Abstract: A turbine exhaust case (TEC) of a turbofan aeroengine includes a mixer for mixing exhaust gases with a bypass air stream, the TEC comprising an annular hub and the mixer surrounding the hub, and a plurality of deswirling struts circumferentially spaced apart with respect to a central axis of the TEC and located entirely within an axial length of the mixer. The mixer defines a trailing edge having one or more upstream-most locations thereof where the mixing of the exhausted gases and the bypass air stream begins to take place. The deswirling struts each extend radially across the annular exhaust gas duct and interconnect the mixer and the hub, defining a trailing edge positioned upstream of and axially spaced away from the one or more upstream-most locations of the trailing edge of the mixer.

Abstract: The present invention relates to an impeller containment system for containing the burst of an impeller or the burst of impeller fragments from an impeller hub. The containment system utilizes a catcher extending from a shroud plate adjacent the impeller, which engages with a snagger formed as a unitary part of the impeller. The catcher and snagger cooperate to restrain a burst impeller or impeller fragments to their shortest radial distance from their point of burst. The system also includes a shroud which circumferentially surrounds the impeller and a diffuser, which circumferentially surrounds the radial tip portions of the impeller.

Abstract: A device for deflecting a fluid flow comprises a casing having a circumferential wall defining a fluid passage, a rotating member disposed in the fluid passage for rotation about an axis substantially parallel to a flow of fluid within the fluid passage, a deflector extending radially from the rotating member for rotation therewith, and an outlet opening defined in the circumferential wall. The revolution of the deflector within the fluid passage forces the fluid to pass through the outlet opening where it can be collected by a strainer.

Abstract: A one piece cold combustor wall for lining the reverse flow hot combustor wall of a gas turbine engine, disposed at a distance from the outer surface of the hot combustor wall. Improved cooling of the hot combustor wall results from the addition of impingement cooling air injected through orifices in the cold combustion wall directed at the hot combustion wall together with film cooling by air conducted between the hot and cold combustor walls. The cold combustor wall is perforated with a pattern of air impingement inlet orifices through the cold combustor wall conducting compressed air from the outer surface of the cold combustor wall in compressed air jets directed at the outer surface of the hot combustor wall. The provision of a cold combustor wall also improves conventional air film cooling by adding impingement cooling and reusing the air after impingement to form a contained air film between the hot and cold walls.

Abstract: A turbine engine having interior cavity sealed by a thermally controlled valve is disclosed. The cavity is defined by at least one cylindrical wall portion. The valve comprises an opening in the cylindrical wall portion and a cylindrical band, coaxial and interior to the wall portion. The cylindrical band is made of material having a higher thermal coefficient of expansion than the wall portion. As the temperature of the engine increases, the band expands at a higher rate than the wall, thereby sealing the valve. As the temperature decreases, the band contracts thereby opening the valve. The valve may be used to permit a cavity to be pressurized at low temperatures. The pressure in the cavity may exert a forward load on a thrust bearing, suspending the engine shaft.

Abstract: The present invention is addressed to a multiple layer blade burst control system for use in turbine engines. The system utilizes a first inner containment ring and a second outer containment ring separated by a layer of thin ductile material. The inner containment ring and outer containment ring are each mounted to an engine housing by the use of a plurality of supporting legs. The first inner containment ring and the second outer containment ring each have complementary ribs and grooves on their respective inner and outer surfaces, so that when broken blades or blade fragments strike the inner surface of the inner containment ring, this ring absorbs the transfer of energy and moves towards the second containment ring. The movement of the inner containment ring also deforms the thin ductile material which creates an additional energy transfer. The system may also be utilized without the thin ductile layer, and a set of intermeshing protrusions and recesses.

Abstract: A key washer for interlocking a pair of concentric parts is described. The key washer is comprised of a flat, metal ring having an outer circumferential edge and an inner circumferential edge. Two or more formations are formed in the inner circumferential edge and adapted to be received on a mating formation of an inner one of the concentric parts. The outer circumferential edge has a plurality of straight flat sections for mating engagement with a corresponding configured surface of an outer one of the concentric parts. The metal ring prevents rotation between the concentric parts. The washer is utilized in a preferred application for interlocking an aircraft turbine engine high pressure rotor assembly and a tie shaft nut.

Abstract: An impact resistance fiber composite shell for supporting an elastic containment belt after impact with a radially propelled broken fan blade of a gas turbine engine.

Abstract: An air distribution system for an impeller rear cavity, including an air bleed at the compressor impeller tip for bleeding pressurized air into the rear cavity, and a second stream of P3 air is passed into the rear cavity area after having been cooled by a heat exchanger. The mixing of the cooled P3 air with the bleed air from the impeller tip reduces the temperature of the pressurized air in the rear cavity to reduce degradation of the impeller as well as to provide a flow of cooling air for the central bearing.

Abstract: A valve comprising a valve body defining a flow path, a seat upon which a closure member may rest for blocking an outlet port of the valve body, and a spacer removably mounted in the valve body to provide at least one arresting surface against which the closure member may abut when displaced in an open position by fluid pressure. The spacer prevent the closure member from frictionally contacting the inner surfaces of the valve body.

