Abstract: The present invention pertains to a fan assembly for a refrigerator. Said assembly comprises a fan with a first and a second outer wall at two ends along axial direction of said fan. Said outer walls extend perpendicular to said axial direction of said fan. Said fan assembly comprises a wall element which delimits an evaporator within said refrigerator. Said wall element has a fan mounting opening with projecting edges in the direction of said fan, said fan assembly further comprising an isolator and a locking element.

Abstract: A rotor for a gas turbine engine includes a central wheel and a plurality of blades that extend outwardly from the central wheel. The blades are non-uniform to reduce flutter and forced response effects induced during operation of a gas turbine engine including the rotor.

Abstract: A power turbine unit includes a turbine housing, an exhaust duct, a turbine wheel with blades positioned in the exhaust duct, a shaft rigidly connected to the turbine wheel and rotatably supported in the housing, and an oil sealing system. The oil sealing system includes a sealing arrangement positioned in the vicinity of the turbine wheel for preventing oil from escaping from the turbine housing along the shaft to the exhaust duct. The oil sealing system further includes a buffer gas duct that is arranged to supply exhaust gas from the exhaust duct to the sealing arrangement for pressurizing the sealing arrangement.

Abstract: An airfoil has an airfoil structure that defines a cooling passage for directing a cooling medium through the airfoil structure. A swirl structure is operatively associated with the cooling passage and configured to impart a tangential velocity to the cooling medium flowing through the cooling passage. An airfoil has an airfoil structure that defines a first cooling passage and a second cooling passage for directing cooling medium through the airfoil structure, each cooling passage having a swirl structure that imparts tangential velocity on the cooling medium flowing through the associated cooling passage. A method of making an airfoil that includes forming an airfoil structure that defines a cooling passage for directing a cooling medium through the airfoil structure and forming a swirl structure that is operatively associated with the cooling passage and imparts tangential velocity to the cooling medium flowing through the cooling passage.

Abstract: A barrier coating for isolating a metallic support component from a composite component in a gas turbine engine is provided. The barrier coating may be applied to the metallic support component so that when the ceramic component is mounted on the metallic support component the barrier coating is engaged.

Abstract: A distributor device for distributing cooling air within a gas turbine engine, the device including a base mountable adjacent an inlet for air to be distributed; and a deflector supported by the base and in fluid communication with the air inlet, the deflector being configured to direct air from the air inlet in a plurality of directions within the engine; wherein the deflector includes one or more deflecting surfaces curvilinearly configured to direct the air differentially in a plurality of desired directions within the engine. In embodiments the deflecting surface(s) is/are curved and are so configured such that air from the air inlet is directable either: (i) in directions of travel in each of a plurality of desired different, non-parallel directions within the engine; or (ii) in each of a plurality of desired different directions within the engine with different flow rates.

Abstract: A fan structure comprising a base, a fan inlet funnel coupled to the base, the fan inlet funnel having an inner surface for conducting air flow into a fan inlet and an outer surface and a plurality of external ribs coupled to the outer surface of the fan inlet funnel.

Abstract: An airfoil may be provided that includes a CMC body and a support piece. The CMC body has an inner surface that defines a chamber within the CMC body. The support piece may be positioned within the chamber of the CMC body. The support piece comprises a channel in a surface of the support piece, the surface being in contact with the inner surface of the CMC body. The channel and the inner surface of the CMC body define a passageway for a cooling fluid. The passageway may wind about the circumference of the CMC body and extend along the span of the airfoil. Outlets may be positioned through the CMC body allowing fluid communication between the passageway and the outer surface of the CMC body.

Abstract: A turbofan engine has a fan having a circumferential array of fan blades. A fan case encircles the fan. There is at least one compressor section, a combustor, and at least one turbine section. The fan case comprises a containment case and a cartridge liner carried therein. A ballistic liner encircles at least a portion of the cartridge liner and is attached thereto.

Abstract: A mid-turbine frame for a gas turbine engine includes an inner frame case defining a sealed torque box cavity. The mid-turbine frame also includes multiple spokes protruding radially outward from the inner frame case. The mid-turbine frame also includes at least one service line connected to the inner frame case.

Abstract: A tool and method for inserting an externally threaded object into a threaded receiving hole and removing and externally threaded object from the receiving hole. The tool is provided with an outer body that has a holding portion to hold the externally threaded object during insertion or removal. The holding portion may be a thread that corresponds with the thread of the externally threaded object. The tool also has a tightening body inside the outer body that has an engagement portion for engaging a corresponding engageable portion of the externally threaded body. The tightening body is rotated within the outer body to tighten or loosen the externally threaded body. During insertion or removal, the externally threaded body is securely held by the holding portion of the outer body.

