A turbine comprising: a turbine housing, a wastegate passage connecting the turbine inlet and the turbine outlet; and a wastegate valve comprising a movable valve member. The wastegate valve has an open state in which a first gas may pass between a turbine inlet a turbine outlet via the wastegate passage and a closed state in which the valve member substantially prevents said first gas from passing between the turbine inlet and the turbine outlet. The valve member is mounted to an actuation member that passes through a bore of the turbine housing. The actuation member is movable to move the wastegate valve between the open and closed states. The turbine comprises a fluid conduit configured to deliver a second gas to the bore to form a fluidic seal between the bore and the actuation member to substantially prevent the passage of said first gas along the bore.

A turbine comprising: a turbine housing, a wastegate passage connecting the turbine inlet and the turbine outlet; and a wastegate valve comprising a movable valve member. The wastegate valve has an open state in which a first gas may pass between a turbine inlet a turbine outlet via the wastegate passage and a closed state in which the valve member substantially prevents said first gas from passing between the turbine inlet and the turbine outlet. The valve member is mounted to an actuation member that passes through a bore of the turbine housing. The actuation member is movable to move the wastegate valve between the open and closed states. The turbine comprises a fluid conduit configured to deliver a second gas to the bore to form a fluidic seal between the bore and the actuation member to substantially prevent the passage of said first gas along the bore.

A gas turbine engine defining a longitudinal direction and a radial direction is provided. The gas turbine engine includes a turbine section comprising a stationary outer portion, a first rotating component, and a second rotating component, wherein the first rotating component includes an aft airfoil defining a hollow passageway and coupled to a radially extended first rotor portion, wherein the hollow passageway is in fluid communication with the stationary outer portion, wherein the second rotating component is coupled to a radially extended second rotor portion; and a seal assembly between a portion of the first rotating component and the second rotating component, the seal assembly defining a balance piston cavity therebetween, wherein the balance piston cavity is in fluid communication with the hollow passageway, wherein a flow of air is routed through the stationary outer portion and the hollow passageway to the balance piston cavity, and wherein a pressure of the flow of air within the balance piston cavity is controlled to provide an axial thrust that counteracts a thrust load on the second rotor portion.

A gas turbine engine defining a longitudinal direction and a radial direction is provided. The gas turbine engine includes a turbine section comprising a stationary outer portion, a first rotating component, and a second rotating component, wherein the first rotating component includes an aft airfoil defining a hollow passageway and coupled to a radially extended first rotor portion, wherein the hollow passageway is in fluid communication with the stationary outer portion, wherein the second rotating component is coupled to a radially extended second rotor portion; and a seal assembly between a portion of the first rotating component and the second rotating component, the seal assembly defining a balance piston cavity therebetween, wherein the balance piston cavity is in fluid communication with the hollow passageway, wherein a flow of air is routed through the stationary outer portion and the hollow passageway to the balance piston cavity, and wherein a pressure of the flow of air within the balance piston cavity is controlled to provide an axial thrust that counteracts a thrust load on the second rotor portion.

A sealing assembly (1) for a turbine engine comprising a first element (2) and a second element (3), the first and second elements (2, 3) being concentric and in relative rotational movement with respect to each other about an axis of rotation (X), the sealing assembly (1) comprising at least one first wiper (4a) and an abradable member (5), the first wiper (4a) being annular in shape and carried by the first element (2), the first wiper (4a) extending radially towards the abradable member (5) and continuously around the axis of rotation (X), the abradable member (5) being annular in shape and carried by the second element (3), the abradable member (5) extending tangentially opposite the first wiper (4a), the first wiper (4a) comprising primary angular portions (11), each extending tangentially along a primary angular sector (11′), the primary angular portions (11) each having, in cross-section, a first constant profile, characterised in that the first wiper (4a) comprises secondary angular portions (13) each extending tangentially along a secondary angular sector (13′), the secondary angular portions (13) each having, in cross-section, a second profile different from the first profile, the number of secondary angular portions (13) being equal to the number of primary angular portions (11), the secondary angular portions (13) being interposed between the primary angular portions (11).

A hybrid abradable seal including a stator substrate having an external surface; a casing coupled to the external surface, the casing including radial walls extending radially from the external surface; an abradable material disposed within the casing; the abradable material and the casing being coupled together and configured to resist a deflection responsive to engine gas loads.

Methods, apparatus, systems and articles of manufacture are disclosed. An inner shroud damper for a gas turbine engine includes: at least one carrier including a joint to couple to an inner shroud, the at least one carrier having a first side and a second side, and at least one mass damper coupled to the at least one carrier.

A rotating shaft of a rotary electric machine is supported by a rotary electric machine housing. For the rotary electric machine housing, compressed air flow passages are formed. In a gas turbine engine, an air bleed port is formed in a shroud case, and compressed air that is compressed by a compressor wheel flows into the air bleed port. The compressed air that has passed through the air bleed port flows through air bleed passages formed in an engine housing and the compressed air flow passages. Then, the compressed air flows into a rotary electric machine housing.

For a rotary electric machine housing, a cooling jacket and compressed air flow passages are formed on an outer circumferential side of the cooling jacket. On an outer side wall of the rotary electric machine housing, a terminal casing is formed and electric terminal portions are accommodated in the terminal casing. Air bleed ports are formed in a shroud case of a gas turbine engine. Compressed air that is compressed by a compressor wheel flows into the air bleed ports. The compressed air that has passed through the air bleed ports flows through air bleed passages formed in an engine housing and the compressed air flow passages. Then, the compressed air reaches the terminal casing.

An aspirating face seal between high and low pressure regions of a turbomachine at a juncture between rotatable and non-rotatable members of turbomachine includes gas bearing rotatable and non-rotatable face surfaces. Primary and starter seal teeth and optional deflector seal tooth are mounted on seal teeth carrier on rotatable member. Non-rotatable face surface is mounted on an annular slider on the non-rotatable member. A pull-off biasing means urges the annular slider away from the rotatable member and the non-rotatable face surface away from the rotatable surface. A secondary seal is in sealing engagement with the annular slider in the low pressure region and the pull-off biasing means is located radially outwardly of the annular slider in the high pressure region. Biasing means may include coil springs within spring chambers of circumferentially spaced cartridges. Tongues extend inwardly from spring chambers into grooves in slider.