Pratt & Whitney Canada Patente

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A method of manufacturing an annular bearing housing (54) for a gas turbine engine includes: producing a flange outer structure segment (58); producing an intermediate structure segment (60) having an outer radial end (76), an inner radial end (78), a body (74) that extends between the outer radial end (76) and the inner radial end (78), and a branch member (84) that extends outwardly from the body (74); producing a main body segment (62); attaching the flange outer structure segment (58) to the outer radial end (76) of the intermediate structure segment (60); and attaching the main body segment (62) to the inner radial end (78) of the intermediate structure segment (60). At least one of the flange outer structure segment (54), the intermediate structure segment (60), or the main body segment (62) is produced using an additive manufacturing process.

An assembly (20) for an aircraft includes a first engine case (22; 32), a bracket (24) and fastener assemblies (30A, 30B). The first engine case (22; 32) includes a first sidewall (38) and a first flange (40) projecting radially out from the first sidewall (38). The bracket (24) is abutted axially against the first flange (40). The fastener assemblies (30A, 30B) attach the bracket (24) to the first flange (40). The fastener assemblies (30A, 30B) include a first fastener assembly (30) with a first bolt (86), a first nut (88) and a retainer. The first bolt (86) includes a first bolt head and a first bolt shank that projects axially out from the first bolt head and axially through the first flange (40) and the bracket (24). The first nut (88) is threaded onto the first bolt shank with the first flange (40) and the bracket (24) axially between the first bolt head and the first nut (88). The retainer is attached to the first bolt shank with the first nut (88) axially between the retainer and the bracket (24).

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An assembly is provided for a rotorcraft (20). This rotorcraft (20) assembly includes a fuselage (28), a tail and a rotorcraft lift system (24). The tail boom (30) is connected to and projects longitudinally out from the fuselage (28). The rotorcraft lift system (24) includes a rotorcraft rotor (42) and a powerplant (44) configured to drive rotation of the rotorcraft rotor (42) to generate rotorcraft lift. The powerplant (44) includes a heat engine (54) and a powerplant flowpath (62). The powerplant flowpath (62) extends through the heat engine (54). The outlet (82) from the powerplant flowpath (62) is fluidly coupled to an interior volume (106) in the tail boom (30).

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A torque measurement system (50; 150) for an aircraft propulsor (10) including a reduction gearbox (31) includes generally a first toothed wheel (52) mounted to a loaded shaft (54), a second toothed wheel (56) mounted to a torque reference tube (58; 158) radially spaced apart from the loaded shaft (54) and concentric therewith, and a torque probe (20) located proximate the first and second toothed wheels (52, 56). A frustoconical element (60, 62) is located proximate an input end (47) of the loaded shaft (54), the frustoconical element (60, 62) having an annular body (65) radially disposed between the loaded shaft (54) and the torque reference tube (58; 158) and being mounted for rotation with one of the two. The frustoconical element (60, 62) includes a frustoconical surface (61, 63) that abuts a complementary running surface. The frustoconical surface (61, 63) of the frustoconical element (60, 62) and the complementary running surface rotate relative to each other and define a contact interface (90), the contact interface (90) being annular and oriented at an angle (θ) relative to the central axis (11).

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An engine assembly (20) for an aircraft propulsion system (10) includes a gas turbine engine (22), a gearbox (24), and a first drive shaft (30). The gas turbine engine (22) includes an engine output shaft (64), an air intake (34), and a compressor (44). The air intake (34) includes an air intake body (86) forming an air inlet (88), an air outlet (90), and an air plenum (92) extending between and connecting the air inlet (88) and the air outlet (90). The air plenum (92) extends circumferentially about the engine output shaft (64) between and to a first circumferential end (104) of the air intake (34) and a second circumferential end (106) of the air intake (34). The first circumferential end (104) and the second circumferential end (106) form a circumferential gap (108). The compressor (44) is connected in fluid communication with the air intake (34). The gearbox (24) includes a gear assembly (68) operably connected to the engine output shaft (64). The first drive shaft (30) is operably connected to the gear assembly (68). The first drive shaft (30) extends through the circumferential gap.

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