Abstract: A thermocouple rake for measuring the temperature of heated fluids. The thermocouple rake is provided with a cooling chamber for circulating a coolant about individual thermocouple assemblies to cool the assemblies during use in the hot gas. A U-shaped channel is formed downstream in the flow of fluid to accept lead wires from the thermocouple assemblies to deflect the hot gas fluid from contacting the lead wires.

Abstract: A variable geometry device is provided for synchronous control of flow of fluid at the compressor inlet and outlet of a turbine engine. The turbine engine includes a support housing, a compressor contained within the support housing, a set of variable inlet guide vanes and a compressed air outlet in which a pair of spaced walls define an annular and radially extending diffuser passageway. The inner end of the diffuser passageway is open to the compressor outlet while the outer end of the diffuser passageway is open to the combustion chamber for the turbine engine. A plurality of circumferentially spaced diffuser vanes are mounted to one of the diffuser walls and protrude across the diffuser passageway. An annular recessed channel is formed around the opposite diffuser wall and an annular ring with a hollow cavity is mounted within the channel.

Abstract: A novel turbine inlet nozzle assembly is provided for use with a gas turbine engine and includes unique nozzle cooling means. The turbine inlet nozzle of the present invention comprises an inner annular shroud, an outer annular shroud coaxial with and spaced radially outwardly from the inner shroud and a plurality of circumferentially spaced vanes extending between the shrouds. The shrouds and the vanes, moreover, are of integral construction with each other and, preferably, each vane has a hollow interior. An annular impingement plate is fixedly secured about each axial end to the outer periphery of the outer shroud while, similarly, a second impingement plate is secured at each axial end to the inner periphery of the inner shroud. Moreover, the impingement plates include a plurality of holes formed therethrough and through which a portion of the turbine compressor output is bled to cool the inner and outer shrouds.

Abstract: A variable geometry device for use with the turbine nozzle of a turbine engine of the type having a support housing and a combustion chamber contained within the support housing. A pair of spaced walls in the support housing define an annular and radially extending nozzle passageway. The outer end of the nozzle passageway is open to the combustion chamber while the inner end of the nozzle passageway is open to one or more turbine stages. A plurality of circumferentially spaced nozzle vanes are mounted to one of the spaced walls and protrude across the nozzle passageway. An annular opening is formed around the opposite spaced wall and an annular ring is axially slidably mounted within the opening. A motor is operatively connected to this ring and, upon actuation, axially displaces the ring within the nozzle passageway.

Abstract: A variable geometry device is provided for use with the compressor outlet of a turbine engine. The turbine engine includes a support housing, a compressor contained within the support housing and having a compressed air outlet and in which a pair of spaced walls define an annular and radially extending diffuser passageway. The inner end of the diffuser passageway is open to the compressed outlet while the outer end of the diffuser passageway is open to the combustion chamber for the turbine engine. A plurality of circumferentially spaced diffuser vanes are mounted to one of the diffuser walls and protrude across the diffuser passageway. An annular recessed channel is formed around the opposite diffuser wall and an annular ring is mounted within the channel. A motor is operatively connected to this ring and, upon actuation, displaces the ring transversely across the diffuser passageway to variably restrict the diffuser passageway.

Abstract: A variable geometry device is provided for use in a turbine engine having a support housing, a rotor contained within the support housing and a pair of spaced walls forming an annular and radially extending passageway open at one end to the rotor. An annular recessed channel is formed in one of the support housing walls while a ring is mounted within the channel and movable between a retracted position in which the ring is nested within the channel and an extended position in which the ring protrudes transversely into and variably restricts the passageway so that the restriction of the fluid passageway is substantially proportional to the transverse position of the ring. A plurality of circumferentially spaced vanes are secured to the ring and these vanes extend transversely across the fluid passageway and are slidably received within slots formed in the other support housing wall.

Abstract: A variable turbine inlet nozzle assembly is provided for use in high temperature environments. The nozzle assembly comprises a plurality of vanes and each vane includes a shaft extending outwardly from it. The shafts in turn are rotatably mounted to an annular mounting member so that the vanes are circumferentially spaced from each other and positioned within a gas stream passageway formed within the turbine housing between the combuster and turbine stages. An actuating assembly includes a ring rotatably mounted to the turbine housing concentrically with the mounting member while actuating arms extending between the ring and each shaft selectively rotates or pivots the vanes in unison with each other. Each vane further includes a hollow interior which is fluidly connected with the turbine engine compressor output to provide cooling to and prevent thermal distortion of the vanes.

Abstract: A bearing lubricant injector comprising a first ring member secured to a shaft which is rotatably supported by a bearing adjacent the first ring member. A second ring member is secured to the first ring member by a plurality circumferentially spaced stanchions to define a lubricant flow passage which directs an axial flow of lubricant into the bearing. The radially outer surface of the first ring member is inclined upwardly toward the bearing so that rotation of the ring centrifugally forces the lubricant into the bearing.

Abstract: A turbine blade indexing assembly adapted for variably adjusting the pitch of the turbine blades in a turbine wheel. The indexing assembly includes a housing secured to a turbine hub and an indexing ring contained between the housing and the hub and adapted for limited rotational movement relative to the housing. A plurality of radial bores are formed around the periphery of the housing and each bore is adapted to receive a cylindrical shank of the turbine blade therethrough. A blade retainer ring, having a transverse bore adapted to register with a transverse bore formed through the turbine blade shank, is positioned on each turbine blade shank so that a pin member inserted through the registering bores in the shank and retainer ring rotatably secures the turbine blade to the housing. One end of the pin member is received in an actuator slot formed in the indexing ring so that rotational movement of the indexing ring produces a corresponding axial rotation of the turbine blades.

Abstract: A bevel gear shimming gage is provided for determining the shim sizes for the bearings supporting the gears within a bevel gear housing. A first main housing abuts against a first bearing, a first bearing support abuts against a second bearing and a first gaging rod is received through registering apertures in the first bearing support and the first main housing and provides a means whereby the axial distance between a gaging rod reference point and a first main housing reference point may be determined. In addition, the gaging rod provides a means whereby the axial distance between reference points on the gaging rod and the bearing supports may be determined.