Dehns

A powerplant assembly (24) includes an engine (32), a turbocompressor (34), and an overspeed protection valve (74). The engine (32) includes an air intake (64) and an engine exhaust (68). The turbocompressor (34) includes a compressor section (46), a turbine section (48), and a rotational assembly (50). The rotational assembly (50) includes a turbocompressor shaft (54), a bladed compressor rotor (56) of the compressor section (46), and a turbine rotor (58) of the turbine section (48). The engine (32) and the turbocompressor (34) form a gas flow path (60). The gas flow path (60) extends from the compressor section (46) to the air intake (64), through the engine (32), and from the engine exhaust (68) to the turbine section (48). The overspeed protection valve (74) forms a portion of the gas flow path (60). The overspeed protection valve (74) is positionable in an open state and a closed state.

A hybrid aircraft power plant (10) includes an air mover (24) for propelling an aircraft (12), a gas turbine engine (14) operable to drive the air mover (24), and an electric machine (46) operable as a motor to drive the air mover (24). The gas turbine engine (14) includes a turbine disk (30) for extracting energy from a stream of combustion gas, and an exhaust duct (38) defining: an exhaust passage for conveying the stream of combustion gas from the turbine disk (30); and a cavity (41) disposed radially inward of the exhaust passage. A shaft (32,50) drivingly connects the turbine disk (30) with the electric machine (46) and extends inside the cavity (41) defined by the exhaust duct (38). A fan (51) is drivingly connected to the shaft (32,50) and operable to circulate cooling air inside the cavity (41) of the exhaust duct (38).

A hybrid-electric aircraft propulsion system (20) includes an engine (22), a first electric machine assembly (80), and a second electric machine assembly (82). The engine (22) includes a first rotational assembly and a second rotational assembly. The first electric machine assembly (80) includes a first electric machine (86), a first control unit (88), first electrical cables (94), and a first cable conduit (96). The first electric machine (86) is coupled with the first rotational assembly. The first electrical cables (94) extend between and electrically connect the first electric machine (86) and the first control unit (88) through the first cable conduit (96). The second electric machine assembly (82) includes a second electric machine (90), a second control unit (92), second electrical cables (98), and a second cable conduit (100). The second electric machine (90) is coupled with the second rotational assembly. The second electrical cables (98) extend between and electrically connect the second electric machine (90) and the second control unit (92) through the second cable conduit (100).

A heat removal device (100) operable to cool a heat-generating device (62) includes a housing (200) having a hollow interior (202) and a base (102) arranged within the hollow interior (202) of the housing (200). The base (102) includes a contact surface (104) and a cooling surface (106). The contact surface (104) is thermally couplable to the heat-generating device (62). At least one fin (120) including a plurality of fin segments (140) is arranged at the cooling surface (106). At least one of the plurality of fin segments (140) includes a plurality of louvers (150).

A replaceable tool tip system (200) for an ultrasonic impact grinder includes a tool (230) having a proximal end adjacent a horn (232) of the ultrasonic impact grinder and a distal end. At least one threaded blind hole (386) is disposed in the distal end of the tool. A replaceable tool tip (235) includes at least one threaded through hole (384) in registration with each threaded blind hole, wherein a first threading of each threaded blind hole is different from a second threading of each corresponding threaded through hole. At least one headless differential screw fastener (280) has first threads (381) for engaging a respective threaded blind hole on a first end and different second threads (383) for engaging a respective through hole on a second end, and is used to attach and preload the replaceable tool tip.

A cooling system for variable frequency drive (VFD) (102) and/or oil-cooled device (103), is disclosed. The cooling system includes a heat exchanger (104) operatively connected to cooling source component (106) and the VFD (102). The cooling system includes a first coolant circuit (108) routed through the heat exchanger (104) and the VFD (102), and a second coolant circuit (110) routed through the heat exchanger (104) and the cooling source component (106). The cooling system includes a double-shafted pump (112) connected to the first coolant circuit (108) and/or the second coolant circuit (110), and configured to circulate first coolant through the first coolant circuit (108) and second coolant through the second coolant circuit (110) for cooling the VFD (102). The first coolant circuit (108) and/or the second coolant circuit (110) includes a three-way valve (114a) and/or a thermostatic valve (114b) defining a bypass (116a, 116b, 116c) on the first coolant circuit (108) for the first coolant exiting the heat exchanger (104), or the second coolant circuit (110) for the second coolant exiting or entering into the heat exchanger (104).

An original feeling is achieved without impairing output performance of an engine.In a saddle-ride vehicle including a multi-cylinder engine (12) and an air cleaner box (51) in which a plurality of air funnels (61a to 61d) in connection with respective cylinders of the engine (12) are disposed downstream of an air cleaner element (52), the plurality of air funnels (61a to 61d) each include an opening portion (62f) directed toward the air cleaner element (52), and a plane (M1) obtained by extending an end surface of the opening portion (62f) is disposed to intersect the air cleaner element (52), and a first air funnel (61a, 61b) of the plurality of air funnels (61a to 61d) is different in diameter of the opening portion (62f) from a second air funnel (61c, 61d).

A method of building a component using additive manufacturing techniques includes depositing and sintering one or more layers of build powder using a PBF-L process to form an intermediate consolidated build powder structure having a sintered surface. The PBF-L process is paused and a laser peening process is performed in situ on the sintered surface to induce a desired residual stress profile in selected layers of the intermediate consolidated build powder structure. The PBF-L process is resumed to deposit and sinter one or more layers of additional build powder onto the intermediate consolidated build powder structure to form an additional intermediate consolidated build powder structure having an additional sintered surface. The steps are repeated a predetermined number of times to form a finished component. The complete component includes one or more zones of residual stress imparted by the laser peening process in one or more interior layers.

A gas turbine engine (20) is provided that includes a compressor section (22), a combustor (24), and a mixed-flow turbine (26). The mixed-flow turbine (26) has a first turbine ("FT") rotor stage (32), an annular first vane stage (34), and a second turbine ("ST") rotor stage (36). The FT rotor stage (32) includes an FT disk (32A) and a plurality of FT rotor blades (32B) extending outwardly from the FT disk (32a). The ST rotor stage (36) includes an ST disk (36A) and a plurality of ST rotor blades extending outwardly from the ST disk (36A). The annular first vane stage (34) includes a plurality of stator vanes (42) that are distributed circumferentially, and disposed axially between the FT rotor stage (32) and the ST rotor stage (36). One or more of the stator vanes (42) includes a radially extending interior passage configured to permit a flow of cooling air to pass through the respective one or more stator vanes (42).

A propulsion system (20) includes an engine (22), a drivetrain (26), and a propulsor (24). The engine (22) includes an engine output shaft (52). The drivetrain (26) is coupled with the engine output shaft (52). The drivetrain (26) includes a propulsor output shaft (60), a gear assembly (64), and an electric motor assembly (62). The gear assembly (64) includes a propulsor output gear (70) mounted on the propulsor output shaft (60). The propulsor output gear (70) includes a ring (84). The ring (84) includes an outer gear face (86) and an inner gear face (88). The electric motor assembly (62) includes at least one electric motor (94). The at least one electric motor (94) includes a rotor (96). The rotor (96) includes an electric motor output shaft (98) and an electric motor output gear (100) mounted on the electric motor output shaft (98). The electric motor output gear (100) is engaged with the inner gear face (88). The propulsor (24) is interconnected with the propulsor output gear (70) by the propulsor output shaft (60).