Pratt & Whitney Canada Patente

An assembly is provided for an aircraft. This aircraft assembly includes a fluid reservoir structure, an aircraft engine housing structure and a mounting assembly (20). The fluid reservoir structure includes a first mount (28). The aircraft engine housing structure includes a second mount (30). The mounting assembly (20) connects the first mount (28) to the second mount (30) while providing controlled intercomponent movement between the first mount (28) and the second mount (30) to reduce internal stress and/or wear. The mounting assembly (20) includes a first bushing (32), a second bushing (34) and a fastener (36).

A propulsion system (20) for an aircraft includes a propulsion rotor, and at least one engine (22) mechanically coupled to the propulsion rotor via a geartrain (60). The propulsion system (20) also includes a first propulsor module (24) having a first housing, a first electric motor (112), and a first bladed propulsor. The first bladed propulsor is coupled with the first electric motor (112) within the first housing. The propulsion system (20) further includes a second propulsor module having a second housing, a second electric motor, and a second bladed propulsor. The second bladed propulsor is coupled with the second electric motor within the second housing. The propulsion system (20) also includes a first generator (82) driven by the at least one engine (22) and electrically connected with the first electric motor (112). Additionally, the propulsion system (20) includes a second generator driven by the at least one engine (22) and electrically connected with the second electric motor.

A labyrinth seal for an aircraft engine includes a base plate (12) for mounting to a housing (10), a first annular insert (14) with a stationary seal element for attaching to the base plate (12), an annular base (22) for mounting to a shaft (20), and second annular insert (24) with a rotating seal element for attaching to the annular base (22). Each of the base plate (12), annular base (22), and the first (14) and second (24) inserts with the seal elements, such as fins, may be made of different materials, which allows clearances (including axial clearances) of the seal elements to be controlled more precisely and may allow reduced wear. Base elements (base plate (12) and/or annular base (22)) and seal elements (first (14) and/or second (24) annular inserts) may be respectively attached to each other by a friction fit (50), an adhesive (70), a weld (60), a plurality of bolts (80), or a plurality of rivets (90).

A gear train (24) includes an output shaft (160), a clutch assembly (70), and an output gear roller bearing (82). The output shaft (160) is configured for rotation about a rotational axis (76). The clutch assembly (70) includes an inner ring-shaft (108), an output gear (78), a clutch (80), and a clutch ball bearing (84). The inner ring-shaft (108) extends between and to a first outer radial side (112) and a first inner radial side (114). The inner ring-shaft (108) is mounted on the output shaft (160) at the first inner radial side (114). The output gear (78) includes an outer ring (98). The outer ring (98) extends between and to a second outer radial side (100) and a second inner radial side (102). The clutch (80) is disposed between the outer ring (98) and the inner ring-shaft (108). The clutch ball bearing (84) is disposed between the first outer radial side (112) and the second inner radial side (114). The output gear roller bearing (82) is in rolling engagement with the outer ring (98) on the second outer radial side (112).

A rotor blade (72) includes an airfoil (86), a root (90), a cooling air passage (122) and a cooling air deflector (94). The root (90) extends axially along an axis (24) between a first end (114) and a second end (116). The root (90) extends laterally between a first side (118A) and a second side (118B). The root (90) projects radially inward and away from the airfoil (86) to an inner end (112) of the root (90). The cooling air passage (122) includes a passage inlet (124) disposed at the inner end (112). The cooling air passage (122) projects radially into the rotor blade (72) from the passage inlet (124). The cooling air deflector (94) projects radially inward from the inner end (112) of the root (90) to an inner end (130) of the cooling air deflector (94). The cooling air deflector (94) is disposed at the second side (118B) and is spaced laterally from the first side (118A). The cooling air deflector (94) includes a cooling air aperture (150).

A method for correcting extrinsic loading effects on kinematic accuracy of a machining assembly (20) includes determining, for a positioning system (32) of the machining assembly (20) including a cantilevered arm (44) and a rotary table (34) mounted on the cantilevered arm (44), a first position and a first orientation of a first axis (54) and a second position and a second orientation of a second axis (56), filling a machining tank (46) with a dielectric fluid, determining a third position and a third orientation of the first axis (54) and a fourth position and a fourth orientation of the second axis (56), and determining position and orientation correction factors for the first axis (54) and the second axis (56) using a position and orientation deviation of the first axis (54) and the second axis (56) in the first condition from the first axis (54) and the second axis (56) in the second condition.

