Abstract: A gas turbine engine mid turbine frame having an inner case supporting at least one bearing and at least three spokes extending radially outwardly to an outer case, the mid turbine frame having an interturbine duct extending through the mid turbine frame, the interturbine duct spaced axially closer to an upstream turbine disc than a bearing supporting structure of the mid turbine frame and mounted axially slidingly relative to the bearing supporting structure to substantially isolate the bearing supporting structure from axial loads, for example such as disc loads incurred in the unlikely event a turbine disc shaft shears within the engine.

Abstract: A mid turbine frame of a gas turbine engine includes an outer case which supports a spoke casing co-axially positioned therein. The spoke casing has load transfer spokes extending radially from an inner case and secured to the outer case. A load transfer device is provided to transfer load from the spokes to the outer case in addition to load transfer through a first group of fasteners securing the spokes to the outer case, thereby forming a secondary load transfer path from the spokes. The load transfer device includes an opening of the outer case into which at least some of the spokes are inserted.

Abstract: Devices and methods for supporting an accessory (32) in a gas turbine engine (10) are disclosed. The accessory (32) may have an interface (36) for coupling to a shaft (24) of the gas turbine engine (10). The device may comprise a first support (38) configured to support a first portion (34) of the accessory (32) proximal the interface (36) and a second support (40) configured to support a second portion (35) of the accessory (32) distal from the interface (36). The second support (40) may be configured to provide a lower resistance to relative displacement between the accessory (32) and structure (42) of the engine (10) than does the first support (34).

Abstract: A mounting system for an annular internal fuel manifold of a gas turbine engine includes three supports equally spaced apart about the annular fuel manifold, the three supports having at least two pin supports disposed between the fuel manifold and a surrounding gas generator casing. Each pin support includes a radially extending pin co-operating with an aligned ring slidingly disposed around the pin for relative sliding displacement therebetween. The pin supports providing axial constraint while permitting the fuel manifold to radially displace relative to the surrounding gas generator casing due to thermal size change.

Abstract: A gas turbine engine mid turbine frame having an inner case supporting at least one bearing and at least three spokes extending radially outwardly to an outer case, the mid turbine frame having an interturbine duct extending through the mid turbine frame, the interturbine duct spaced axially closer to an upstream turbine disc than a bearing supporting structure of the mid turbine frame and mounted axially slidingly relative to the bearing supporting structure to substantially isolate the bearing supporting structure from axial loads, for example such as disc loads incurred in the unlikely event a turbine disc shaft shears within the engine.

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: A mounting system, for installing a starter-generator to an accessory housing, where the starter-generator has a mounting end with a connecting flange and a cooling air outlet radially inward of a peripheral starter-generator housing edge, and where the accessory housing has a matching connecting flange radially inward of a peripheral accessory housing edge. The mounting system includes a cooling air outlet collection shroud enveloping the peripheral starter-generator housing edge and the peripheral accessory housing edge, the shroud having a discharge outlet. A V-band clamp releasably secures the connecting flanges together and is enveloped within the shroud in a compact mounting system that collects and discharges the exhausted cooling air.

Abstract: An access conduit for access to the interior of a combustor for the washing of the turbine components of a gas turbine engine. The access conduit is secured between a gas generator case and a combustion chamber liner of the combustor. The access conduit has an open outer end accessible from an outer face of the gas generator case and an open inner end exiting in a combustion chamber through the liner. The access conduit has one or more openings disposed in a combustor gap between the gas generator case and the liner of the combustor. A plug is removably secured in the open outer end and extends into the access conduit to obstruct the one or more openings.

Abstract: A fuel conveying member of a gas turbine engine is described and includes a fuel manifold defining an annular fuel flow passage through a body of the fuel manifold. A plurality of fuel nozzles extend from the manifold in fluid flow communication with the annular fuel flow passage. The fuel manifold includes integral attachment lugs thereon for mounting the fuel manifold within the gas turbine engine. The attachment lugs are adapted to receive pins therein and provide a mounting mechanism which allows for thermal expansion of the fuel manifold relative to a surrounding support structure to which the fuel manifold is mounted via the attachment lugs.

Abstract: A combustor for a gas turbine engine having an inner combustor wall and an outer combustor wall with a number of heat shields mounted internally thereto with fasteners. Each combustor wall has an end wall defining a combustor dome with a number of: fuel nozzle openings; impingement air openings; and heat shield fastener openings. Each of the end walls has an overlapping portion with mutually engaging sealing surfaces with the openings within the overlapping portions being aligned in overlapping pairs, where an exterior overlapping portion has at least one of the aligned openings of one overlapping pair being of larger dimension than the aligned opening in an interior overlapping portion.

