Abstract: In a gas turbine engine, a fan rotor and a compressor rotor are connected to a joint which is attached to a shaft. The fan rotor is connected to the joint by a plurality of fasteners extending through mounting openings in the joint and through apertures in the fan rotor. A standard retaining ring is attached to the joint to cover a portion of an enlarged head of each of the respective fasteners in order to prevent removal of the respective fasteners from the mounting openings in the joint before the respective fasteners are connected to the fan rotor.

Abstract: A mid turbine frame with an annular interturbine duct may be assembled by placing an mid turbine frame inner case of into the interturbine duct, inserting a plurality of mid turbine frame spokes radially through respective hollow radial struts of the interturbine duct to be connected to the mid turbine frame inner case to form a mid turbine frame spoke casing. A mid turbine frame outer case is also connected to the spokes, to provide an assembled mid turbine frame.

Abstract: A combustor heat shield sealing arrangement comprises a sealing rail extending from the combustor liner shell at the exit of the combustor for sealing engagement with a rail-less downstream end portion of the combustor heat shield. The sealing rail is offset relative to the downstream vane passage. Doing so may minimize the combustor/vane waterfall and, thus, minimize the horseshoe vortex effect at the leading edge of the turbine vanes.

Abstract: In a gas turbine engine, a fan rotor and a compressor rotor are connected to a joint which is attached to a shaft. The fan rotor is connected to the joint by a plurality of fasteners extending through mounting openings in the joint and through apertures in the fan rotor. A standard retaining ring is attached to the joint to cover a portion of an enlarged head of each of the respective fasteners in order to prevent removal of the respective fasteners from the mounting openings in the joint before the respective fasteners are connected to the fan rotor.

Abstract: A gas turbine engine has a casing component, such as a mid turbine frame system, which includes an outer case surrounding a spoke or strut casing. Load transfer spokes of the spoke casing are detachably connected to the outer case and radially extend between the outer case and an inner case of the spoke casing. A bearing housing is supported by the inner case of the spoke casing. An arrangement for radially centring the bearing within the outer case is provided, the arrangement including at least three radial locators mounted to the outer case.

Abstract: The manifold includes supports which slidably engage a heat shield to floatingly suspend it around the manifold. The manifold is part of a heat shield assembly inside a gas turbine engine. The assembly comprises a plurality of radially-extending supports extending from a casing of the engine to the manifold. A heat shield encloses the manifold. The heat shield has openings through which the supports pass to slidably engage the heat shield. The supports floatingly suspend the heat shield relative to the manifold.

Abstract: A gas turbine engine with: a compressor section; a turbine section; a combustor, disposed between the compressor and turbine sections, having at least one combustor mounting assembly connecting the combustor to the engine. Each combustor mounting assembly has: a longitudinal axis; and an articulating joint having a first and second portion constrained from relative translation transverse to the longitudinal axis, and where said first and second portion have a multiple rotational degrees of freedom relative to each other about axes transverse to the longitudinal axis.

Abstract: A gas turbine engine has a mid turbine frame system which includes an outer case surrounding a spoke casing. Spokes of the spoke casing are detachably connected to the outer case and radially extend through hollow struts of a segmented interturbine duct which is disposed between the outer case and an inner case of the spoke casing. A bearing housing is supported by the inner case of the spoke casing. The mid turbine frame is assembly by inserting the interturbine duct segments over the spokes and then inserting the spoke casing into the outer case.

Abstract: A fuel nozzle for a gas turbine engine comprises a nozzle body defining a passage extending therethrough and a flange around the nozzle body extending radially and outwardly from the nozzle body. The flange defines a mounting face thereof and a plurality of mounting holes in the mounting face extending through the flange. The mounting face includes a contacting land protruding from the mounting face for abutting a mounting surface of a support structure of the engine when the fuel nozzle is mounted to the support structure.

Abstract: An assembly for a gas turbine engine, the assembly comprising a combustor and a vane assembly downstream from the combustor. The vane assembly includes at least one airfoil radially extending between an inner and outer platform defining an annular gas path therebetween. At least the outer platform forms a first sliding joint connection with an adjacent outer combustor wall such that radial sealing between the outer platform and the outer combustor wall is provided at engine operating temperature, while permitting relative axial displacement therebetween.

