Pratt & Whitney Canada Patente

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An assembly for a propulsion system of an aircraft includes a gearbox module (32), an electric motor assembly (28), a first accessory load assembly (24), and a propulsor (34). The gearbox module (32) includes a gear assembly (64) and an output shaft (62). The gear assembly (64) includes a main gear (72) and a plurality of offset gears (74). The electric motor assembly (28) includes an electric motor (38). The electric motor (38) includes a rotor. The rotor is mounted to a first offset gear of the plurality of offset gears (74). The rotor is configured for rotation about a rotational axis to drive rotation of the gear assembly (64) and the output shaft (62). The first accessory load assembly (24) includes at least one first accessory load (84). The at least one first accessory load (84) is mounted to a second offset gear of the plurality of offset gears (74). The propulsor (34) is coupled to the output shaft (62).

An aircraft propulsion system (18) and method is provided. The system (18) includes compressor, combustor, and turbine sections (80, 84, 22), a fuel source (64), a heat exchanger (66), a compressor bleed air passage (86), and a cooling air passage (88). The fuel source (64) is configured to contain a non-hydrocarbon fuel. The heat exchanger (66) has separate air and fuel passages (68). The air passage (68) permits passage of the compressed air therethrough. The fuel passage (74) is configured to permit a passage of the non-hydrocarbon fuel therethrough. The compressor bleed air passage (86) is configured to receive compressed air bleed off a core flow path (82) upstream of the combustor section (84). The compressor bleed air passage (86) is in fluid communication with the air passage air inlet (70). The cooling air passage (88) is configured to receive compressed air exiting the air passage (68) air outlet (72) and configured to direct the compressed bleed air to the vane stage or rotor stage of the turbine section (22), or both.

The aircraft has a cabin (11), an electric engine (112) drivingly coupled to a rotary airfoil device (114), a battery (120) powering the electric engine (112); a heat pump (240) having a refrigerant circuit (242) fluidly connecting, a compressor (241), a condenser (243), an expansion valve (245), and an evaporator (248), and a pressurized air subsystem (250) having a network of pressurized air lines (252) operable to deliver pressurized air from one or more pressurized air sources (176) to the cabin (11). The network has a hot line (254) fluidly connecting one of the one or more pressurized air sources to a mixing volume (281), a cold line (256) parallel to the hot line (254), the cold line (256) fluidly connecting one of the one or more pressurized air sources (176) to the mixing volume (281), and a delivery line (258) fluidly connecting the mixing volume (281) to the cabin (11). The hot line (254) is connected in heat exchange relationship with a source of heat, and the cold line (256) is in heat exchange relationship with the evaporator (248).

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An electric aircraft engine (100) includes an electric motor (109) driving a propulsor (108). A power source (110) powers the electric motor (109). An electric compressor (112) supplies compressed air. A nacelle (106) surrounds the electric motor (109), the power source (110) and the electric compressor (112). An aircraft (20) and a method are also disclosed.

An assembly for a propulsion system (20) of an aircraft (1000) includes a gearbox module (32), at least one accessory load assembly (24), a propulsor (34), and an electric motor (38). The gearbox module (32) includes a gear assembly (88) and an output shaft (90). The gear assembly (88) is connected to the output shaft (90). The at least one accessory load assembly (24) includes at least one accessory load (124) coupled to the output shaft (90). The propulsor (34) is coupled to the output shaft (90). The electric motor (38) includes a rotor (42). The rotor (42) is coupled to the gear assembly (88) to drive rotation of the output shaft (90) about a rotational axis (104). The rotation of the output shaft (90) drives rotation of the propulsor (34) and the at least one accessory load (124) for each accessory load assembly (24) of the at least one accessory load assembly (24).

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A tube assembly (10) comprises a tube (12) having a tube flange (18) securable to an associated mounting surface (20) of a turbine engine component (14). A first seal (30) is provided at the bore interface between the tube (12) and a fluid port (34) of the engine component (14). A second seal (32) is provided at the flange interface between the tube flange (18) and the tube mounting surface (20) of the engine component (14). The second seal (32) includes a gasket having a sheet metal body (38) with corrugations (46a, 46b) projecting from the tube facing side (40) of the gasket. Tabs (52) are distributed along a periphery of the gasket for resiliently holding the gasket on the tube flange (18) with the tube facing side (40) of the gasket facing the tube flange (18).

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An assembly for a gas turbine engine of an aircraft includes a rotational assembly, a starter generator (28), and a control relay (54). The starter generator (28) is coupled with the rotational assembly and is configured to selectively drive rotation of the rotational assembly and a motor winding (64) including a first electrical terminal (65) and a second electrical terminal (66). The control relay (54) includes a switch (72) electrically connected to the first electrical terminal (65). The switch (72) is positionable in a first contact position and a second contact position, in the first contact position, the first electrical terminal (65) is electrically isolated from the second electrical terminal (66) through the switch (72). In the second contact position, the first electrical terminal (65) is electrically connected to the second electrical terminal (66) through the switch (72) such that a closed electrical circuit is formed through the motor winding (64), the first electrical terminal (65), the second electrical terminal (66), and the switch (72).