Abstract: Turbine wheels, turbine engines, and methods of forming the turbine wheels are provided herein. In an embodiment, a turbine wheel includes a rotor disk and a plurality of turbine blades. Each turbine blade is operatively connected to the rotor disk through a blade mount, which is bonded to the rotor disk. The blade mount and the rotor disk have a fore surface on a higher pressure side thereof and an aft surface on a lower pressure side thereof. The blade mount includes a blade attachment surface that extends between and connects the fore surface and the aft surface. The turbine blade extends from the blade attachment surface. A gap is defined between adjacent blade mounts. The gap separates the blade mounts and extends into the rotor disk. The gap includes a pocket that has a fore opening in the fore surface. A pocket seal is disposed in the pocket.

Abstract: Turbine wheels, turbine engines, and methods of fabricating the turbine wheels are provided. An exemplary method includes fabricating a turbine wheel that includes a rotor disk and a plurality of turbine blades operatively connected to the rotor disk through a blade mount. The method includes locating a cooling passage within a blade mount preliminary configuration and a cooling inlet on a surface of the blade mount preliminary configuration. A rotor disk bonding surface geometry and a blade mount bonding surface geometry are designed based upon a stress analysis of the turbine wheel and locations of the cooling passage and cooling inlet. A rotor disk production configuration and a blade mount production configuration are generated based upon the preliminary configurations. A blade mount and a rotor disk are formed based upon the production configurations. A blade ring including a plurality of blade mounts is formed and bonded to the rotor disk.

Abstract: The invention relates to an assembly for securing a fastening element to a first component, wherein the first component has a passage opening for a shaft of the fastening element, said assembly comprising a securing element, which reaches around the shaft of the fastening element, wherein a head part of the fastening element and the securing element are arranged on opposite sides of the first component and the shaft of the fastening element engages in a receptacle of a second component for the frictional and/or interlocking connection of the two components. According to the invention, the securing element is pre-fastened to the second component before a first connection of the first component to the second component and is separated from the second component and reaches around the shaft of the fastening element after a first release of the connection between the first component and the second component.

Abstract: An angular coupling for fastening a first component, especially a mounting part in a vehicle, to a second component, especially a vehicle body, which comprises a coupling bolt with a head and a coupling socket in which the coupling bolt can be pivoted in a plane angle portion while the head of the coupling bolt is locked releasably or not releasably. The coupling socket comprises an arch with a push-in opening, a fastening collar surrounding the push-in opening having a not round shape with a longitudinal axis and a shorter transverse axis, wherein the arch encloses a pivoting plane generated by the longitudinal axis of the push-in opening and the push-in direction, which defines a variable angular orientation of the lockable coupling bolt in a plane angle portion which is limited at the maximum by an inner wall of the arch.

Abstract: A dual zone auxiliary climate control system for a vehicle includes an evaporator, a heater core having a first zone and a second zone, a first zone mode door downstream from the first zone of the heater core, a second zone mode door downstream from the second zone of the heater core and a blower. The blower forces air through the evaporator and the heater core toward the first zone mode door and the second zone mode door. A method of providing a dual zone auxiliary climate control system is also disclosed.

Abstract: A turbine blade with an integral flow meter is provided. The turbine blade includes a trailing edge and a leading edge opposite the trailing edge. The turbine blade includes a plurality of cooling passages each having a respective inlet in fluid communication with a source of cooling fluid to receive a cooling fluid. The turbine blade includes a plurality of flow meters, with at least a respective one of the plurality of flow meters associated with a respective one of the plurality of cooling passages at the respective inlet.