Abstract: A method is provided for disassembling a gas turbine engine. The gas turbine engine includes a compressor section, a combustor section, a turbine section, a static structure and a bypass duct. The static structure houses and supports the compressor section, the combustor section and the turbine section. The static structure includes a turbine support structure. The bypass duct includes an inner duct wall, an outer duct wall and a bypass flowpath formed radially between the inner duct wall and the outer duct wall. The outer duct wall extends axially along the static structure and overlaps the turbine support structure. During the method, the turbine support structure is removed from the gas turbine engine while the outer duct wall remains installed.

Abstract: A casing assembly includes first case with a first case body at least partially disposed in a hot section. The first case body has a first case flange and the first case body adjacent to the first case flange is resiliently deformable. A second case downstream of the first case has a second case body with a second case flange extending radially outwardly to a radially-outer wall defining an outer diameter of the second case flange. The first case flange abuts the radially-outer wall of the second case flange. The second case has struts extending radially from an inner end to an outer end. The leading edge portion at the outer end of each of the struts has an axial position defined along the center axis that is similar to an axial position of the second case flange.

Abstract: A gas turbine engine has a spool including compressor and turbine rotors connected by a first shaft. The first shaft extends concentrically around a second shaft. The first shaft forward end has a portion with an inner diameter of close tolerance with the second shaft. The second shaft has a region of enlarged diameter located axially aft of the compressor rotor but axially forward of the forward end of the first shaft. The region of enlarged diameter has a diameter greater than the inner diameter of the forward end portion of the first shaft to cause the region of enlarged diameter of the second shaft to engage the first shaft in interference in the event that the second shaft is moved axially aft relative to the first shaft more than a pre-selected axial distance.

Abstract: A combustor assembly includes a hot skin of a combustion chamber wall having an inner face exposed to the combustion chamber and an opposite outer face, a receiving skin having a securing portion affixed to the hot skin outer face in an air-tight manner and a receiving flange, extending from the securing portion, that is offset from the hot skin outer face to form a female recess, a cold skin having a cold wall portion spaced from the hot skin and forming a cooling cavity therebetween, a securing portion extending from a first end of the cold wall portion affixed to the hot skin outer face in an air-tight manner and a male flange extending from a second end of the cold wall portion opposite the first end, the male flange snugly received in the female recess and forming a sliding engagement therebetween.

Abstract: A compound engine assembly with an engine core including at least one internal combustion engine, a turbine section, and a compressor having an outlet in fluid communication with an inlet of the engine core. A casing is connected to the turbine section, the compressor and the engine core. A mount cage is connected to mounts attached to the casing between the compressor and a hot zone including the turbine section and the engine core. The mount cage includes a plurality of struts all extending from the mounts away from the turbine section and engine core. The casing may be a gearbox module casing through which the turbine shaft in engaged with the engine shaft. The mount cage may be completely contained within an axial space with the turbine section and engine core being located outside of the axial space.

Abstract: A head part of an annular combustor for a gas turbine includes an annular bulkhead at the upstream end of the combustor. The bulkhead includes a first annular section integrally, inwardly and radially extending from the outer annular wall of the combustor, and a second annular section integrally, outwardly and radially extending from the annular inner wall of the combustor. The first and second annular sections are overlapped adjacent to the annular inner wall and secured together by segmented heat shields which have integrated threaded studs engaging with self-locking nuts, and cover the downstream side of bulkhead. The first annular section has a plurality of apertures circumferentially spaced apart from one another to receive fuel burners. Each burner is radial-displaceably positioned in the aperture and sealed by a burner collar, which is clamped between the heat shield and the bulkhead wall.

Abstract: A combustor heat shield assembly comprises a circumferential array of heat shield panels individually mounted to an inner surface of a combustor shell. Each heat shield panel has a sealing rail extending from a back side thereof and a plurality of bolted connections securely holding the heat shield panel on the combustor shell with the sealing rail in sealing contact with the inner surface of the combustor shell. Each pair of adjacent heat shield panels comprises first and second panels having adjoining lateral edges, the first panel having a boltless area on its back side at a location adjacent to its adjoining lateral edge. The second panel has a first one of its bolted connections provided adjacent to its adjoining lateral edge and in facing relationship with the boltless area of the first panel.