Abstract: A fan rotor has a hub, and a plurality of axial flow fan blades extending radially outwardly of the hub. A radial compressor impeller is positioned radially inwardly of the fan blades. The radial compressor impeller has an upstream inlet which extends generally in an axial direction defined by an axis of rotation of the hub. The radial flow compressor impeller has an outlet that extends radially outwardly of the inlet, and into a supply passage for supplying air to a core engine. An engine is also disclosed.

Abstract: An airfoil includes an airfoil body that has a leading edge and a trailing edge and a first sidewall and a second sidewall that is spaced apart from the first sidewall. The first sidewall and the second sidewall join the leading edge and the trailing edge and at least partially define a cavity in the airfoil body. A damper member is enclosed in the cavity and is free-floating within the cavity.

Abstract: The invention relates to a housing (1) of a radial flow compressor, comprising an intake pipe (4), a compressor duct (7) and an outlet pipe (5), wherein the housing comprises a housing body (basic construction) comprising at least an upper housing member (3) and a lower housing member (2) made of a fiber-reinforced thermoplastic polymer composition, and wherein the members (2, 3) are made, assembled together and fixed to each other in an integrated 2-step injection molding process.

Abstract: A wind turbine having a set of curved blades mounted on a central rotatable huh. Each of the blades has a defined pitch angle, to a rotational axis of the hub, along the blade from the hub to the tip. A curve is provided on the wind contact surface along each of the blades over the blade surface from the leading edge of the blade to the trailing edge of the blade by an amount between about 6 and about 24 degrees. The defined pitch angle from any point along the leading edge of the blade being defined by the arc-sine of a ratio of blade velocity to apparent wind velocity, with a variance of ±30 percent of the complementary angle to the arc-sine; and apparatus for varying the velocity of the blade to control power output so that it is within fifteen percent of maximum obtainable power of the blade most distant from the hub.

Abstract: A gas turbine nozzle section of a gas turbine may include an inner endwall with a leading edge. A serpentine passage may be configured substantially within the leading edge. The serpentine passage may have an inlet and an outlet. Air may be received at the inlet and exhausted at the outlet, cooling the leading edge.

Abstract: A sealing plate for sealing a gap between two primary sealing plates is provided. The sealing plate has a sealing portion and a connector portion, wherein the sealing portion has a width which is greater than a width of the connector portion. An apparatus for sealing a gap between two structural components of a turbine, the apparatus including a plurality of primary sealing components, and at least one sealing plate is also provided, as is a turbine having a plurality of structural components with a gap between said structural components, wherein the gap is sealed by a plurality of sealing components, the sealing components comprising a plurality of primary sealing components and at least one sealing plate.

Abstract: A product and method for use with a turbocharger system may include a housing with a shaft rotatably supported by the housing. The shaft may extend in an axial direction. A bearing assembly may support the shaft in the housing. A wheel may be connected to the shaft and may rotate relative to the housing. A clearance opening may be defined in the axial direction between the wheel and the housing. A thrust washer may be engaged with the bearing assembly. The thrust washer may have an outer circumference and may be movable relative to the housing. An efficiency washer may be disposed around the outer circumference of the thrust washer and may determine the clearance opening by defining a space within which the thrust washer moves relative to the housing in the axial direction.

Abstract: A turbine airfoil includes pressure and suction sidewalls extending along a span from a base to a tip. Spanwise spaced apart trailing edge cooling holes in the pressure sidewall end at corresponding spanwise spaced apart trailing edge cooling slots extending chordally substantially to the trailing edge. Each cooling hole includes in downstream serial cooling flow relationship, a curved inlet, a constant area and constant width metering section, and a spanwise diverging section leading into the trailing edge cooling slot, and a spanwise height substantially greater than a hole width through the cooling hole. A pressure sidewall surface of the pressure sidewall may be planar through the metering and diverging sections. The width may be constant through the metering and diverging sections. A raised floor may include a flat up ramp in the diverging section, a flat down ramp in the slot.

Abstract: An improved nozzle vane for a gas turbine engine, comprising a vane wall having inner and outer wall surfaces, the wall surfaces being spaced from one another to define a plurality of fluid passageways for a cooling medium; discreet cavities formed by interior wall members disposed between the inner and outer wall surfaces and within the fluid passageway for the cooling medium; a plurality of impingement cooling sleeves disposed in the discreet cavities defined by the inner and outer wall surfaces and by interior wall members; and a plurality of non-round, e.g., serrated, openings in each of the impingement cooling sleeves, with the openings being sufficient in size and number to accommodate the flow of a cooling media.

