Abstract: A turbine exhaust drain system has a sump where liquid collects and a suction pipe having an inlet end fluidly connected to the sump and an outlet end fluidly connected to a core gas path of a turbine exhaust case. In use, the combustion gases flowing through the exhaust case creates a venturi effect to draw the liquid from the sump into the core gas path where the liquid and the combustions gases combine into a mixed flow before being discharged through an outlet end of the exhaust case.

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 tube assembly according to an exemplary aspect of the present disclosure includes, among other things, an adjustable joint having a flange axially movable along an end fitting having a male/female connection with a mating part. The flange is threadably engaged with the end fitting to provide for the adjustment of the position of the flange along the end fitting. The adjustable joint accommodates thermal effects and tolerance stack-up in a male/female connection.

Abstract: A blade containment assembly for a gas turbine engine comprises a casing having a first casing member surrounding a set of rotor blades and a second casing member extending axially from the first casing member. The first casing member has an outer annular wall welded to the second casing member at a weld joint disposed in a blade containment zone of the casing and an inner containment ring spaced radially inwardly from the outer annular wall and extending axially from a first location forward of the weld joint to a second location aft of the weld joint.

Abstract: A turbine exhaust case assembly has an exhaust case and a bearing housing mounted in the exhaust case. A plurality of fasteners secures the bearing housing to the exhaust case. A spacer is mounted between the fasteners and one of the bearing housing and the exhaust case. The fasteners are welded to the spacer, thereby locking the fasteners against rotation.

Abstract: A gas turbine engine has a bearing housing mounted to structure linked to the engine mounting pads. The bearing housing has bearing housing flanges with bearing housing flange openings aligned with attachment flange openings of the structure. Some of the bearing housing flange openings are slots. A first group of fasteners extends through one of the attachment flange openings and through one of the bearing housing flange openings. A second group of fasteners extends through one of the attachment flange openings and through one of the slots. The first group of fasteners are sacrificial fasteners configured to fracture in response to a load on the bearing housing exceeding a fracture load. The bearing housing is displaceable relative to the structure after fracture of the sacrificial fasteners via the second group of the fasteners moving within and relative to respective ones of the slots.

Abstract: A gas turbine engine has a housing exposed to a high temperature environment. The housing has a circumferential wall extending around the engine centerline and circumscribing an oil cavity. The wall has a sealing interface at an inner diameter thereof, the sealing interface having a central axis offset from the engine centerline. A boss is formed on the wall on the offset side relative to the engine centerline and a probe is mounted to the boss. The probe projects into the oil cavity. The oil in the oil cavity thermally shields the probe from the high temperature environment.

Abstract: A bearing assembly comprises a first bearing axially spaced from a second bearing, each bearing having an inner race disposed on a shaft and having an outer race. The bearings are mounted to a mounting sleeve having an outer sleeve surface and an inner sleeve surface engaging the outer race of each bearing. The mounting sleeve has an outer surface engaged with an inner bearing support of a bearing housing having an enclosed chamber. A housing oil inlet is in fluid communication with the enclosed chamber. The mounting sleeve includes an axially extending sleeve oil passage in fluid communication with the housing oil inlet. The mounting sleeve has a first outlet in the vicinity of the first bearing and the sleeve oil passage has a second outlet in the vicinity of the second bearing.

Abstract: A variable guide vane (VGV) assembly, has: a casing enclosing a cavity and defining apertures distributed around a central axis; variable guide vanes (VGVs) distributed around the central axis and having an airfoil portion extending from a first end to a second end along a pivot axis, and a shaft portion pivotably received within the apertures; vane drive members secured to the shaft portions of the VGVs and located within the cavity, a unison transmission member within the cavity and rotatable about the central axis and engaged to the vane drive members, and an external mechanism secured to the second end of one of the VGVs and disposed outside the cavity, the external mechanism engageable by an actuator for rotating the one of the VGVs about its pivot axis, thereby rotating the unison transmission member, which, in turn, drives a remainder of the VGVs in rotation.

Abstract: A reverse-flow gas turbine engine includes a core of the gas turbine engine comprising multiple spools rotatable about a center axis of the gas turbine engine. Each spool is configured to pressurize air and to extract energy from combustion gases. The air and combustion gases are configured to flow through the core in a forward direction from an air inlet at an aft end of the core to an outlet at a forward end of the core. A propeller is disposed forward of the outlet. A reduction gearbox (RGB) is drivingly engaged to the core. An electric motor is drivingly engaged to the propeller and disposed axially between the RGB and the propeller.

