Abstract: A turbine blade for a gas turbine engine has an airfoil including leading and trailing edges joined by spaced-apart pressure and suction sides to provide an external airfoil surface extending from a platform in a spanwise direction to a tip. The external airfoil surface is formed in substantial conformance with multiple cross-sectional profiles of the airfoil defined by a set of Cartesian coordinates set forth in Table 1, the Cartesian coordinates provided by an axial coordinate scaled by a local axial chord, a circumferential coordinate scaled by a local axial chord, and a span location.

Abstract: The turbine rotor assembly can include a turbine rotor disc drivingly mounted to a shaft for rotation about a rotation axis and having a central aperture extending coaxially with the shaft through the turbine rotor disc and being defined by a radially inner surface of the turbine rotor disc, a cavity downstream of and housing at least a part of the turbine rotor disc, a nut secured to the shaft and extending across the central aperture, a first air passage defined between an outer surface of the nut and the radially inner surface of the turbine rotor disc and fluidly connected to the cavity, a second air passage defined radially inward of the first air passage by an inner surface of the shaft and an inner surface of the nut.

Abstract: A gas turbine engine comprising: a shaft about an axis; a first turbine assembly mounted to the shaft, a first flow path and a second flow path extending through first turbine assembly along the axis. The second flow path is located radially inward of the first flow path relative to the axis. A second turbine assembly is about the axis downstream of the first turbine assembly, with a gap defined between the first turbine assembly and the second turbine assembly, the gap in fluid communication with the first flow path and the second flow path. A washer is downstream of the first turbine assembly. The washer has an annular body including a deflector between the first turbine assembly and the second turbine assembly, the deflector obstructing the first flow path and extending toward the second flow path.

Abstract: An integrated strut and turbine vane nozzle (ISV) has inner and outer annular duct walls defining an annular flow passage therebetween. Circumferentially spaced-apart struts extend radially across the flow passage. Circumferentially spaced-apart vanes also extend radially across the flow passage and define a plurality of inter-vane passages. Each of the struts is integrated to an associated one of the vanes to form therewith an integrated strut-vane airfoil. The inter-vane passages on either side of the integrated strut-vane airfoil may be adjusted for aerodynamic considerations. The vanes may be made separately from the struts and manufactured such as to cater for potential misalignments between the parts.

Abstract: A turbine blade for a gas turbine engine, the turbine blade having a peripheral blade tip wall surrounding a radially recessed tip pocket, the peripheral blade tip wall having: a wall height; a leading edge; a trailing edge; a pressure side wall; and a suction side wall; and a rib extending between the pressure side wall and the suction side wall defining a leading portion and a trailing portion of the radially recessed tip pocket, the rib having a rib height less than the wall height.

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 gas turbine engine comprising: a shaft about an axis; a first turbine assembly mounted to the shaft, a first flow path and a second flow path extending through first turbine assembly along the axis. The second flow path is located radially inward of the first flow path relative to the axis. A second turbine assembly is about the axis downstream of the first turbine assembly, with a gap defined between the first turbine assembly and the second turbine assembly, the gap in fluid communication with the first flow path and the second flow path. A washer is downstream of the first turbine assembly. The washer has an annular body including a deflector between the first turbine assembly and the second turbine assembly, the deflector obstructing the first flow path and extending toward the second flow path.

Abstract: The turbine rotor assembly can include a turbine rotor disc drivingly mounted to a shaft for rotation about a rotation axis and having a central aperture extending coaxially with the shaft through the turbine rotor disc and being defined by a radially inner surface of the turbine rotor disc, a cavity downstream of and housing at least a part of the turbine rotor disc, a nut secured to the shaft and extending across the central aperture, a first air passage defined between an outer surface of the nut and the radially inner surface of the turbine rotor disc and fluidly connected to the cavity, a second air passage defined radially inward of the first air passage by an inner surface of the shaft and an inner surface of the nut.

Abstract: A turbine blade for a gas turbine engine, the turbine blade having a peripheral blade tip wall surrounding a radially recessed tip pocket, the peripheral blade tip wall having: a wall height; a leading edge; a trailing edge; a pressure side wall; and a suction side wall; and a rib extending between the pressure side wall and the suction side wall defining a leading portion and a trailing portion of the radially recessed tip pocket, the rib having a rib height less than the wall height.

