Abstract: An air cooled turbine airfoil such as a stator vane in which the airfoil is hollowed out and an insert is secured within the hollowed out section that produces sequential impingement cooling of the airfoil. The insert is formed from a plurality of plates bonded together outside of or inside of the airfoil to form a single piece insert with the cooling circuit. The plates are bonded together using TLP bonding process with sheets of boron placed between adjacent plates so that no excess material seeps out and into the cooling features formed with the plates. The cooling features of the plates are formed by photo-etching.

Abstract: A micro gas turbine engine in which the turbine rotor blades are formed as an integral bladed rotor with cooling air passages formed within the blades and the rotor disk by an EDM process. an adjacent stator vane includes an air riding seal with an air cushion supplied through the vanes to provide cooling, and where the air cushion is then passed into the turbine blades and rotor disk to provide cooling for the turbine blades. With cooling of the turbine blades, higher turbine inlet temperatures for micro gas turbine engines can be produced.

Abstract: A differential having four pinions supported for rotation on cross pins within a differential case. The differential employs a retainer system for securing the cross pins relative to the differential case. The retainer system can include a collar and a plurality of pin members.

Abstract: An air cooled turbine airfoil, such as a rotor blade, with a sequential impingement cooling circuit that provides a high level of cooling with a low amount of cooling air. The airfoil is formed of a spar and shell construction in which the spar is formed from a series of alternating layers that form the cooling circuit with the shell forming the gap for the impingement cooling channels. Two different layers form the impingement cooling channels with a third layer being a separation layer. The impingement cooling circuit includes a first impingement circuit to cooling a forward half of the pressure side wall, a second impingement cooling circuit to cool the aft half of the pressure side wall, and a third impingement cooling circuit to cool the entire suction side wall. The spent cooling air is collected and channeled through a series of exit holes in the trailing edge to discharge the cooling air form the airfoil.

Abstract: The present invention is a process for designing the internal cooling passages with these small scale features using a meshed solid model in a FEA program to perform the CFD analysis. Instead of modeling these small scale features (cooling holes, impingement holes, and turbulators) in the meshed FEA solid model, most of the small scale features are replaced by grid extraneous source terms in which the small scale feature is eliminated from the solid model and replaced with point source terms. The source terms can duplicate the effect of the feature within the analysis without requiring the complex analysis that such features would require in the analysis. Text files for each of the cooling holes, impingement holes and turbulators are inputted and then translated into grid extraneous source terms that include position, energy, and continuity. A conjugate CFD solver performs an analysis and produces new values for the thermal and boundary conditions.

Abstract: A vehicle with primary and secondary drivelines and a power take-off unit (PTU). The primary driveline has a first differential that is configured to distribute power to a first set of wheels. The PTU has a PTU input, a PTU output and a synchronizer for selectively de-coupling the PTU output from the PTU input. The secondary driveline is configured to distribute power to a second set of wheels and has a propshaft, a second differential, a pair of half-shafts and at least one torque transfer device (TTD). The propshaft transmits rotary power between the PTU output and an input of the second differential. The half-shafts are rotatably coupled to an output of the second differential and are configured to transmit rotary power to the second set of wheels. The at least one TTD is configured to selectively inhibit torque transmission through the second differential to the second set of wheels.

Abstract: A differential having four pinions supported for rotation on cross pins within a differential case. The differential employs a retainer system for securing the cross pins relative to the differential case. The retainer system can include a collar and a plurality of pin members.

Abstract: An overrunning torque transmitting device that employs a plurality of cone clutches and an overload mechanism for limiting the torque transmitted through the device in a predetermined rotational direction. A method for transmitting torque is also provided.

Abstract: A differential having four pinions supported for rotation on cross pins within a differential case. The differential employs a retainer system for securing the cross pins relative to the differential case. The retainer system can include a collar and a plurality of pin members.

Abstract: Two pairs of ribs define three intermediate cooling chambers. Each rib in each pair extends parallel to the other rib in the pair. The ribs in a first pair are non-parallel to the ribs in a second pair. A first rib from the first pair is positioned spaced toward the leading edge. A first rib of the second pair is then serially positioned spaced toward the trailing edge. A second rib of the first pair is then positioned toward the trailing edge relative to the first rib in the second pair. A second rib in the second pair is then positioned toward the trailing edge relative to the second rib in the first pair.

Abstract: A turbine component includes a coolant passage and a plurality of trip members that extend within the coolant passage. Each of the plurality of trip members includes an orientation relative to an expected flow direction through the coolant passage. At least three of the trip members have orientations that are different from each other. For example, the orientations of the trip members progressively transition along the length of the coolant passage.

