Abstract: A pre-diffuser and exit guide vane (EGV) system for a gas turbine engine includes an annular EGV assembly containing a number of guide vanes and having an annular opening bounded by a radially inner annular sealing surface at a first radius and a radially outer annular sealing surface at a second radius. First and second seals substantially matching the first and second radii respectively join the EGV assembly to an annular pre-diffuser having an annular opening bounded by radially inner and outer annular sealing surfaces at substantially the first and second radii. The seals seal the inner sealing surface of the EGV assembly to the inner sealing surface of the pre-diffuser and the second seal seals the outer sealing surface of the EGV assembly to the outer sealing surface of the pre-diffuser, such that the EGV assembly annular opening is in fluid communication with the annular opening of the pre-diffuser.

Abstract: A combustion liner includes air guiding caps which are respectively engaged to a mounting member and are turned in a flow direction of air so as to collect a fluid flowing around the combustion liner and feed it to the combustion liner, thereby smoothly introducing cooling air into the combustion liner. The combustion liner includes a plurality of through-holes which are formed in a surface of the combustion liner; and a plurality of air guiding caps provided on the combustion liner in plural rows arranged at regular intervals in a circumferential direction. With the above configuration, the combustion liner can instantaneously cope with irregular air flowing around the combustion liner to effectively introduce the air into the combustion liner, and can be varied in position and direction for the purpose of easy maintenance thereof.

Abstract: A method for repairing an air cycle machine compressor housing includes removing a journal bearing support sleeve in an air cycle machine compressor housing, positioning a cylindrical insert within the air cycle machine compressor housing, wherein the cylindrical insert has an outer diameter greater than an outer diameter of at least one portion of the removed journal bearing support sleeve, an inner diameter less than an inner diameter of at least one portion of the removed journal bearing support sleeve, and a length greater than a length of the removed journal bearing support sleeve, welding the cylindrical insert to the air cycle machine compressor housing, and machining the welded cylindrical insert to form a replacement journal bearing support sleeve.

Abstract: A turbine bucket according to various embodiments includes: a base; a blade coupled to the base and extending radially outward from the base, the blade including: a body having: a pressure side; a suction side opposing the pressure side; a leading edge between the pressure side and the suction side; and a trailing edge between the pressure side and the suction side on a side opposing the leading edge; a plurality of radially extending cooling passageways within the body; and at least one bleed aperture fluidly coupled with at least one of the plurality of radially extending cooling passageways, the at least one bleed aperture extending through the body at the trailing edge; and a shroud coupled to the blade radially outboard of the blade.

Abstract: A turbine blade has a body enclosing a labyrinth of internal channels for circulation of coolant received through an inlet integrally formed in terminal portion of blade root. The labyrinth includes; inlet arranged on an axially upstream face of terminal portion leading to an upstream duct portion having first section adjacent the inlet and a second section axially downstream of first, second section having reduced cross section compared to first section. Leading edge passage intersects first section and extends through blade body towards the tip. Main blade passage intersects second section. Trailing edge passage intersects downstream duct portion which is in axial alignment with but separate from second section and channel connects second section with the downstream duct portion. Channel has reduced cross section compared to second section and downstream duct portion. The inlet has an inverted keyhole shape with cross section extends through upstream duct portion first section.

Abstract: A geared architecture for a gas turbine comprising an output shaft for connection with a fan, an input shaft and a gearbox connecting the input shaft with the output shaft. The gearbox has a forward planet carrier plate supported by a forward radially fixed bearing structure and a rearward planet carrier plate supported by a rearward radially fixed bearing structure. By supporting the carrier plates on radially fixed bearing structures the planet carriers can rotate about their own axis to lower vibration and mesh forces within the gearbox.

Abstract: A compressor impeller for an Auxiliary Power Unit (APU) includes a hub including a plurality of splitter blades interposed between a plurality of main blades. Each of the plurality of splitter blades and the plurality of main blades include a first surface and a second surface. The first surface and the second surface of the plurality of splitter blades are defined as a set of X-coordinates, Y-coordinates and Z-coordinates set out in Table S-1 and S-2 scaled by a desired factor. The X-coordinate being in an axial direction, the Y-coordinate being in a first radial direction and the Z-coordinate being in a second radial direction transverse to the first radial direction. Each of the plurality of splitter blades includes a contour between the tip and the leading edge. An auxiliary power unit and method are also disclosed.

Abstract: An electronic begin of regulation (EBOR) control system and method is disclosed for a hydraulic motor of a machine having an engine for producing power and a track system for moving. The EBOR system includes a flow source, variable displacement motor, pressure sensor and control unit. The operator sets a pressure setpoint. The flow source generates flow in a loop with the motor. The pressure sensor senses loop working pressure. The control unit adjusts motor displacement based on comparisons between the pressure setpoint and sensed loop working pressure. The flow source can be bidirectional, and different pressure sensors can be used depending on the direction. The pressure setpoint can be varied during operation, and the control unit can adjust the displacement of the motor based on comparisons between the latest pressure setpoint and the loop working pressure sensed by the appropriate pressure sensor.

Abstract: Described is a modular linear actuator for use in an aerospace application, comprising: a piston housing having a closed end and an open end; a piston rod slideable within an interior of the piston housing between an extended position and a compressed position, the piston rod having a first end proximal to the closed end of the piston housing and a second end distal to the closed end of the piston housing; an attachment mechanism for removably attaching a lug end to the closed end of the piston housing, the lug end for attaching the actuator to a first component; an attachment mechanism for removably attaching a rod end to the second end of the piston rod, the rod end for attaching the piston rod to a second component; and, a piston head removably attached to the first end of the piston rod, the piston head for providing a snubbing engagement with the closed end of the piston housing.

