Abstract: A thermal shielding arrangement for a turbine probe extending through an exhaust case and a turbine housing of a gas turbine engine comprises a sleeve having a radially inner end fixedly mounted to the turbine housing and a radially outer end floatingly received in a probe boss on the exhaust case. The radially outer end of the sleeve opens to an air cavity between the exhaust case and a surrounding engine nacelle to allow for air circulation around the probe.

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 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 turbine shroud segment for a gas turbine engine having an annular gas path extending about an engine axis. The engine has a turbine rotor mounted for rotation about the axis and having a plurality of blades extending into the gas path. The turbine shroud segment includes a body extending axially between a leading edge and a trailing edge and circumferentially between a first and second lateral edges. The body has a radially outer surface and a radially inner surface. The radially outer surface includes a textured surface exposed to a cooling flow. The radially inner surface defines an outer flow boundary surface of the gas path next to a tip of one of the blades. A cooling flow passageway is defined in the body and extends axially between one or more cooling inlets receiving the cooling flow from the textured surface and one or more cooling outlets.

Abstract: A turbine shroud segment has a body having a radially outer surface and a radially inner surface extending axially between a leading edge and a trailing edge and circumferentially between a first and a second lateral edge. A first serpentine channel is disposed axially along the first lateral edge. A second serpentine channel is disposed axially along the second lateral edge. The first and second serpentine channels each define a tortuous path including axially extending passages between a front inlet proximate the leading edge and a rear outlet at the trailing edge of the body.

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 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.

Abstract: A mid-turbine frame module comprises an outer structural ring, an inner structural ring and a plurality of circumferentially spaced-apart spokes structurally interconnecting the inner structural ring to the outer structural ring. At least one of the tubular spokes accommodates a service line. The remaining spokes with no service line have an internal architecture which mimics an air cooling scheme of the at least one spoke housing a service line in order to provide temperature uniformity across all spokes.

Abstract: A mid-turbine frame module comprises an outer structural ring, an inner structural ring and a plurality of circumferentially spaced-apart spokes structurally interconnecting the inner structural ring to the outer structural ring. The spokes are used as air feed pipe to provide cooling to different engine systems, such as an oil scupper line and a disc cavity of an adjacent turbine disc.

Abstract: There is disclosed a bearing assembly for a gas turbine engine. The bearing assembly has a central axis and includes at least two bearings being axially spaced from one another relative to the central axis and configured to rotatably support a rotating component of the gas turbine engine. A bearing housing includes bearing supports supporting the at least two bearings. The bearing housing is securable to a casing of the gas turbine engine via hairpin structures being axially spaced from one another.

Abstract: There is disclosed a bearing assembly for a gas turbine engine including at least two bearings axially spaced from one another relative to a central axis, and a squirrel cage secured to a casing of the gas turbine engine. The squirrel cage supports respective bearing loads of the at least two bearings. The squirrel cage has a frangible section between the bearings configured to preferentially fail upon application of a load greater than a preselected threshold bearing load.

Abstract: There is disclosed a gas turbine engine including a bearing housing having at least two bearings axially spaced from one another relative to a central axis. The bearing housing has a case between the at least two bearings having a joint configured for relative axial movement between the bearing supports. A method of operating a bearing assembly including the bearing housing is also disclosed.

Abstract: There is disclosed a bearing assembly for a gas turbine engine including at least two bearings axially spaced from one another relative to a central axis, and a squirrel cage secured to a casing of the gas turbine engine. The squirrel cage supports respective bearing loads of the at least two bearings. The squirrel cage has a frangible section between the bearings configured to preferentially fail upon application of a load greater than a preselected threshold bearing load.

Abstract: There is disclosed a gas turbine engine including a bearing housing having at least two bearings axially spaced from one another relative to a central axis. The bearing housing has a case between the at least two bearings having a joint configured for relative axial movement between the bearing supports. A method of operating a bearing assembly including the bearing housing is also disclosed.

Abstract: There is disclosed a bearing assembly for a gas turbine engine. The bearing assembly has a central axis and includes at least two bearings being axially spaced from one another relative to the central axis and configured to rotatably support a rotating component of the gas turbine engine. A bearing housing includes bearing supports supporting the at least two bearings. The bearing housing is securable to a casing of the gas turbine engine via hairpin structures being axially spaced from one another.

Abstract: The gas turbine engine can have a rotary shaft mounted to a casing via a bearing housed in a bearing housing, for rotation around a rotation axis, a gas path provided radially externally to the bearing housing, a feed pipe having a radial portion extending from an inlet end, radially inwardly across the gas path and then turning axially to an axial portion leading to an outlet configured to feed the bearing housing, the axial portion of the feed pipe broadening laterally toward the outlet.

Abstract: A turbine shroud segment has a body having a radially outer surface and a radially inner surface extending axially between a leading edge and a trailing edge and circumferentially between a first and a second lateral edge. A first serpentine channel is disposed axially along the first lateral edge. A second serpentine channel is disposed axially along the second lateral edge. The first and second serpentine channels each define a tortuous path including axially extending passages between a front inlet proximate the leading edge and a rear outlet at the trailing edge of the body.

Abstract: The gas turbine engine can have a structure for holding bearings within a casing, with a shaft being rotatably mounted to the casing via the bearings and via the structure, the structure having a first wall segment and a base structure receiving the bearings, the first wall segment having a proximal end structurally joined to the base structure, the first wall segment extending away from the base structure, and having a portion extending at least partially axially and thereby being radially flexible relative to the second wall segment, the structure providing both structural resistance and radial stretchability.