Abstract: An airfoil includes an airfoil structure defining a damping network that includes a first cavity, a second cavity, a flow passage connecting the first and second cavities. The airfoil further includes a damping material configured to flow through the damping network. A method of forming an airfoil includes forming an airfoil body having a damping network that includes a first cavity, a second cavity, and a flow passage connecting the first and second cavities. The method further includes adding a damping material configured to flow through the damping network.

Abstract: A turbofan gas turbine engine for use in an aircraft includes a fan, an engine core, and a cleaning system. The fan and engine core cooperate to provide thrust for an aircraft when in use but may suffer performance degradation when dirty. The cleaning system is configured to conduct a cleaning agent from a supply into the turbofan gas turbine engine to clean the turbofan gas turbine engine.

Abstract: A conical impeller with a hub that has a conical surface extending into the interior of the impeller. The hub has spiral, slanting arms which are attached or integrally formed with a plurality of curved blades. The blades can be connected at the bottom by a ring. The intersection of the conical surface of the hub with the blade forms an upward path for fluids and their entrained particles or gases which have been brought into the interior of the impeller to effectively completely be ejected. The discharge edges of the blades and/or the conical surface of the hub may have openings for discharging gas into the fluid. The impeller imparts low shear to the fluid and its components, and the shear is independent or only depends slightly on the size of the impeller. The impeller minimizes or eliminates particle agglomeration and fouling of the impeller. The efficiency of and flow pattern produced by the impeller means that containers don't require the use of baffles.

Abstract: Seal assemblies for reducing leakage between components of turbomachinery include a metallic shim, at least a pair of non-metallic end blocks, and ceramic fiber positioned between the shim and the end blocks. The shim may be mechanically coupled with the end blocks such that the metallic shim, end blocks and ceramic fiber are coupled. The end blocks account for misalignment of turbine components by ensuring sealing engagement of the seal to the components. The end blocks may be a ceramic or glass material, and the ceramic fiber may be a high temperature woven ceramic fiber. The ceramic fiber and/or the end blocks protect the metallic shim from reaching harmful temperatures during use of the seal, such as use in high temperature turbines including CMC components.

Abstract: A belly band seal for use in a multi-stage turbomachine having plural rotor disks includes a seal strip positionable in a space between a pair of arms defined by opposing portions of adjoining rotors. The seal strip includes opposite edges for locating in respective slots in end faces of said pair of arms. The belly band seal further includes an anti-rotation structure disposed on a radially inner surface of the seal strip. The anti-rotation structure is configured as a cantilever having a pivoted end fixed to the radially inner surface and a free end comprising a radially inwardly extending engagement member for removably positioning in a radial recess in one of the arms. The cantilever is configured so as to urge the engagement member toward the radial recess by spring action. The radial recess is configured to constrain a tangential movement of the engagement member upon being positioned therein.

Abstract: A fan case for use in a gas turbine engine of an aircraft includes an outer shroud and a liner extending along the outer shroud. The fan case provides a protective band that blocks fan blades from being thrown out of the fan case in case of a blade-off event in which a fan blade is released during operation of the gas turbine engine.

Abstract: A turbine blade airfoil (25, 31R, 31M, 31T, 72) comprising an outer surface shape defined by Cartesian coordinates of successive transverse profiles at radial increments as set forth in Tables 1a to 1k, wherein each table defines a transverse sectional profile characterized by a smooth curve connecting the coordinates, and the surface shape comprises a smooth surface connecting the sectional profiles. The blade may include a tip shroud with edge profiles defined by Cartesian coordinates set forth in Table 2a and 2b. A gusset/fillet may be provided between the blade airfoil and the tip shroud, with a planar diagonal surface over most of a diagonal bracing area of the gusset/fillet.

Abstract: An airfoil for a gas turbine engine includes an airfoil body that extends in a radial direction from a support. The airfoil body has pressure and suction side walls joined at leading and trailing edges to provide an exterior airfoil surface. A chord-wise direction extends between the leading and trailing edges and a thickness direction transverse to chord-wise direction and extending between the pressure and suction side walls. Cooling passages extend from the support into the airfoil body. The cooling passages include adjacent passageways in the thickness direction and are separated by a chord-wise wall. One of the adjacent passageways is adjacent to another passageway in the chord-wise direction and is separated by a rib in the thickness direction. The rib is discontinued at a location along the radial direction to provide an opening that fluidly connects one of the adjacent passageways to the other passageway.

Abstract: One exemplary aspect of this disclosure relates to an assembly for a gas turbine engine having an engine axis. The assembly includes a case including an integrally formed projection configured to extend transverse to the engine axis. The assembly further includes an engine component including a flange configured for contact with the projection to limit motion of the component along the engine axis.