constructed of a plurality of substantially rectangular segments positioned such that circumferential gaps between adjacent centerbody segments align alternatively with and between carburetors positioned in the inner and outer domes.

Segmented centerbody for a double annular combustor

A replaceable tip cap for attachment to the end of a rotor blade. The tip cap includes a plurality of walls defining a compartment which, if desired, can be divided into a plurality of subcompartments. The tip cap can include inlet and outlet holes in walls thereof to permit fluid communication of a cooling fluid therethrough. Abrasive material can be attached with the radially outer wall of the tip cap.

Tip cap for a rotor blade

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.

Structural cooling air manifold for a gas turbine engine

A turbine assembly is provided by which a variable area turbine vane may be cantilever mounted from an outer structural frame and further supported by an inner structural frame. The vane includes an inner trunnion about which is installed an inner band sector to partially define a flow path through the turbine. The band sector is provided with a hole which receives the trunnion. Once the vane is cantilevered from the outer frame and the band sector installed, an inner annular frame is slid under the vane trunnion to align a hole in the frame with the trunnion. A generally cylindrical trunnion extension is inserted through the frame hole and over the end of the trunnion, and then attached to the trunnion through a bolted connection. The extension is journaled for rotation within the inner structural frame hole. Passageways are provided to route cooling air from the vane into the structural frame to provide cooling of the band sector. Such a structure eliminates the need for expensive uniballs or matched assembly halves at the inner end of the turbine vanes.

Variable turbine vane assembly

A cantilevered turbine vane of the variable area variety is provided with unique retaining means to prevent relative movement between the vane and a fixed turbine housing through which the vane trunnion passes. Vernier adjusting means are provided to maintain a predetermined radial clearance between the vane and the fixed turbine housing, thereby eliminating binding between the two structures.

Variable area turbine nozzle and means for sealing same

A variable area turbine vane, for use in high temperature aircraft gas turbines, having a load carrying spar with a heat shield member surrounding the load carrying member. The heat shield member is positioned in grooves which permit spanwise and cordwise expansion of the heat shield member. Cooling air enters the hollow load bearing member and passes through holes in the load bearing member and heat shield member.

Turbine vane construction

In a segmented cylindrical flow confining apparatus, fluidic sealing is provided between the segments of the apparatus. Adjacent segments include flanges in overlapped radially spaced relationship to form a gap therebetween. A seal member resides in a pair of overlapping pockets formed in the overlapping flanges. The seal member is in sealing engagement with the end wall of each pocket and is free to rotate from a first sealing position to a second sealing position when the flow confining apparatus is subject to thermally induced growth.

Growing community of inventors

Hamilton, OH, United States of America

Eugene N Tuley