Abstract: Disclosed is a radial tilt pad bearing assembly comprising: an outer carrier; a plurality of tilt pads retained within the outer carrier; and a corresponding plurality of retaining pins to retain the tilt pads in given circumferential positions, each fixed in the bearing assembly outer carrier so as to abut a side face of a cavity in the corresponding tilt pad. At least one retaining pin and the corresponding cavity are respectively shaped such that, when in use, a clearance in a plane transverse to the axes of the bearing assembly and the tilt pad between the retaining pin and the side face is lesser at a first location which lies substantially at the inner surface of the carrier, than at all corresponding locations at radially inner portions of the side face, with respect to the first location. A contact point between the retaining pin and the tilt pad when in use, lies substantially at the inner surface of the outer carrier.

Abstract: An apparatus for supporting a rotating shaft comprising: a housing surrounding the shaft; interposed between the housing and the shaft a plurality of tilting pads which extend in contiguous manner circumferentially around the shaft, each tilting pad being able to rock in the rotation of the shaft; and interposed between each pair of adjacent tilting pads retaining means for preventing circumferential movement of the pads around the housing due to rotation of the shaft, wherein the physical relationship between at least one tilting pad and its adjacent retaining means is such that said rocking of the pad takes place without circumferential slippage of the pad around the housing.

Abstract: The invention provides a radial tilt pad bearing assembly comprising: an outer carrier (12); a plurality of tilt pads (14) retained within the outer carrier; and a corresponding plurality of retaining pins (50) to retain the tilt pads in given circumferential positions, each fixed in the bearing assembly outer carrier so as to abut a side face (38) of a cavity (28) in the corresponding tilt pad. At least one retaining pin (50) and the corresponding cavity (28) are respectively shaped such that, when in use, a clearance (c) in a plane transverse to the axes of the bearing assembly and the tilt pad between the retaining pin (50) and the side face (38) is lesser at a first location (54) which lies substantially at the inner surface of the carrier (12), than at all corresponding locations at radially inner portions of the side face, with respect to the first location.

Abstract: A turbine nozzle support assembly includes nozzle segments each having an inner band with an integral retention flange extending radially inwardly therefrom. A plurality of retention tabs extend radially inwardly and are spaced axially aft of the retention flange to define a capture slot therebetween. A nozzle support includes a radially outwardly extending upper flange having a plurality of support pins extending axially, forwardly therefrom and disposed in complementary retention apertures in the retention flanges of the nozzle segments. A retention key is disposed in the capture slot axially between the upper flange and the retention tabs for axially retaining the nozzle segments on the nozzle support.

Abstract: A high pressure turbine in a gas turbine engine contains an arrangement of channels, holes and windows through components controlling the operating clearance between tips of turbine blades and casing shroud segments wherein the arrangement defines a serial supply path for a single cooling airflow through the clearance control components. The arrangement also includes a plurality of holes defined through a cover located between shroud holders and segments.

Abstract: In a gas turbine engine having an annular casing with a stationary support structure, a high pressure turbine, and an annular high pressure turbine nozzle having at least one stage which includes a plurality of circumferentially aligned nozzle segments and which is disposed in the annular casing between a combustor and the high pressure turbine, a nozzle support arrangement is provided for mounting each nozzle segment to the stationary support structure. The arrangement includes a single mounting pin mounted on and extending from an annular nozzle support flange on the casing support structure and a hole defined in an oval shape in the one end portion of an inner band flange for receiving the mounting pin in an interference fitting relation.

Abstract: A gas turbine engine nozzle includes outer and inner bands and a plurality of spaced apart vanes extending therebetween. The inner band includes an outer surface facing the outer band over which is flowable combustion gases, and a radially inwardly facing inner surface. A plurality of circumferentially spaced apart turbulators are joined to the inner band inner surface adjacent the trailing edges of the vanes for increasing cooling of the inner band by cooling air channeled over the turbulators.

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.