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: 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 includes an axially deformable bellows between the bearings configured to permit axial relative movement of the bearings. A method of operating a bearing assembly is also disclosed.

Abstract: A shroud for a turbine blade includes a shroud body having an outer side and opposite first and second Z-shaped side edges; a first sealing fin and a second sealing fin extending outwardly from the outer side and spaced apart from each other in a streamwise direction, the first and second sealing fins extending between the first and second side edges of the shroud body; a first ridge extending radially outwardly from the outer side, the first ridge extending from and connecting the first and second sealing fins along the first side edge and having a radial height which varies; and a second ridge extending radially outwardly from the outer side, the second ridge extending from and connecting the first and second sealing fins along the second side edge and having a radial height which varies.

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 gas turbine engine rotary assembly comprises a disc mounted for rotation about an axis and having a first bayonet feature, a cover mounted to the disc; and a retaining ring having a second bayonet feature engaged with the first bayonet feature of the disc.

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 shroud for a turbine blade includes a shroud body having an outer side and opposite first and second Z-shaped side edges; a first sealing fin and a second sealing fin extending outwardly from the outer side and spaced apart from each other in a streamwise direction, the first and second sealing fins extending between the first and second side edges of the shroud body; a first ridge extending radially outwardly from the outer side, the first ridge extending from and connecting the first and second sealing fins along the first side edge and having a radial height which varies; and a second ridge extending radially outwardly from the outer side, the second ridge extending from and connecting the first and second sealing fins along the second side edge and having a radial height which varies.

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 includes an axially deformable bellows between the bearings configured to permit axial relative movement of the bearings. A method of operating a bearing assembly is also disclosed.

Abstract: A rim seal between a stator and a rotor in a gas turbine engine is described. The seal includes an axial overlap between platform rims of the stator and the rotor. The axial length of the platform rim of one of the stator and the rotor is accommodated within a radially aligned trench defined in the other of the stator and the rotor.

Abstract: A gas turbine engine rotary assembly comprises a disc mounted for rotation about an axis and having a first bayonet feature, a cover mounted to the disc; and a retaining ring having a second bayonet feature engaged with the first bayonet feature of the disc.

Abstract: A rim seal located between a stator and a rotor in a gas turbine engine includes an axial overlap between platform rims of the stator and the rotor. The axial length of the platform rim of one of the stator and the rotor is accommodated within a radially aligned trench defined in the other of the stator and the rotor.

Abstract: The turbine exhaust structure for a gas turbine engine includes a turbine exhaust duct and a bearing housing. The turbine exhaust duct includes annular inner and outer case portions radially spaced apart to define an annular gas path therebetween and a plurality of struts extending between and structurally interconnecting the inner and outer case portions. The struts are circumferentially spaced apart about within the annular gas path. The bearing housing is disposed within the inner case portion of the turbine exhaust duct. A plurality of structural ribs extend between the bearing housing and the inner annular case portion. The structural ribs are circumferentially spaced from one another and are circumferentially offset from the struts.

Abstract: A mid-turbine frame of a gas turbine engine has a structural ring assembly comprising an outer ring, an inner ring having a plurality of threaded bosses extending from a radially outer surface thereof, and a corresponding number of structural spokes interconnecting the inner ring to the outer ring. Each spoke has a radially inner threaded end threadably engaged in an associated one of the threaded bosses on the inner ring.

Abstract: A multi-spool gas turbine engine comprises a low pressure (LP) spool and a high pressure (HP) spool independently rotatable about a central axis. The LP pressure spool has an LP compressor and an LP turbine. The HP spool has an HP turbine and an HP compressor. An accessory gear box (AGB) is drivingly connected to the HP spool. The LP compressor is disposed axially between the HP compressor and the AGB. A gear train drivingly couples the LP compressor to the LP turbine. The gear train is integrated to the AGB.

Abstract: A movement-constraining assembly for a fluid-conveying system comprises a tubular body adapted to be secured to a component coupling end of a component of the fluid-conveying system. A fluid-conveying tube has a tube coupling end adapted to be connected to the component of the fluid-conveying system and defining an inner passage for fluid to pass therethrough to or from the component, the tube having an interface at the tube coupling end. A blocking nut has an inner surface complementary to at least a surface of the interface of the tube to block rotation between the tube and the blocking nut, the blocking nut further comprising an outer surface complementary to a surface of the tubular body to block rotation between the blocking nut and the component, whereby the blocking nut blocks a rotation between the fluid-conveying tube and the component coupling end.

Abstract: A spoke locking arrangement comprising a washer seated in a seat defined in a structural ring of a gas turbine engine, the washer having a portion thereof plastically deformed into an anti-rotation notch defined in the structural ring, thereby locking the washer against rotation in the seat, the washer further comprising a set of holes for receiving corresponding bolts, and wherein the washer further has at least one anti-rotation tab at each hole, the anti-rotation tabs being deformable in engagement with the bolts to individually lock the same against rotation.

Abstract: A turbine shroud segment forms part of a circumferentially segmented shroud assembly surrounding a circumferential array of turbine blades of a gas turbine engine. The turbine shroud segment has a platform extending axially from an upstream end portion to a downstream end portion relative to a flow of gas through the gas turbine engine. A heat shield extension projects radially inwardly and in an upstream direction from the upstream end portion of the platform.

Abstract: A rim seal between a stator and a rotor in a gas turbine engine is described. The seal includes an axial overlap between platform rims of the stator and the rotor. The axial length of the platform rim of one of the stator and the rotor is accommodated within a radially aligned trench defined in the other of the stator and the rotor.

Abstract: A multi-spool gas turbine engine comprises a low pressure (LP) spool and a high pressure (HP) spool independently rotatable about a central axis. The LP pressure spool has an LP compressor and an LP turbine. The HP spool has an HP turbine and an HP compressor. An accessory gear box (AGB) is drivingly connected to the HP spool. The LP compressor is disposed axially between the HP compressor and the AGB. A gear train drivingly couples the LP compressor to the LP turbine. The gear train is integrated to the AGB.

Abstract: An integrated shroud structure surrounds a circumferential array of stator vanes and a circumferential array of rotor blades of a gas turbine engine. The shroud structure includes a plurality of vane shroud segments and a plurality of blade shroud segments. The blade shroud segments integrally extend downstream from the vane shroud segments and each pair of circumferentially adjacent blade shroud segments defines an inter-segment gap. At least one slot extends axially from a location downstream of the vane shroud segments to an aft end of the blade shroud segment. The inter-segment gaps and slots are sealed by a sealing band mounted around the full circumference of the integrated shroud structure.