Abstract: Turbine wheels, turbine engines, and methods of fabricating the turbine wheels are provided. An exemplary method includes fabricating a turbine wheel that includes a rotor disk and a plurality of turbine blades operatively connected to the rotor disk through a blade mount. The method includes locating a cooling passage within a blade mount preliminary configuration and a cooling inlet on a surface of the blade mount preliminary configuration. A rotor disk bonding surface geometry and a blade mount bonding surface geometry are designed based upon a stress analysis of the turbine wheel and locations of the cooling passage and cooling inlet. A rotor disk production configuration and a blade mount production configuration are generated based upon the preliminary configurations. A blade mount and a rotor disk are formed based upon the production configurations. A blade ring including a plurality of blade mounts is formed and bonded to the rotor disk.

Abstract: A coupling element of a two-part plug-in coupling has a head section from which a female connection structure extends perpendicularly in an installation direction of the coupling element, with a locking web projecting inwards on an inner side so that a male bolt element can be inserted into the connection structure opposite to the installation direction and can be locked there, or a male cylinder-like connection structure extends so that the male cylinder-like connection structure can be inserted in a female receiving element and can be locked there. The coupling element has an integral locking structure which has a circumferential, or a plurality of locking webs which, together with the head section, form an installation gap for receiving the component, so that the female or the male coupling element can be locked in the opening of the component with a relative movement in installation direction between coupling part and component.

Abstract: A turbine blade with an integral flow meter is provided. The turbine blade includes a trailing edge and a leading edge opposite the trailing edge. The turbine blade includes at least one cooling passage defined internally within the turbine blade, and the at least one cooling passage is in fluid communication with a source of cooling fluid via an inlet to receive a cooling fluid. The turbine blade also includes at least one flow meter formed within the turbine blade at the inlet that supplies the cooling fluid to the at least one cooling passage.

Abstract: A motor vehicle includes a motor compartment, a passenger compartment and a firewall separating the motor compartment from the passenger compartment. The motor vehicle also includes a heating, ventilation and air conditioning system. That heating, ventilation and air conditioning system includes an HVAC inlet subassembly and an HVAC air distribution subassembly in the passenger compartment and a transition duct in the motor compartment directing an airstream from the HVAC inlet subassembly to the HVAC air distribution subassembly.

Abstract: Turbine wheels, turbine engines, and methods of forming the turbine wheels are provided herein. In an embodiment, a turbine wheel includes a rotor disk and a plurality of turbine blades. Each turbine blade is operatively connected to the rotor disk through a blade mount, which is bonded to the rotor disk. The blade mount and the rotor disk have a fore surface on a higher pressure side thereof and an aft surface on a lower pressure side thereof. The blade mount includes a blade attachment surface that extends between and connects the fore surface and the aft surface. The turbine blade extends from the blade attachment surface. A gap is defined between adjacent blade mounts. The gap separates the blade mounts and extends into the rotor disk. The gap includes a pocket that has a fore opening in the fore surface. A pocket seal is disposed in the pocket.

Abstract: Turbine wheels, turbine engines, and methods of forming the turbine wheels are provided herein. In an embodiment, a turbine wheel includes a rotor disk and a plurality of turbine blades. Each turbine blade is operatively connected to the rotor disk through a blade mount, which is bonded to the rotor disk. The blade mount and the rotor disk have a fore surface on a higher pressure side thereof and an aft surface on a lower pressure side thereof. The blade mount includes a blade attachment surface that extends between and connects the fore surface and the aft surface. The turbine blade extends from the blade attachment surface. A gap is defined between adjacent blade mounts. The gap separates the blade mounts and extends into the rotor disk. The gap includes a pocket that has a fore opening in the fore surface. A pocket seal is disposed in the pocket.

Abstract: An airfoil for a rotor blade in a gas turbine engine includes a first side wall and a second side wall joined to the first side wall at a leading edge and a trailing edge. The airfoil further includes a tip cap extending between the first and second side walls such that the tip cap and at least portions of the first and second side walls form a blade tip and an internal cooling system. The internal cooling system includes a leading edge cooling circuit, a central cooling circuit, and a trailing edge cooling circuit. Each of the internal passages within the leading edge cooling circuit, the central cooling circuit, and the trailing edge cooling circuit is bounded in the radial outward direction with a surface that has at least one escape hole or that is positively angled in the radial outward direction relative to a chordwise axis.