Abstract: A through-flow gas turbine engine includes a core comprising multiple spools rotatable about a center axis. An accessory gearbox (AGB) is drivingly engaged to the core and disposed aft of the outlet. A reduction gearbox (RGB) is drivingly engaged to the core and disposed forward of the inlet. The RGB has an RGB output to provide rotational output to a rotatable load. An electric motor is drivingly engaged to the rotatable load. An electric generator is configured to provide electrical power to the electric motor. One of the electric motor and the electric generator is disposed axially between the outlet and the AGB and the other of the electric motor and the electric generator is disposed axially between the inlet and the RGB.

Abstract: A twin-engine system includes a gas turbine engine comprising a core and a first output shaft drivable by the core. An electric engine has an electric motor configured to drive a second output shaft. A reduction gear box (RGB) has an RGB input drivingly engaged to both the first output shaft and the second output shaft. The RGB has an RGB output to provide rotational output to a rotatable load.

Abstract: A bearing assembly comprises a first bearing axially spaced from a second bearing, each bearing having an inner race disposed on a shaft and having an outer race. The bearings are mounted to a mounting sleeve having an outer sleeve surface and an inner sleeve surface engaging the outer race of each bearing. The mounting sleeve has an outer surface engaged with an inner bearing support of a bearing housing having an enclosed chamber. A housing oil inlet is in fluid communication with the enclosed chamber. The mounting sleeve includes an axially extending sleeve oil passage in fluid communication with the housing oil inlet. The mounting sleeve has a first outlet in the vicinity of the first bearing and the sleeve oil passage has a second outlet in the vicinity of the second bearing.

Abstract: A gas turbine engine exhaust case assembly comprises: an exhaust case having an axis and defining an annular gas path; a bearing housing coaxially supported within the exhaust case; an exhaust cone coaxial and rearward of the exhaust case; a heat shield joined to the exhaust cone, the heat shield being disposed radially between the exhaust cone and the bearing housing; and a mounting bracket extending from the exhaust case and joining the exhaust case and the exhaust cone together.

Abstract: Turbine and other bladed disc assemblies and associated methods are disclosed. In an embodiment, a turbine assembly includes a rotor and a turbine disc secured to the rotor via a nut and a deformable retainer. The nut is threadably engaged with the rotor to secure the turbine disc to the rotor. The retainer is deformed to co-operatingly engage with a periphery of the nut and configured to hinder rotation of the nut relative to the rotor.

Abstract: A gas turbine engine exhaust case assembly comprises: an exhaust case having an axis and defining an annular gas path; a bearing housing coaxially supported within the exhaust case; an exhaust cone coaxial and rearward of the exhaust case; a heat shield joined to the exhaust cone, the heat shield being disposed radially between the exhaust cone and the bearing housing; and a mounting bracket extending from the exhaust case and joining the exhaust case and the exhaust cone together.

Abstract: A turbine exhaust case assembly has an exhaust case and a bearing housing mounted in the exhaust case. A plurality of fasteners secures the bearing housing to the exhaust case. A spacer is mounted between the fasteners and one of the bearing housing and the exhaust case. The fasteners are welded to the spacer, thereby locking the fasteners against rotation.

Abstract: A gas turbine engine has: an engine shaft rotatable about a rotation axis; at least two bearings spaced apart from one another along the rotation axis, the at least two bearings having inner races for rotation with the engine shaft, outer races, and rolling elements disposed radially between the inner races and the outer races; a bearing support extending axially along the rotation axis from one of the at least two bearings to the other, the bearing support secured to both of the outer races of the at least two bearings, the bearing support secured to a structural case of the gas turbine engine via frangible tabs.

Abstract: A mid-turbine frame (MTF) assembly having: an outer case circumferentially extending around a central axis; an outer ring secured to the outer case and disposed radially inwardly of the outer case relative to the central axis; an inner case structurally connected to the outer case and disposed radially inwardly of the outer ring relative to the central axis; a main plenum circumferentially extending around the central axis and located between the outer case and the outer ring, the main plenum having an inlet fluidly connectable to a source of cooling air, a first outlet fluidly connected to a secondary plenum between the main plenum and the inner case, a second outlet configured to be fluidly connected to a rotor cavity of the low-pressure turbine, and a third outlet configured to be fluidly connected to a plenum surrounding a containment ring of the low-pressure turbine.

Abstract: A case assembly for a turbine section has a structural outer case structurally connected to a gas generator upstream of the outer case and to an exhaust case downstream of the outer case. The assembly further comprises a containment ring mounted within the outer case and surrounding a plurality of axially spaced-apart turbine stages. An inner surface of the containment ring defines a plurality of shroud receiving portions. An annular plenum is defined between the outer case and the containment ring. The plenum has an inlet connected to a source of pressurized coolant. Outlets are circumferentially and axially distributed and defined through the containment ring. The outlets provides flow communication between the annular plenum and the plurality of axially spaced-apart turbine stages.