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: An integrated strut and turbine vane nozzle (ISV) arrangement according to an embodiment, includes a single-piece interturbine duct (ITD) and a plurality of vane nozzle segments removably attached to the ITD. Vane airfoils of the vane nozzle segments in combination with trailing edge portions of the struts, form a vane nozzle integrated with the ITD.

Abstract: An integrated strut and turbine vane nozzle (ISV) has inner and outer annular duct walls defining an annular flow passage therebetween. Circumferentially spaced-apart struts extend radially across the flow passage. Circumferentially spaced-apart vanes also extend radially across the flow passage and define a plurality of inter-vane passages. Each of the struts is integrated to an associated one of the vanes to form therewith an integrated strut-vane airfoil. The inter-vane passages on either side of the integrated strut-vane airfoil may be adjusted for aerodynamic considerations. The vanes may be made separately from the struts and manufactured such as to cater for potential misalignments between the parts.

Abstract: A compressor turbine includes a series of compressor turbine blades each having an airfoil with a profile substantially in accordance with at least an intermediate portion of the Cartesian coordinate values of X, Y and Z set forth in Table 2. The X and Y values are distances, which when smoothly connected by an appropriate continuing curve, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete airfoil shape.

Abstract: A shroud mounting arrangement comprises a shroud housing and a shroud mounted to the shroud housing. The shroud is configured to surround a stage of rotor blades of a gas turbine engine. A circumferentially segmented vane ring is disposed axially adjacent to the stage of rotor blades. The circumferentially segmented vane ring comprises a plurality of vane segments. The vane segments jointly support the shroud housing.

Abstract: An integrated strut and turbine vane nozzle (ISV) has inner and outer annular duct walls defining an annular flow passage therebetween. Circumferentially spaced-apart struts extend radially across the flow passage. Circumferentially spaced-apart vanes also extend radially across the flow passage and define a plurality of inter-vane passages. Each of the struts is integrated to an associated one of the vanes to form therewith an integrated strut-vane airfoil. The inter-vane passages on either side of the integrated strut-vane airfoil may be adjusted for aerodynamic considerations. The vanes may be made separately from the struts and manufactured such as to cater for potential misalignments between the parts.

Abstract: In an integrated strut and turbine vane nozzle (ISV) configuration, lug/slot or tag/groove arrangements may be provided between an interturbine duct (ITD) of the ISV and a vane ring of the ISV such that struts of the ITD and associated vanes are angularly positioned to form integrated strut-vane airfoils, reducing mismatch at the integration.

Abstract: A compressor turbine includes a series of compressor turbine blades each having an airfoil with a profile substantially in accordance with at least an intermediate portion of the Cartesian coordinate values of X, Y and Z set forth in Table 2. The X and Y values are distances, which when smoothly connected by an appropriate continuing curve, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete airfoil shape.

Abstract: A gas turbine engine comprises a shaft assembly including a hollow shaft of the gas turbine engine and a plug connected to the inlet end of the shaft. The hollow shaft has a shaft bore having a bore diameter. The hollow shaft has an inlet end for receiving a first portion of an incoming air flow. The plug has a plug bore therethrough, and an inlet end having an inlet diameter. The inlet diameter of the plug is smaller than the bore diameter. The plug includes a deflection surface adapted to deflect a second portion of the incoming air flow away from the shaft bore. A plug for connecting to an end of a hollow shaft of a gas turbine engine and s method of controlling a flow of fluid through a shaft having a bore therethrough of a gas turbine engine are also presented.

Abstract: In an integrated strut and turbine vane nozzle (ISV) configuration, lug/slot or tag/groove arrangements may be provided between an interturbine duct (ITD) of the ISV and a vane ring of the ISV such that struts of the ITD and associated vanes are angularly positioned to form integrated strut-vane airfoils, reducing mismatch at the integration.

Abstract: A gas turbine engine comprises a shaft assembly including a hollow shaft of the gas turbine engine and a plug connected to the inlet end of the shaft. The hollow shaft has a shaft bore having a bore diameter. The hollow shaft has an inlet end for receiving a first portion of an incoming air flow. The plug has a plug bore therethrough, and an inlet end having an inlet diameter. The inlet diameter of the plug is smaller than the bore diameter. The plug includes a deflection surface adapted to deflect a second portion of the incoming air flow away from the shaft bore. A plug for connecting to an end of a hollow shaft of a gas turbine engine and s method of controlling a flow of fluid through a shaft having a bore therethrough of a gas turbine engine are also presented.