Abstract: The present disclosure describes a spring connection element, by means of which at least two components can be connected to each other by means of a claw-fit in at least one component opening. The spring connection element is characterized by the following features: a spiral spring-like wire coil with a first and a second end, said coil comprising a plurality of axially spaced windings, a spiral collar which extends radially beyond a circumference of the wire coil and which is arranged at the first end of the wire coil, and a central traction element protruding radially into the wire coil, which is arranged at the second end of the wire coil, which does not extend axially beyond the wire coil, and by means of which the spring connection element can be pulled into a component opening substantially rotation-free.

Abstract: A panel and defrost plenum includes a manifold section, an air feed section and a branch section. The manifold section includes a first air distribution door, a second air distribution door and an optional third air distribution door. The manifold section also includes at least one actuator to displace the first air distribution door, the second air distribution door and the optional third air distribution door if present, between multiple operating positions. The air feed section is located upstream of the manifold section and functions to deliver an airstream past a package restriction to the manifold section. The branch section is downstream from the manifold section. A related method of routing an airstream past a package restriction is also disclosed.

Abstract: An airfoil for a rotor blade in a gas turbine engine includes a first side wall and a second side wall joined to the first side wall at a leading edge and a trailing edge. The airfoil further includes a tip cap extending between the first and second side walls such that the tip cap and at least portions of the first and second side walls form a blade tip and an internal cooling system. The internal cooling system includes a leading edge cooling circuit, a central cooling circuit, and a trailing edge cooling circuit. Each of the internal passages within the leading edge cooling circuit, the central cooling circuit, and the trailing edge cooling circuit is bounded in the radial outward direction with a surface that has at least one escape hole or that is positively angled in the radial outward direction relative to a chordwise axis.

Abstract: An extension adapter of a plug-in coupling, with which a free space between a male coupling element and a female coupling element can be bridged in a connecting manner and which comprises the following features: a male coupling end which can be inserted into the female coupling element, a female coupling end in which the male coupling element can be received and which is connected to the male coupling end via an intermediate piece, and a locking element which is displaceably arranged in the axial direction of the extension adapter and with which, in a locking position surrounding the female coupling end, the release of a male coupling element from the female coupling end is prevented.

Abstract: A turbine blade and a radial turbine having at least one blade is provided. The turbine blade includes a trailing edge and a leading edge opposite the trailing edge. The turbine blade also includes a cooling passage defined internally within the turbine blade. The cooling passage is in fluid communication with a source of cooling fluid via a single inlet to receive a cooling fluid. The cooling passage diverges at a first point downstream from the single inlet into at least two branches that extend along the at least one blade from the first point to a second point near a tip of the leading edge and the cooling passage converges at the second point.

Abstract: A panel and defrost plenum includes a manifold section, an air feed section upstream from the manifold section and a branch section downstream from the manifold section. The air feed section delivers an airstream past a HUD package restriction to the manifold section. A related method of routing an airstream past a HUD package restriction is also disclosed.

Abstract: Turbine wheels, turbine engines, and methods of fabricating the turbine wheels are provided. An exemplary method includes fabricating a turbine wheel that includes a rotor disk and a plurality of turbine blades operatively connected to the rotor disk through a blade mount. The method includes locating a cooling passage within a blade mount preliminary configuration and a cooling inlet on a surface of the blade mount preliminary configuration. A rotor disk bonding surface geometry and a blade mount bonding surface geometry are designed based upon a stress analysis of the turbine wheel and locations of the cooling passage and cooling inlet. A rotor disk production configuration and a blade mount production configuration are generated based upon the preliminary configurations. A blade mount and a rotor disk are formed based upon the production configurations. A blade ring including a plurality of blade mounts is formed and bonded to the rotor disk.