An aircraft engine circulation system comprises a conduit arranged in use to communicate a lubricant to and from one or more bearings of an engine. The conduits define a space which comprises a material that is selected to change phase at a predetermined temperature.

Apparatus and associated methods relate to an in-space propulsion system configured to generate propulsion from a recirculated working fluid. In an illustrative example, the propulsion system may include a boiler configured to generate high pressure gas from the working fluid. The gas may, for example, be ejected from a nozzle into a distributor tube. A radiator coupled to the distributor tube may, for example, facilitate phase transition of the gas back into the working fluid. The fluid may be collected via one or more collection ducts coupled to the radiator. One or more pumps may recirculate the working fluid from the one or more collection ducts back into the boiler. Various embodiments may advantageously recirculate the working fluid such that propulsion is generated in response to an external power source while substantially an entire mass of the working fluid is preserved in the propulsion system.

Proposed is a hybrid rocket engine using an electric motor-driven oxidizer pump, the hybrid rocket engine including: an oxidizer tank configured to store the oxidizer; an oxidizer pump configured to pressurize the oxidizer by being connected to the oxidizer tank through a first oxidizer supply line; a drive unit including an electric motor configured to drive the oxidizer pump and a battery configured to supply power to the electric motor; an auxiliary oxidizer line configured to guide the oxidizer from the oxidizer tank to the electric motor to cool the electric motor; an oxidizer recirculation line configured to recharge oxidizer vapor, generated through heat exchange between the electric motor and the oxidizer, to the oxidizer tank, thereby pressurizing an inner side of the oxidizer tank; and a combustion chamber configured to combust the oxidizer and fuel by being connected to the oxidizer pump through a second oxidizer supply line.

A device and related method that provides, but is not limited thereto, a two-phase heat transfer device with unique combination of enhanced evaporation and increased cooling capacity. An advantage associated with the device and method includes, but is not limited thereto, increased cooling capacity per unit area, controlled and optimized evaporation, 10 prevention of boiling, and prevention of drying of the evaporator. An aspect associated with an approach may include, but is not limited thereto, using a non-wetting coating or structure to keep working fluid away from the spaces between elongated members of an evaporator and using a wetting coating or structure to form thin films of working fluid around the distal region of the elongated members.

An orifice assembly includes a first member defining an orifice having a first dimension in a compressed state and a thermally-sensitive material arranged adjacent to the first member. The thermally-sensitive material has a rigid, first state that applies force to the first member so as to maintain the first dimension of the orifice in the compressed state and a flexible, second state configured to release the force applied to the first member. As such, when subjected to temperatures above a predetermined temperature threshold, the thermally-sensitive material changes from the rigid, first state to the flexible, second state to allow the first dimension of the first member in the compressed state to passively expand to a decompressed, second dimension, the second dimension being larger than the first dimension.

The present invention provides a heat transferring device and a method for making thereof. The heat transferring device has a thermal conducting substrate and a porous layer. The thermal conducting substrate has a plurality of protrusions and concave bottom surfaces. The concave bottom surfaces are located between the protrusions. The porous layer is embedded between the protrusions. The present invention also provides a high temperature material transferring system comprising a cylindrical container and the heat transferring device disposed on the surface of the cylindrical container.

Aircraft engines include a turbine engine comprising a compressor section, a burner section, and a turbine section arranged along a shaft, with a core flow path through the turbine engine such that exhaust from the burner section passes through the turbine section, a condensing assembly arranged downstream of the turbine section of the turbine engine along the core flow path, and an exhaust compressor arranged downstream of the condensing assembly along the core flow path. The condensing assembly is configured to reduce a mass flow of the exhaust compressor by condensing water vapor from the core flow and removing liquid water from the core flow.

A method is provided during which an aircraft powerplant is provided. The aircraft powerplant includes a combustor and a water recovery system. The water recovery system includes a condenser and a reservoir. Fuel is combusted within the combustor to provide combustion products. Water is extracted from the combustion products using the condenser. The water recovery system is operated in one of a plurality of modes based on likelihood of contrail formation. The modes include a first mode and a second mode, where the water is collected within the reservoir during the first mode, and where the water passes through the water recovery system during the second mode.

A liquid fuel system for a turbine engine may include one or more sensors configured to generate sensor outputs corresponding to one or more phase properties of a fuel supplied to the turbine engine through a fuel pathway, and a controller configured to generate control commands configured to control one or more controllable components of the liquid fuel system based at least in part on the sensor outputs. The one or more sensors may include one or more phase detection sensors. The fuel may include hydrogen. The fuel may have a liquid phase state.

A pericritical fluid system for a thermal management system associated with a turbine engine may include one or more sensors configured to generate sensor outputs corresponding to one or more phase properties of a pericritical fluid flowing through a cooling circuit of the thermal management system, and a controller configured to generate control commands configured to control one or more controllable components of the thermal management system based at least in part on the sensor outputs. The one or more sensors may include one or more phase detection sensors, such as an acoustic sensor.