A method of manufacturing a component of a housing defining a rotor cavity (20), the method includes: obtaining a body (214C,218F) of the component of the housing, the body (214C,218F) having a first face (211A,218A) and a second face opposite to the first face (211A,218A) , the second face facing away from the rotor cavity (20), the body (214C,218F) made of a first material; performing a treatment to the body (214C,218F) to increase a wear-resistance of the first material; depositing a bonding layer (214D,218H) on the second face of the body (214C,218F), the bonding layer (214D,218H) including a second material being dissimilar from the first material, the first material being more wear-resistant than the second material, the second material defining an exposed face of the bonding layer (214D,218H) facing away from the body (214C,218F); and completing a shape of the body (214C,218F) by bonding a quantity of a third material to the exposed face of the bonding layer (214D,218H).

An aircraft engine has a high pressure spool including a high pressure turbine drivingly connected to a high pressure compressor. A low pressure spool including a low pressure compressor is fluidly connected to the high pressure compressor. A low pressure turbine is drivingly connected to the low pressure compressor to drive the low pressure compressor. A load is drivingly connected to the low pressure turbine, the load consisting of one of a propeller and a helicopter rotor. A method of creating classes of an aircraft engine from an engine platform is disclosed.

An assembly of a gas turbine engine, having: a shaft (50) having a shaft outer surface (120A) and a shaft inner surface (120B), the shaft (50) axially extends from a shaft forward end (50A) to a shaft aft end (50B), the shaft forward end (50A) defines axially extending shaft slots (130) that are circumferentially spaced apart from each other; a bearing (110) having a first race (150), the first race (150) is ring shaped with a first race outer surface (160) and a first race inner surface (170), the first race (150) is sized so the first race inner surface (170) fits around the shaft outer surface (120A), the first race (150) extends axially from a first race forward end (180) to a first race aft end (190), the first race forward end (180) defines radially inwardly extending bosses (200) that are circumferentially spaced apart from each other and aligned with ones of the axially extending slots (130) of the shaft forward end (50A), rotationally fixing the first race (150) against the shaft (50).

An assembly is provided for an aircraft propulsion system (20). This assembly includes a geartrain (68), a propulsor rotor (40), a compressor rotor (41), a rotating structure (60) and an electric machine (24). The geartrain (68) includes a first component, a second component and a third component. The propulsor rotor (40) is coupled to the geartrain (68) through the first component. The compressor rotor (41) is coupled to the geartrain (68) through the second component. The rotating structure (60) is coupled to the geartrain (68) through the third component. The rotating structure (60) includes a turbine rotor (44). The electric machine (24) is positioned remote from the geartrain (68). The electric machine (24) includes an electric machine rotor (86), and the electric machine rotor (86) is coupled to the geartrain (68) through the third component.

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A plenum assembly for a compressor has a plenum housing (50) defining a radially inward entry to a compressor and an outer circumference, and at least two open areas in the outer circumferences which are defined by at least two plenum flanges (52, 54); an inlet duct (82) connected to a first plenum flange (54) of the at least two plenum flanges (52, 54); and a panel (60) having a flow control feature (72), wherein the panel (60) is connected to a second plenum flange (52) of the at least two plenum flanges (52, 54).

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An aircraft (10) has a cabin (11), a rotary airfoil device (14; 114), an electric engine (12; 112), a battery (120) powering the electric engine (12; 112), a transmission (144) coupling the electric engine (12; 112) to the rotary airfoil device (14; 114), a lubricant subsystem (22; 220) having a lubricant circuit (222) and a lubricant pump (24) operable to circulate a lubricant in the lubricant circuit (222), the lubricant circuit (222) connected in heat exchange relationship with the transmission (144), a coolant subsystem (230) having a coolant circuit (232) and a coolant pump (174) operable to circulate a coolant in the coolant circuit (232), the coolant circuit (232) connected in heat exchange relationship with at least one of the electric engine (12; 112) and the battery (120), and a pressurized air subsystem (250) having a pressurized air line (254) operable to deliver pressurized air from a pressurized air source (64) to the cabin (11). The pressurized air line (254) is connected in heat exchange relationship with at least one of the coolant circuit (232) and the lubricant circuit (222).

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