Abstract: The system provides engine maintenance information automatically from fault code data received from an onboard engine performance monitoring computer. The maintenance information is provided by an HTML repair guide electronically called by the control system using the fault code as part of the page address in the HTML guide. The control system automatically ensures that all fault codes are responded to, i.e. that maintenance personnel carry out the appropriate maintenance actions in response to each and every fault code, with a view to improve quality assurance of maintenance. Maintenance actions of maintenance personnel are automatically recorded for the purposes of validating and/or generating warranty claim applications. The system also has a warranty claim report generator for processing aircraft maintenance action log data.

Abstract: A cover plate for a bladed rotor in a turbine section of a gas turbine engine which comprises an annular plate segment comprising a plurality of spaced-apart seats with each seat coincident with a rivet. The rivets are the rivets used for anchoring the root of the blade in the disc, and the seats and the covers have frusto-conical surfaces having an axis which is the axis of the rivet.

Abstract: A seal assembly for a turbine blade tip shroud including a one-piece bent metallic sheet inter-segment seal having an axial component and a vertical component adapted to fit in a groove formed in the end walls of each shroud segment, wherein the shroud segment has a platform and radially extending ribs, and the seal fits tightly in the groove providing an axial and a radial component to the seal. A ring seal is also provided for sealing a joint between the shroud and a mounting structure where an annular gap is formed having an "L" shaped cross-section, the ring seal having a "C" shaped configuration and one of the legs of the "C" extending within an axial component of the "L" shaped gap. The leg has a wave pattern with the peaks of the wave in contact with opposite radial walls of the axial component of the gap for creating a gas seal at the joint.

Abstract: A cooling arrangement for a bladed rotor in a gas turbine engine, wherein each of the blades includes cooling air passages and a cover with curved fins is mounted adjacent to but connected to the rotor and spaced apart slightly from the rotor disc to form a passageway for the cooling fluid. The cooling arrangement includes a tapered, conically shaped inlet formed in the cooling passage which then diverges to form a diffuser near the outer end of the passageway. The cover includes an enlarged inner portion and a thin outer wall portion beyond the free ring diameter. A hammerhead is formed at the outer periphery of the cover whereby the hammerhead will move closer to the disc in response to centrifugal forces, thus sealing the passage.

Abstract: The present invention relates to a blade retention apparatus for a bladed rotor in a turbine section of a gas turbine engine which comprises a rivet grip which has serration at one end and an upset head at the other end, and a sleeve made of a soft metal which is compressed to the serration actually against the surfaces of the disk and the blade. The retention apparatus of the present invention provides a reliable attachment and only requires a simple hand-held pneumatic riveting tool to install.

Abstract: An assembly for improving the operation of a gas turbine engine having an annular turbine support case and a plurality of shroud segments supported on the inner, radial side of the turbine support case. The shroud segments are located end-to-end to form an annular shroud within the turbine support case. Slots are provided in each of the adjacent ends of adjacent shroud segments, and seals are provided for insertion in the slots for sealing the gaps between the adjacent ends of adjacent shroud segments. The seals further include extensions which cooperate with the turbine support case to prevent rotation of the shroud segments relative to the turbine support case.

Abstract: An outer housing for supporting a stator assembly in a gas turbine engine, wherein the support includes two outer ring sections between which the vane segments of the stator assembly are mounted to form a ring within the cylindrical support. A central ring section is provided between the outer ring sections and is connected thereto by means of spokes. The central ring section locates the structure within the engine casing. The spokes extend at an angle to the axis of the stator assembly and define openings therebetween whereby thermal distortion between the outer rings and the central ring is attenuated.

Abstract: A noise attenuating device for reducing the noise generated by a gas flow passing through an open butterfly valve having a disc pivotally mounted in a valve housing for rotation about a transversal axis between an open and a closed position thereof. The noise attenuating device comprises a first series of elongated members extending from the upstream side of the disc above the transversal axis and a second series of generally diametrically opposed elongated members extending from the downstream side of the disc below the horizontal axis. Typically, the elongated members extend at 45 degree from the disc of the butterfly valve.

Abstract: A modified turbine engine design in which control of the forward load on a thrust bearing is improved, while reducing or eliminating the need for the use of a balance piston is disclosed. The turbine engine has a longitudinal axis and comprises, a compressor for pressurizing gases in the engine. The impeller has an impeller rear face and a tip. The engine further comprises a shaft mounted to a thrust bearing for rotation about the axis. The impeller is fixed to the shaft for rotation therewith. A cavity fixed within the engine casing is defined at least by the impeller rear face and is in communication with the pressurized gases at the impeller tip. The engine further comprises a bleed in communication with both the cavity and the pressurized gases, so that the cavity is pressurized by the pressurized gases from the impeller tip and the bleed, thereby loading the impeller rear face to load the thrust bearing through the shaft.

Abstract: A cooling structure for the leading edge area of an airfoil having a plurality of passages wherein each passage has a radial component and a downstream component relative to the leading edge axis, and the outlet of each passage has a diffuser area formed by conical machining, wherein the diffuser area is recessed in the wall portion downstream of the passage.