Abstract: A gas turbine engine has a plurality of casings defining a chamber exposable to a gasflow therein, and a plurality of retaining members are associated with the housings to retain them against displacement. Each retaining member has an end portion extending into the chamber and a shield is associated with the casings to define a protective cavity within the chamber about the end portions of the retaining members thereby to isolate the end portions from the chamber. A method of assembling a gas turbine engine is also disclosed.

Abstract: A nozzle seal arrangement, for a turbine nozzle of a gas turbine engine, which impedes leakage of high pressure cooling air past the nozzle inner bands into the flow path to the outside thereof. The nozzle seal arrangement includes an annular nozzle support flange attached to and extending along the stationary support structure adjacent to the nozzle, a band flange attached to and extending along the inner band of each nozzle segment and disposed adjacent to the support flange, a continuous seal member having a W-shaped configuration in cross-section which extends circumferentially about the central axis, and an annular recess defined in the forward face of the nozzle support flange which extends circumferentially about the central axis and receives and seats the seal member at the aft side thereof.

Abstract: A turbine engine of the type having a compressor section, combustor section and high-pressure turbine section in which compressor air is conveyed internally of the compressor and turbine sections to cool the turbine interstage volume, a first stage turbine disk includes a shaft supporting a second stage turbine disk, a turbine interstage seal is secured by boltless engagement to the disks and is prestressed to resist flexure, and the first stage disk carries a forward seal attached by boltless connections. The interstage seal includes a bore having a rearwardly-extending arm engaging the aft shaft in a bayonet connection to prevent deflection of the bore and includes passages to allow air flow around the bore. The forward seal includes radially-extending vanes to convey cooling air along the disk, and is secured by inward and outward bayonet connections, the inward connection including locking pins which are arranged to perform a balancing function.

Abstract: An inventive turbine nozzle attachment comprises a nozzle mount having a radial and tangential load carrying hook and a radial load carrying land. The nozzle hook fits onto a stud in a stationary nozzle support. The stud is adapted for carrying the tangential and radial load from a respective one of a plurality of nozzle segments, each nozzle segment includes a nozzle mount for coupling to a corresponding stud. The plurality of nozzle segments are joined circumferentially to form an annular turbine nozzle. Each nozzle segment further includes the radial land on one circumferential end of the mount and a circumferentially extending support member on an opposite circumferential end of the segment. The radial support member of one segment rests on the land of an adjacent segment. The gas loads on the nozzle segments cause each segment to load up on the support studs in the tangential and radial directions. The support members on each opposite segment end load radially downward on a land of an adjacent segment.

Abstract: A balance weight for the rotor of a gas turbine engine is adapted to mount within the cavity formed between the innermost surface of the dovetail slots formed in the circumference of the rotor disk and the bottom of the dovetail root of the rotor blades inserted within the dovetail slots. The balance weight has a head portion formed with a bottom surface which mates with the innermost surface of the dovetail slots, and a lip connected to the head portion which engages the aft surface of the rotor disk. The balance weight is supported in an aft direction within the dovetail slots by an aft blade retainer having a shoulder or projection which contacts the balance weight.

Abstract: A boltless blade retainer for preventing forward axial movement of the rotor blades in a turbo machine relative to the rotor disk comprises an annular extension or hook formed on each dovetail post on the web of the rotor disk, an impeller or blade retainer formed with a flange which is carried against the web and dovetail posts and a retaining ring interposed between the hooks of the dovetail posts and the flange of the impeller. The retaining ring secures the impeller in a fixed axial position relative to the dovetail posts and rotor disk, and is positioned to engage the rotor blades carried in the axial slots between adjacent dovetail posts to prevent their movement in a forward axial direction.