A tesla-type turbine for converting the enthalpy of a gas volume flow into mechanical energy, a method for operating the Tesla-type turbine, and an apparatus for converting thermal energy into mechanical energy, a method for converting thermal energy into mechanical energy, and a method for converting thermal energy into electrical energy. The Tesla-type turbine has at least one disc which is positioned on an axis of rotation and is set into rotation by a gas volume flow flowing substantially tangentially, so that mechanical energy can be collected at a shaft coupled to the disc. A disc body that forms the disc has at least one cavity in which, for the purpose of cooling the disc body, a cooling medium, in particular a cooling liquid, is received or can be received.

A thermal management system includes a first heat source assembly including a first heat source exchanger, a first thermal fluid inlet line extending to the first heat source exchanger, and a first thermal fluid outlet line extending from the first heat source exchanger; a second heat source assembly including a second heat source exchanger, a second thermal fluid inlet line extending to the second heat source exchanger, and second a thermal fluid outlet line extending from the second heat source exchanger; a shared assembly including a thermal fluid line and a heat sink exchanger, the shared assembly defining an upstream junction in fluid communication with the first thermal fluid outlet line and second thermal fluid outlet line and a downstream junction in fluid communication with the first thermal fluid inlet line and second thermal fluid inlet line; and a controller configured to selectively fluidly connect the first heat source assembly or the second heat source assembly to the shared assembly.

A thermal management system includes a first heat source assembly including a first heat source exchanger, a first thermal fluid inlet line extending to the first heat source exchanger, and a first thermal fluid outlet line extending from the first heat source exchanger; a second heat source assembly including a second heat source exchanger, a second thermal fluid inlet line extending to the second heat source exchanger, and second a thermal fluid outlet line extending from the second heat source exchanger; a shared assembly including a thermal fluid line and a heat sink exchanger, the shared assembly defining an upstream junction in fluid communication with the first thermal fluid outlet line and second thermal fluid outlet line and a downstream junction in fluid communication with the first thermal fluid inlet line and second thermal fluid inlet line; and a controller configured to selectively fluidly connect the first heat source assembly or the second heat source assembly to the shared assembly.

An auxiliary power unit for an aircraft, having a compressor, an intercooler including first conduit(s) having an inlet in fluid communication with the compressor outlet and second conduit(s) configured for circulation of a coolant therethrough, an engine core having an inlet in fluid communication with an outlet of the first conduit(s), and a bleed conduit in fluid communication with the outlet of the first conduit(s) through a bleed air valve. The auxiliary power unit may include a generator in driving engagement with the shaft of the engine core to provide electrical power for the aircraft. A method of providing compressed air and electrical power to an aircraft is also discussed.

An auxiliary power unit for an aircraft, having a compressor, an intercooler including first conduit(s) having an inlet in fluid communication with the compressor outlet and second conduit(s) configured for circulation of a coolant therethrough, an engine core having an inlet in fluid communication with an outlet of the first conduit(s), and a bleed conduit in fluid communication with the outlet of the first conduit(s) through a bleed air valve. The auxiliary power unit may include a generator in driving engagement with the shaft of the engine core to provide electrical power for the aircraft. A method of providing compressed air and electrical power to an aircraft is also discussed.

In one aspect of the present disclosure, there is provided a nozzle assembly comprises a first fuel conduit defined between a nozzle body and a fuel swirler and extending along a longitudinal axis from an inlet of the first fuel conduit to an outlet of the fuel nozzle assembly. A second fuel conduit is defined between the fuel swirler and a heat shield and extending along the fuel swirler along the longitudinal axis from an inlet of the second fuel conduit to the outlet of the fuel nozzle assembly. An air conduit extends through the heat shield along the longitudinal axis from an inlet of the air conduit to the outlet of the fuel nozzle assembly.

An aircraft engine has a combustor supplied by a hydrogen fuel system and is configured to combust hydrogen and generate water vapor. A water vapor collector receives at least part of the water vapor. A condenser is in fluid communication with the water vapor collector to receive and cool in the condenser the at least part of the water vapor and thereby condense at least part of the at least part of the flow of water vapor. A spray nozzle is in fluid communication with the condenser and operable to spray the condensed part of the at least part of the flow of water vapor onto a component of the aircraft engine.

A thermal management system for a gas turbine engine includes a primary vapor compression system including a primary evaporator defining thermal communication between a primary refrigerant and a flow of fuel to cool the fuel. A boost vapor compression system includes a boost heat exchanger defining thermal communication between the primary refrigerant. A boost refrigerant cools the primary refrigerant and a boost condenser in thermal communication with an air stream cools the boost refrigerant.

An oil pumping system for use with a gas turbine engine includes an electric machine, an oil pump assembly, and a variable frequency drive controller. The variable frequency drive is connected with the electric machine and the oil pump assembly. The variable frequency drive controller is programmed to control a torque and speed of the pump motor independent of the gas turbine engine speed so that a flow of oil moved by the oil pump assembly is controlled to cool or lubricate components of the gas turbine engine independent of the gas turbine engine speed.

An oil pumping system for use with a gas turbine engine includes an electric machine, an oil pump assembly, and a variable frequency drive controller. The variable frequency drive is connected with the electric machine and the oil pump assembly. The variable frequency drive controller is programmed to control a torque and speed of the pump motor independent of the gas turbine engine speed so that a flow of oil moved by the oil pump assembly is controlled to cool or lubricate components of the gas turbine engine independent of the gas turbine engine speed.