Abstract: A stationary blade includes a main unit having a hollow blade structure formed from a metal plate by plastic forming. The stationary blade includes a blade tail section. In a blade tail upper portion, the metal plate has a concave-shaped recess and a rib formed on an inner surface side thereof and the metal plate further has slits formed by slitting on a blade pressure side thereof, so that droplets affixed on a blade surface can be guided into an inside of the hollow blade when the blade tail section is joined to the hollow blade main unit. The recess in the metal plate is covered so as to be lidded by a suction-side protrusion of a suction-side metal plate from a blade suction side to thereby form a hollow blade tail section. The metal plates are welded together to the main unit.

Abstract: An airfoil according to an exemplary aspect of the present disclosure includes, among other things, an airfoil section having an external wall and an internal wall. The internal wall defines a first reference plane extending in a spanwise direction and through a thickness of the internal wall. A first cavity and a second cavity are separated by the internal wall. A plurality of crossover passages within the internal wall connects the first cavity to the second cavity. Each of the plurality of crossover passages defines a passage axis. The plurality of crossover passages are distributed in the spanwise direction and arranged such that the passage axis of each of the plurality of cooling passages intersects a surface of the second cavity. The plurality of crossover passages include a first set of crossover passages and a second set of crossover passages positioned on opposite sides of the first reference plane.

Abstract: A heat shield (44) for an external component, such as a gearbox (42), of a gas turbine engine (20) for limiting heat transfer from the engine (20) to the external component is disclosed. The heat shield (44) may be formed to the shape of the gearbox (42) to reduce the geometric envelope of the gearbox (42) and heat shield (44). The heat shield (44) may be formed by a thin thermal insulation core (50) surrounded by a metal sheet (51). The small thickness of the heat shield (44) also reduces the geometric envelope of the heat shield (44). Since no extra equipment is needed to provide cooling fluid to the gearbox (42), the heat shield (44) reduces the overall weight of the gas turbine engine (20) as well.

Abstract: A flow control device for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a seal body having a radially inner surface and a radially outer surface and at least one stand-up protruding from the radially outer surface and configured to seal an interrupted surface.

Abstract: Hub assembly and propeller blade assemblies incorporating partial hub assembly having a backing plate with a set of partial root seats and a set of clamps selectively operably couplable to the backing plate with each clamp defining a second partial root seat and wherein when a clamp is coupled to the backing plate a root seat is formed, propeller blades having roots are received within the root seats.

Abstract: A gas turbine engine component is provided. The gas turbine engine component comprises a main body having a leading edge and a leading edge wall including an elongated transition portion extending between the leading edge and a proximate flowpath surface of the main body. The elongated transition portion has an axial length that is greater than a radial height. A gas turbine engine is also provided.

Abstract: A gas turbine includes at least one rotor assembly and at least one compressor casing. The compressor casing has at least one inner compressor casing chamber for arranging the rotor assembly and at least one outer compressor casing chamber for tempering the compressor casing. The inner and outer compressor casing chambers are separated from each other by a separating casing wall. The outer compressor casing chamber has at least one boundary casing wall. The boundary casing wall and the separating casing wall are oppositely spaced such that the outer compressor casing chamber is formed. The boundary casing wall has at least one inlet opening for leading in an inlet tempering gas flow with tempering gas into the outer compressor casing chamber such that a tangential material temperature variation of the compressor casing is reduced in comparison to a non tempered compressor casing.

Abstract: The invention relates to an impeller for an axial fan, having an impeller body, which has an outer impeller shell and a carrier disc having a hub for connection for conjoint rotation to a drive shaft. A multiplicity of radially outward-pointing blades, which each have a blade root and a vane, is arranged on the carrier disc. Each blade root has a fastening portion accommodated with positive engagement between two fastening segments each arranged opposite one another on both sides of the carrier disc. The two opposite fastening segments and the carrier disc each have at least two through-holes for accommodating a long sleeve and a short sleeve. The fastening portion can be clamped firmly between the two opposite fastening segments with the aid of screw bolts, in each case inserted through the sleeves, and nuts, wherein each blade root is guided in a respective recess of the carrier disc.

Abstract: A non-ducted tail rotor comprising a hub and at least five blades, each of the blades extending to a free end that, in rotation, describes a circle presenting a given “maximum” radius. The hub is rigidly secured to a drive shaft, the hub comprising a hollow circular body centered on an axis of rotation, the body presenting an “internal” radius between the axis of rotation and an outer periphery of the body, the internal radius lying in the range 0.2 times to 0.4 times the maximum radius, each blade presenting a root extended by an airfoil element projecting from the body, extending from the root to the free end, the root being swivel-hinged to the outer periphery about a pitch axis.

Abstract: A turbine shroud adapted for use in a gas turbine engine includes a plurality of metallic carrier segments and a plurality of blade track segments mounted to corresponding metallic carrier segments. Cooling flow inserts direct cooling air onto the blade track segments to cool the blade track segments when exposed to high temperatures in a gas turbine engine.

Abstract: A method for repairing a cabin air compressor outlet housing includes removing a journal bearing support sleeve in a cabin air compressor outlet housing, positioning a cylindrical insert within the cabin air compressor outlet housing, wherein the cylindrical insert has an outer diameter greater than an outer diameter of at least one portion of the removed journal bearing support sleeve, an inner diameter less than an inner diameter of at least one portion of the removed journal bearing support sleeve, and a length greater than a length of the removed journal bearing support sleeve, welding the cylindrical insert to the cabin air compressor outlet housing, and machining the welded cylindrical insert to form a replacement journal bearing support sleeve.