Abstract: An example turbomachine geared architecture support assembly includes a compliant member configured to hold a geared architecture within a turbomachine. The compliant member has a compliant section that permits rotation of the geared architecture relative to a fixed portion of the turbomachine. A stop limits rotation of the geared architecture relative to the fixed portion of the turbomachine.

Abstract: An airfoil for a gas turbine engine includes an airfoil body and a cooling circuit defined within the airfoil body. The cooling circuit includes at least a first cavity in fluid communication with a second cavity. A first portion of the first cavity extends between an outer diameter and an inner diameter of the airfoil body and a second portion of the first cavity extends across a space between a leading edge and a trailing edge of the airfoil body.

Abstract: A sealing assembly for use in a gas turbine engine having a disk arranged relative to an axis, the assembly including a circumferential groove defined in the disk and an annular wire seal positioned at least partially within the groove. The groove includes a first sidewall, a base portion adjoining the first sidewall, and a second sidewall adjoining the base portion opposite the first sidewall, wherein the second sidewall is angled in a range greater than 0° and less than 90° with respect to the axis.

Abstract: A core for a casting process includes a core body and a first cooling hole forming portion that extends from the core body. The core body includes a varying thickness along a length of the core body. The core body can include an undulating shaped section and can be a ceramic core body.

Abstract: An environmental control system, includes an air cycle machine for conditioning an interior space with cooling air, the air cycle machine including a fan coupled to a shaft that rotates about a shaft axis, the fan being located at a distal end of the air cycle machine; a speed sensor module having a speed sensor for sensing a rotational speed of the shaft; wherein the speed sensor module includes an outer portion having a first bore aligned on the shaft axis, an intermediate portion having a second bore aligned on the shaft axis, and an inner portion aligned on the shaft axis; and a diffuser assembly including a cylindrical assembly for ducting a first portion of the cooling air to an inlet side of the fan and for communicating a second portion of the cooling air directly to a discharge side of the fan without passing the inlet side.

Abstract: A turbomachine component includes a body having a first end that extends to a second end. One of the first and second ends includes a mounting element, and a mounting component. A cover plate is arranged at the one of the first and second ends to establish an interface region. The cover plate includes a mounting member configured to align with the mounting element, and a mounting portion configured to align with the mounting element. A fastener member is configured and disposed to cooperate with the mounting element and the mounting member to constrain the cover plate to the body along at least two axes with the interface region being devoid of a metallurgical bond.

Abstract: A turbomachine has a housing having a passage extending along an axis and an annular axially directed housing face extending radially from the passage. A shaft extending axially in the passage has an outer shaft surface radially spaced from an inner surface of the passage and forming therewith an annular axially extending gap. A radial impeller fixed to the shaft outside the housing has an axially directed and radially extending impeller face axially spaced from and confronting the radial housing face and forming therewith a radially extending gap opening into the axially extending gap. An impeller housing forms a flow space with the impeller outside the housing. The radial gap opens into the flow space. A plurality of spaced seals engaged in the radial gap between the radial faces of the housing and impeller fluidically separates the axial gap from the flow space.

Abstract: A compressor rotor includes a rotor body mounting a disk supporting an array of blades on a radially outer surface of the disk in a primary flow path. A radially inner portion of the disk is formed with an annular array of radially extending vanes adapted to move cooling air flowing in a secondary flow path from a radially-inward direction to an axial direction at a substantially center portion of said disk. Some of said radially-extending vanes have relatively longer radial lengths and some of the radially extending vanes having relatively shorter radial lengths to thereby provide a sufficient flow area while also lessening the formation of vortices along the vanes.

Abstract: An exemplary housing of a cooling fan includes a metallic base plate and a plastic bear seat. Clasps extend upwardly from the base plate. The bear seat is formed on the base plate via injection process. A bottom end of the bear seat directly contacts the base plate. The clasps are embedded in the bear seat.

Abstract: A fan shaft support assembly for a gas turbine engine includes first and second bearing assembles supported by a bearing support structure. The bearing support structure includes a first support including a first support end supporting the first bearing assembly and a second support including a second support end supporting the second bearing assembly. The first support end and the second support end are spaced apart to provide a preload on the first and second bearing assemblies.

Abstract: Embodiments of the present disclosure include a system having a turbine blade segment having a blade and a mounting segment coupled to the blade. The mounting segment is configured to couple to a slot in a rotor, and the mounting segment has a cavity extending radially into the mounting segment.