A gas turbine engine includes a compressor section that provides first and second compressor stages that are configured to respectively provide first and second cooling fluids. The first compressor stage has a higher pressure than the second compressor stage. The gas turbine engine further includes a component that has platform with an internal cooling passage fed by first and second inlets that respectively receive fluid from the first and second cooling sources. The second inlet is downstream from the first inlet.

A thermal management system for transferring heat between fluids includes a thermal transport bus through which a heat exchange fluid flows. Additionally, the system includes a heat source heat exchanger arranged along the bus such that heat is added to the fluid flowing through the heat source heat exchanger. Moreover, the system includes a plurality of heat sink heat exchangers arranged along the bus such that heat is removed from the fluid flowing through the plurality of heat sink heat exchangers. Furthermore, the system includes a bypass conduit fluidly coupled to the bus such that the bypass conduit allows the fluid to bypass one of the heat source heat exchanger or one of the heat sink heat exchangers. In addition, the system includes a valve configured to control a flow of the fluid through the bypass conduit based on a pressure of the fluid within the bus.

A component, such as for a turbine engine, can include an airfoil with an outer wall defining an exterior surface bounding an interior and defining a pressure side and a suction side extending between a leading edge and a trailing edge to define a chord-wise direction and extending between a root and a tip to define a span-wise direction. The component can also include at least one cooling passage within the interior.

A motor assembly has a motor having a rotor and a stator. An impeller is connected to a rotary shaft of the rotor and a housing is disposed between the impeller and the motor and surrounding an upper side of the motor. A diffuser discharges air, which is suctioned by the impeller, along an outer surface of the housing. A heat dissipation cover covers an outer surface of the motor. The heat dissipation cover includes an inner cover spaced apart from the outer surface of the motor and forming an inside-cover flow channel that air flows through and an outer cover having a diameter greater than that of the inner cover and forming an outside-cover flow channel through which air flows along the outer surface thereof.

An assembly for a gas turbine engine according to an example of the present disclosure includes at least one platform having a main body extending between a first mate face and a second mate face to establish a gas path surface. The main body has an internal passage extending circumferentially between a first opening along the first mate face and a second opening along the second mate face relative to an assembly axis. A perimeter of the first mate face establishes a first area, a perimeter of the second opening establishes a second area, and the second area is greater than the first area. An airfoil section extends radially from the at least one platform.

A heat exchanger system for a propulsion system inlet duct includes a heat exchanger assembly that is disposed within an inlet duct assembly. The heat exchanger includes a heat exchanger with a front facing area that is greater than an area of the inlet duct that is transverse to a longitudinal length of the inlet duct.

A pump of a dishwasher has an integrated heating element, a pump chamber with an inlet and an outlet, a pump rotor inside the pump chamber and a drive motor, wherein the heating element and a temperature sensor are provided on a wall of the pump chamber. For measuring a calcification of the pump chamber it is filled with water and then the pump rotor rotates for mixing the water in the pump chamber without transporting water out of the pump chamber. The temperature of the water in the pump chamber is measured with the temperature sensor as a starting temperature, and then the heating element is activated to heat the water in the pump chamber while the temperature of the water in the pump chamber is measured. Then the heating element is deactivated and the maximum temperature of the water during the heating duration or directly afterwards is determined. A temperature relation between the maximum temperature and the starting temperature of the water is calculated. These steps are executed in the pump at the very beginning of an operation of the new dishwasher after its installation for determining an initial temperature relation. These steps are automatically executed again at a later stage for determining a later temperature relation to determine the heating efficiency of the pump by comparing the later temperature relation to the initial temperature relation.

A turbine blade including an airfoil portion having a leading edge, a trailing edge, and a pressure surface and a suction surface extending between the leading edge and the trailing edge. The airfoil portion internally forming a cooling passage, which includes first and second cooling passages, and a plurality of outflow passages each having one end which opens to a merging portion formed by connecting an end portion of the first cooling passage on a side of the trailing edge and an end portion of the second cooling passage on the side of the trailing edge, and another end which opens to the trailing edge. The first cooling passage and the second cooling passage are divided by a partition member disposed in the airfoil portion. The cooling passage includes pressure side pin fins in the first cooling passage, and suction side pin fins in the second cooling passage.

A self-rotation graphene heat-dissipation device for a direct-drive electro-hydrostatic actuator, that includes inner and outer walls of a shell eccentrically arranged relative to each other, the shell sleeves on an outer side of a self-rotation mechanism. The self-rotation mechanism is arranged on an outer side of a shaft; the shaft is coaxial with the inner wall of the shell and connected with outer and inner end covers. The self-rotation mechanism includes a rotor and blades, the rotor sleeves on the shaft and is connected with the outer and inner end covers. The rotor is slidably connected with the blades, and outer walls of the blades are closely attached to the inner wall of the shell. Graphene heat-dissipation layers are coated on outer walls of all of the shell, blades, the rotor, the inner and outer end covers respectively.

A sensor assembly includes a housing defining a potting chamber and arranged along a sensor axis, a mounting flange extending about the sensor axis the axially offset along the sensor axis from the housing, and one or more intermediate flange. The one or more intermediate flange is arranged between the housing and the mounting flange along the sensor axis, the one or more intermediate flange coupling the mounting flange to the housing. The one or more intermediate flange is spaced apart from mounting flange to limit thermal communication between the mounting flange and the housing. Gas turbine engines and methods of cooling sensor assemblies are also described.