Abstract: A gas turbine engine includes a primary flow path fluidly connecting a compressor section, a combustor section and a turbine section. A cooling air flowpath is positioned radially outward of the primary flowpath. A first seal spans from an inner diameter of the cooling air flowpath to an outer diameter of the cooling air flowpath. The first seal includes at least one axial convolution and a plurality of pass through features. A bifurcation feature is positioned downstream of the first seal. The bifurcation feature is configured to direct a portion of an airflow through the first seal into a cooling air passage. A second seal contacts the bifurcation and the first seal, such that fluid radially inward of the bifurcation feature.

Abstract: An airfoil for a gas turbine engine according to an example of the present disclosure includes a platform section and an airfoil section extending in a spanwise direction from the platform section to a tip portion establishing a tip. The airfoil section has an external wall defining pressure and suction sides extending in a chordwise direction between a leading edge and a trailing edge, and the pressure and suction sides are spaced apart in a thickness direction between the leading edge and the trailing edge. The tip portion includes a tip pocket and a tip shelf extending inwardly from the tip. The tip pocket and tip shelf are on opposite sides of a shelf wall.

Abstract: A sensor signal produced by a sensor as a feedback device rotates with a propeller about an axis and moves along the axis with adjustment of a blade angle of the propeller is received, the sensor signal indicative of a rotational speed and of the blade angle of the propeller. From the sensor signal, it is determined whether the rotational speed is within a predetermined range of a reference speed and an expected change in the blade angle has occurred in response to a command to adjust the blade angle to maintain the rotational speed at the reference speed. In response to determining that the rotational speed is within the predetermined range of the reference speed and the expected change in the blade angle has failed to occur in response to the command, inoperable movement of the feedback device along the axis is determined and an alert is output.

Abstract: To provide a turbine blade, a manufacturing method for a turbine blade, and a gas turbine. In the turbine blade including a cooling passage provided along a blade height direction, the cooling passage includes: a first cooling hole including one end opening toward a front end, and having an inner diameter that is constant along the blade height direction; and a second cooling hole including one end communicating with the other end of the first cooling hole without a level difference, and having an inner diameter that is increased toward a base end. A length from the one end of the first cooling hole to a position where the first cooling hole and the second cooling hole are communicated with is 40% to 60% of a length from the one end of the first cooling hole to a gas path surface on the base end.

Abstract: A blower for providing a supply of air at positive pressure in the range of approximately 2 cmH2O to 30 cmH20 includes a motor, at least one impeller, and a stationary component. The stationary component includes an inlet and an outlet. The motor, the impeller, the inlet and outlet are co-axial.

Abstract: Compressor rotor structure for turbomachinery, such as a compressor, is provided. Disclosed embodiments can benefit from sealing sleeves that may be arranged to inhibit passage onto respective hirth couplings of process fluid being processed by the compressor. The sealing sleeves may be affixed to adjoining structures (e.g., adjoining impeller bodies) by way of a slip fit connection to one of the adjoining structures and an interference fit connection with respect to the other adjoining structure, which is conducive to a user-friendly assembly of the sealing sleeves with the adjoining structures.

Abstract: An internally cooled turbine blade for use in a gas turbine engine includes a serpentine channel extending within the turbine blade for flowing cooling air through the interior of the blade. The turbine blade includes turbulators positioned within the serpentine channel to cause or increase turbulence of the cooling air flowing through the serpentine channel, increasing the heat transfer between the turbine blade and the cooling air before exiting a plurality of air outlets within the turbine blade.

Abstract: A multiphase pump for conveying a multiphase process fluid includes a pump housing, a stationary diffuser, a rotor and swirl brake. The rotor is arranged in the pump housing and is rotatable about an axial direction, the rotor including a pump shaft and an impeller fixedly mounted on the pump shaft. The stationary diffuser is arranged adjacent to and downstream of the impeller. The impeller includes a blade with the blade having a radially outer tip, and a ring surrounding the impeller and arranged at the radially outer tip of the blade. A passage is between the ring and a stationary part configured to be stationary with respect to the pump housing, the passage extending in the axial direction from an entrance to a discharge. The swirl brake is disposed at the passage, and configured and arranged to brake swirling of the process fluid passing through the passage.

Abstract: A turbomachine has a bearing in a bearing compartment. A first seal system isolates the bearing compartment and has: a first runner; a second runner; an inner seal encircling the first runner; and an outer seal encircling the second runner. The inner seal has a static clearance with the first runner. The outer seal has a static clearance with the second runner, greater than the inner seal static clearance. The first runner has an inner portion cantilevered inward. The second runner has an outer portion cantilevered outward.

Abstract: A sensor includes a mount arranged along a sensor axis, an airfoil body fixed to the mount and having a first face and second face extending along the sensor axis, a heater element, and a temperature probe. The heater element and the temperature probe are positioned within the airfoil body and extend axially along the airfoil body. The airfoil body defines within its interior a pressure channel having an inlet segment extending between the heater element and the first face of the airfoil body to prevent ice formation and/or melt ice entrained within air traversing the pressure channel. Gas turbine engines, methods of removing ice or preventing ice formation, and methods of making sensors are also described.