Abstract: A mounting system for an annular internal fuel manifold disposed within a gas generator case of a gas turbine engine including at least one fastener support assembly and at least one receiving element, each fastener support assembly including a primary fastener engaging the receiving element to constrain a relative movement between the fuel manifold and the gas generator case in an axial direction while allowing the relative movement in a radial direction and a secondary fastener in position to passively and automatically engage the receiving element upon failure of the primary fastener.

Abstract: A gas turbine engine case having a working fluid flow, includes inner and outer case portions defining an annular duct for directing the working fluid flow, and a plurality of struts positioned within the annular duct and extending between the inner and outer case portions. The struts are welded to the inner and outer case portions with a first weld along a peripheral line of the respective struts and with second weld, of fillet type, in selected locations for additionally connecting a portion of each strut to the respective inner and outer case portions.

Abstract: The mounting system can be used in mounting a turbofan gas turbine engine having a nacelle including two halves, each half having a hinged end hingedly connected to the pylon and a free end lockingly engageable with the engine structure. The mounting system can include a primary connection connecting the engine structure to the pylon, and a flexible connection provided between the hinged connections and the pylon, the flexible connection being elastically deformed when a significant force is exerted in a transversal plane upon one of the halves in the closed position.

Abstract: A gas turbine engine fuel supply assembly which includes a fuel manifold mounted to a casing surrounding a combustor of the engine, and a plurality of fuel nozzles mounted to the fuel manifold. A mating interface between the fuel nozzles and the fuel manifold has at least one sealing element, and at least one aperture defined in the fuel nozzle proximate to the mating interface. The aperture is a non fuel conveying passage, and reduces conductive heat transfer to the sealing element by preventing a direct conductive heat transfer path between a hot region of the fuel nozzle and the sealing element.

Abstract: A combustor liner for a gas turbine engine including first and second annular liner portions engaged to one another with an interference fit. The first liner portion includes at least one anti-rotation feature extending therefrom and engaging the second liner portion and having a threaded hole defined therethrough at least substantially perpendicularly to an adjacent radially extending surface of the second liner portion for threadingly receiving a pushing tool for pushing against that surface.

Abstract: A gas turbine engine has an engine casing component, such as a mid turbine frame system, which may includes an outer case surrounding a spoke or strut casing. Load transfer spokes of the spoke casing extend between the outer case and an inner case of the spoke casing. A bearing housing supported by the engine casing may include a fuse arrangement for isolating bearing seizure loads from the engine casing. A seal arrangement may be provided to centralize the rotors after the fuse fails. The mid turbine frame may be provided to have a desired flexibility through the configuration of the casing and bearings in design.

Abstract: An assembly for a gas turbine engine includes a combustor and a vane assembly disposed downstream thereof. A portion of an outer platform of the vane assembly defines an axial sliding joint connection with the combustor, and includes a plurality of depressions located in an outer circumferential surface thereof opposite the combustor. The depressions are disposed in regions of expected higher thermal growth about the circumference of the outer platform such that thermal growth of the entire outer platform is substantially uniform circumferentially therearound.

Abstract: A gas turbine engine is provided having an annular duct having an inner duct wall and an outer duct wall. At least one strut extends between the inner duct wall and the outer duct wall. The strut has an aerodynamic shape. At least one vane located circumferentially adjacent the strut and axially behind a leading edge of the strut, and an aerodynamic deflector located circumferentially between each strut and each vane. The aerodynamic deflector may positioned axially upstream of a flow separation point which would otherwise be caused by the strut.

Abstract: An assembly for a gas turbine engine includes a combustor and a vane assembly disposed downstream thereof. A portion of an outer platform of the vane assembly defines an axial sliding joint connection with the combustor, and includes a plurality of depressions located in an outer circumferential surface thereof opposite the combustor. The depressions are disposed in regions of expected higher thermal growth about the circumference of the outer platform such that thermal growth of the entire outer platform is substantially uniform circumferentially therearound.

Abstract: A gas turbine engine case having a working fluid flow, includes inner and outer case portions defining an annular duct for directing the working fluid flow, and a plurality of struts positioned within the annular duct and extending between the inner and outer case portions. The struts are welded to the inner and outer case portions with a first weld along a peripheral line of the respective struts and with second weld, of fillet type, in selected locations for additionally connecting a portion of each strut to the respective inner and outer case portions.