Abstract: A die for forming a lost wax ceramic core allows the formation of non-parallel separating spaces between adjacent portions of the core. The core will eventually form cooling channels in an airfoil. The die for forming the core includes a plurality of moving parts having rib extensions. At least some rib extensions are non-parallel to form the non-parallel spaces. The die includes two main die halves that come together to form several of the spaces. Inserts move with those die components and come together to form other spaces. At least one of the inserts contacts surfaces on one of the die halves, such that the non-parallel spaces are formed.

Abstract: A propeller shaft assembly includes a substantially cylindrical hollow propeller shaft, a stub shaft and a constant velocity joint having inner race and an outer race drivingly interconnected by a plurality of balls. The stub shaft has a first end fixed to the propeller shaft and a second end drivingly coupled to the inner race. The second end includes a portion positioned adjacent to the inner race that defines an outer diameter greater than an outer diameter defined by the interface between the inner race and the plurality of balls.

Abstract: An axle assembly having an axle assembly with first and second sumps for holding a lubricant. A rotating ring gear associated with a differential can rotate through the lubricant in the first sump to cause a portion of the lubricant to cling to the ring gear. A portion of the lubricant that has clung to the ring gear can be removed from the ring gear and transferred to the second sump. The lubricant in the second sump can be drained to lubricate teeth of a pinion that is in meshing engagement with the ring gear and/or to lubricate bearings that support the pinion. A related method is also provided.

Abstract: A vehicle with primary and secondary drivelines and a power take-off unit (PTU). The primary driveline has a first differential that is configured to distribute power to a first set of wheels. The PTU has a PTU input, a PTU output and a synchronizer for selectively de-coupling the PTU output from the PTU input. The secondary driveline is configured to distribute power to a second set of wheels and has a propshaft, a second differential, a pair of half-shafts and at least one torque transfer device (TTD). The propshaft transmits rotary power between the PTU output and an input of the second differential. The half-shafts are rotatably coupled to an output of the second differential and are configured to transmit rotary power to the second set of wheels. The at least one TTD is configured to selectively inhibit torque transmission through the second differential to the second set of wheels.

Abstract: A die for forming a lost wax ceramic core allows the formation of non-parallel separating spaces between adjacent portions of the core. The core will eventually form cooling channels in an airfoil. The die for forming the core includes a plurality of moving parts having rib extensions. At least some rib extensions are non-parallel to form the non-parallel spaces. The die includes two main die halves that come together to form several of the spaces. Inserts move with those die components and come together to form other spaces. At least one of the inserts contacts surfaces on one of the die halves, such that the non-parallel spaces are formed.

Abstract: A die for forming a lost wax ceramic core allows the formation of non-parallel separating spaces between adjacent portions of the core. The core will eventually form cooling channels in an airfoil. The die for forming the core includes a plurality of moving parts having rib extensions. At least some rib extensions are non-parallel to form the non-parallel spaces. The die includes two main die halves that come together to form several of the spaces. Inserts move with those die components and come together to form other spaces. At least one of the inserts contacts surfaces on one of the die halves, such that the non-parallel spaces are formed.

Abstract: A die for forming a lost wax ceramic core allows the formation of non-parallel separating spaces between adjacent portions of the core. The core will eventually form cooling channels in an airfoil. The die for forming the core includes a plurality of moving parts having rib extensions. At least some rib extensions are non-parallel to form the non-parallel spaces. The die includes two main die halves that come together to form several of the spaces. Inserts move with those die components and come together to form other spaces. At least one of the inserts contacts surfaces on one of the die halves, such that the non-parallel spaces are formed.

Abstract: A propeller shaft assembly includes a substantially cylindrical hollow propeller shaft, a stub shaft and a constant velocity joint having inner race and an outer race drivingly interconnected by a plurality of balls. The stub shaft has a first end fixed to the propeller shaft and a second end drivingly coupled to the inner race. The second end includes a portion positioned adjacent to the inner race that defines an outer diameter greater than an outer diameter defined by the interface between the inner race and the plurality of balls.

Abstract: A gas turbine engine is provided with a turbine rotor disk having a plurality of disk slots which each receive a turbine blade. Cooling air is delivered into the disk slots, and flows into cooling air passages at a radially inner surface of the turbine blades. As known, the cooling air flows through the turbine blades to cool internal and external surfaces of the turbine blade. The disk slots are formed to have a greater cross-sectional area adjacent at the inlet end than at downstream locations. In this manner, the velocity of the air at the inlet end is reduced compared to the prior art, and pressure losses are minimized compared to the prior art.