RTX Corporation

An aircraft powerplant assembly includes a gearbox (102) and a power coupler (104). The gearbox (102) includes a first power transfer apparatus (128) and a second power transfer apparatus (130). The first power transfer apparatus (128) is configured to couple and transfer first mechanical power through the gearbox (102) between a first engine apparatus (142) and a first engine accessory (106). The second power transfer apparatus (130) is configured to couple and transfer second mechanical power through the gearbox (102) between a second engine apparatus (152) and a second engine accessory (108) during a first mode. The power coupler (104) includes a variable speed transmission (160) and a clutch (162). The variable speed transmission (160) is coupled between the clutch (162) and the second power transfer apparatus (130). The clutch (162) is configured to couple the variable speed transmission (160) to the second engine apparatus (152) during the first mode. The clutch (162) is configured to decouple the variable speed transmission (160) from the second engine apparatus (152) during a second mode.

An apparatus is provided that includes a first electric device (128), a second electric device (130), an electric cable (122) and a cable shield (124). The electric cable (122) electrically couples the first electric device (128) to the second electric device (130). The cable shield (124) includes a first metal and a second metal. The first metal has a first permeability and a first impedance. The second metal has a second permeability and a second impedance. The first permeability is greater than the second permeability. The first impedance is greater than the second impedance. The electric cable (122) projects longitudinally, through a bore (126) of the cable shield (124) and along the first metal and the second metal, between the first electric device (128) and the second electric device (130).

An aircraft powerplant system (22) includes a turbine engine (24) and an accessory system. The turbine engine (24) includes a core flowpath (52), a first rotating structure (72), a compressor section (45), a combustor section (46) and a turbine section (47). The first rotating structure (72) includes a first bladed rotor (65, 66, 67, 68) arranged along the core flowpath (52) in the compressor section (45) or the turbine section (47). The accessory system includes a first electromechanical apparatus (172), an air circuit (136) and an air device (142). The first electromechanical apparatus (172) includes a first electric machine (102) and a first boost compressor (138). The first electric machine (102) includes a first electric machine rotor (106) that is operatively coupled to the first rotating structure (72). The first boost compressor (138) includes a first boost compressor rotor (166) that is operatively coupled to the first electric machine rotor (106) and the first rotating structure (72). The air circuit (136) is configured to direct air received from an air source (144), through the first boost compressor (138), to the air device (142).

A gas turbine includes a propulsor for delivering air as propulsion air, and for delivering air into a core engine. The core engine includes a compressor section, a combustor and a turbine section. A turbine rotor in the turbine section drives the propulsor, and a compressor rotor in the compressor section. There is an epicyclic gear reduction (48) between the turbine rotor and the propulsor. The epicyclic gear reduction (48) includes a sun gear (102) driven by the turbine rotor to engage and rotate intermediate gears (106). The intermediate gears (106) are mounted in a carrier. The intermediate gears (106) also engage a ring gear (100). At least one of the carrier and ring gear (100) drive the propulsor, and the intermediate gears (106) include a rim and gear teeth (109) extending outwardly of the rim. The intermediate gears (106) are mounted on journal bearings (108) which are supported in the carrier. The intermediate gear rims are provided with cooling passages extending with at least a component in a direction parallel to an axis of rotation of the intermediate gears (106).

An aircraft assembly includes an engine core (46), a core case (76), a nacelle structure (78), a core compartment (80), a first electric machine (104A) and a first driveshaft (130A). The engine core (46) includes a first rotating structure (68A) rotatable about a first axis (34) and that includes a first structure rotor (61; 64). The core case (76) is radially outboard of and houses the engine core (46). The nacelle structure (78) is radially outboard of and covers the core case (76). The core compartment (80) is disposed radially between and is formed by the core case (76) and the nacelle structure (78). The first electric machine (104A) is disposed in the core compartment (80). The first electric machine (104A) includes a first machine rotor (108A) and a first machine case (116). The first machine case (116) houses the first machine rotor (108A). The first machine case (116) is connected to and projects out from a section (120) of the core case (76). The first drivetrain (130A) operatively couples the first machine rotor (108A) to the first rotating structure (68A).

An assembly for an aircraft propulsion system (20) includes an open propulsor rotor (34), a housing structure (54), and a turbine engine core (76). The open propulsor rotor (34) includes a plurality of open propulsor blades (42) arranged circumferentially around an axis (24). Each of the plurality of open propulsor blades (42) projects radially out into an environment (22) external to the aircraft propulsion system (20). The housing structure (54) includes an engine case assembly (106) and a nacelle (108). The nacelle (108) forms at least a portion of an exterior flow boundary (56) for the aircraft propulsion system (20). The nacelle (108) forms a guide vane structure receptacle (136) at the exterior flow boundary (56). The nacelle (108) further includes a nacelle interior skeletal structure (140) disposed at the guide vane structure receptacle (136). The turbine engine core (76) is housed within the engine case assembly (106). The turbine engine core (76) is configured to drive rotation of the open propulsor rotor (34) about the axis (24).

An assembly for an aircraft propulsion system (20) includes a housing structure (54), a guide vane structure (36), and a front mount assembly (148). The housing structure (54) includes an engine case assembly (106). The engine case assembly (106) includes a front center body (122). The guide vane structure (36) includes a guide vane structure base (50). The front mount assembly (148) is mounted on the front center body (122). The front mount assembly (148) is disposed axially coincident with the guide vane structure (36). The front mount assembly (148) includes at least one pylon attachment linkage (154).

An aircraft powerplant (20) assembly includes a first electric device (108A) and a cooling system (36). The first electric device (108A) includes a first device heat exchanger (160A), a first device housing (118A) and first electrical circuitry (120A). The cooling system (36) includes a liquid circuit (138), an air circuit (136) and a system heat exchanger (140). The cooling system (36) is configured to cool the first electrical circuitry (120A) using a liquid flowing in the liquid circuit (138) and air flowing in the air circuit (136). The liquid circuit (138) extends through the system heat exchanger (140) and the first electric device (108A). The first device heat exchanger (160A) is configured to transfer heat energy from the first electrical circuitry (120A) into the liquid in the liquid circuit (138). The air circuit (136) extends through the system heat exchanger (140). The system heat exchanger (140) is configured to transfer at least some of the heat energy from the liquid in the liquid circuit (138) into the air in the air circuit (136).

An operating method is provided for an aircraft. During this method, a first control signal is provided to drive rotation of a first propulsor rotor of a first propulsion system of the aircraft using a first engine of the first propulsion system. Operation of the first engine is monitored to provide first engine data. A degraded condition of the first engine is identified based on the first engine data. In response to the identifying of the degraded condition, a second control signal is provided to drive the rotation of the first propulsor rotor at a first rate using a first electric machine of the first propulsion system. The first rate is equal to or greater than fifty percent of a second rate at which a second propulsor rotor of a second propulsion system of the aircraft is being rotated.

A start mechanism for a propulsion system including a receptacle in operative communication with a case; at least one portable source of energy disposed within the receptacle; a flow channel fluidly coupled to the receptacle; and a turbine flow path within the case, the turbine flow path fluidly coupled to the flow channel; wherein the at least one portable source of energy is configured to produce at least one of electrical energy and a source of chemical energy.