Abstract: A turbine blade includes an aerofoil including a leading edge, a trailing edge, a first sidewall, a second sidewall, and an internal cooling circuit disposed within the aerofoil and configured to direct a cooling fluid within the aerofoil. The turbine blade includes at least one first recessed portion formed on the first sidewall proximal to a tip of the turbine blade. The first recessed portion is disposed proximal to and spaced apart from the trailing edge of the aerofoil. The first recessed portion includes a base surface, a first surface, and a second surface. The first recessed portion further includes at least one slot extending from the first surface to the internal cooling circuit. The slot is configured to allow a flow of the cooling fluid from the internal cooling circuit to the first recessed portion.

Abstract: A shroud hanger assembly is provided for hangers and shrouds defining dimensionally incompatible components such as those which are press or frictionally fit to engage one another. The shroud hanger assembly includes a multi-piece hanger and a shroud that is pinned to the hanger assembly by at least one axially extending pin and which locates the shroud relative to the hanger to control motion in one or both of circumferential (tangential) and radial directions relative to the engine.

Abstract: A component for a gas turbine engine. The component includes a body. The body has an exterior surface abutting a flowpath for the flow of a hot combustion gas through the gas turbine engine. Further, the body defines a cooling passageway within the body to supply cool air to the component. The component includes a leading face and a trailing face defining a trench therebetween on the exterior surface. The body defines a plurality of cooling holes extending between the cooling passageway and a plurality of outlets defined in the trench such that the trench is fluidly coupled to the cooling passageway. Additionally, the leading face and trailing face are each tangent to at least one of the plurality of outlets. The trench directs the cool air along a contour of the component.

Abstract: A turbomachine turbine casing that extend around an axis and includes an annular wall and a cooling device. The annular wall is provided with a casing hook which extends in radial protrusion from an inside of the annular wall. The casing hook allows a mounting, on the turbomachine turbine casing, of ring segments disposed circumferentially end to end around the axis. The cooling device includes a collector duct intended to convey cooling air, the collector duct extending circumferentially around the annular wall. The collector duct has a cooling air inlet and a cooling air outlet. The collector duct and the annular wall have a common portion, which delimits the collector duct and from which the corresponding casing hook extends.

Abstract: A device includes a molten metal pump and a metal-transfer conduit. A clamp may be used to attach the metal-transfer conduit to the pump. The pump has a pump base including an indentation configured to receive the metal-transfer conduit and align the pump outlet with the transfer inlet. The pump outlet may be formed in the indentation and preferably near the center of the indentation in order to better align with the transfer inlet. As the pump operates it moves molten metal through a pump outlet that is in communication with a transfer inlet in the metal-transfer conduit. The molten metal enters the transfer inlet, moves upwards in a passage in the metal-transfer conduit, and out of a transfer outlet.

Abstract: A seal assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, a first side plate, a second side plate and a backing plate that extend circumferentially about an assembly axis. A first brush seal and a second brush seal are positioned on opposite sides of the backing plate such that the first brush seal is between the first side plate and the backing plate and such that the second brush seal is between the second side plate and the backing plate. The first brush seal is dimensioned to establish a first sealing relationship with a first gas turbine engine component. The second brush seal is dimensioned to establish a second sealing relationship with a second gas turbine engine component. A method of assembly is also disclosed.

Abstract: A gas turbine engine has an accessory gearbox disposed outside of a bypass channel and connected to a housing part, which radially delimits the bypass channel, in a connection region near the housing part and in a connection region far from the housing part. A connecting element is provided between the housing part and the connection region far from the housing part. A longitudinal axis of the connecting element includes an angle in the range of 75° to 115° with a vertical axis of the accessory gearbox. The connecting element can vary a distance between the far connection region and a connection point of the connecting element on the housing part such that deformation of the housing part and a resulting position change of the connection point cause a lesser deflection of the accessory gearbox than a deflection with an unchanged length of the connecting element.

Abstract: A pump in which an electric motor which is connected to a rotor provided with at least one pump vane is integrated into a pump casing. The electric motor is a ring motor surrounding at least a portion of a fluid flow path through the pump. A stator is arranged internally in an intermediate section of the pump casing and surrounds the rotor. The rotor, which is supported in the pump casing, is cylinder-shaped and forms an intermediate portion of the fluid flow path, and the at least one pump vane is attached internally in the rotor.

Abstract: A storable fan includes a fan head, a support rod and a base that are connected detachably. A first accommodating groove and a second accommodating groove are formed in the base, and the storable fan has a used state and a stored state. In response to the used state of the storable fan, the fan head, the support rod and the base are connected sequentially. In response to the stored state of the storable fan, the fan head is stored in the first accommodating groove, and the support rod is stored in the second accommodating groove. The fan head, the support rod and the base are connected detachably, for ease of detachment of the storable fan. Both the fan head and the support rod can be stored in the base. The storage process can be accomplished without detaching such fasteners as screws and nuts or by only using few fasteners.

Abstract: An article includes a gas turbine engine component that has a ceramic matrix composite (CMC) body and a fiber layer circumscribing a cavity. There is a ceramic insert incorporated into the CMC article body, the insert bordering the cavity.