A thermal energy system for use with an aircraft includes a cooling loop and a cooler. The cooling loop includes a fluid conduit and a pump configured to move fluid through the fluid conduit to transfer heat from a heat source to the fluid in the fluid conduit to cool the heat source. The cooler includes an air-stream heat exchanger located in a duct and is in thermal communication with the fluid conduit to transfer heat between the fluid in the cooling loop and the air passing through the duct.

A gas turbine engine includes a compressor, an annular casing surrounding the compressor, and a bleed flow adapter mounted to an exterior side of the annular casing. The annular casing includes the exterior side and an interior side. The interior side surrounds a compressor bleed cavity located downstream of at least a portion of the compressor. The bleed flow adapter is in fluid communication with the bleed cavity. The bleed flow adapter includes an inlet end, an outlet end, and an inner diameter surface extending between the inlet end and the outlet end. The inner diameter surface defines a bleed passage. The bleed flow adapter further includes a fluid port formed through the inner diameter surface. The gas turbine engine further includes a bleed flow measurement system including a first pressure sensor in fluid communication with the bleed passage of the bleed flow adapter via the fluid port.

Methods and systems are provided for a turbocharger. In one example, a method may include flowing bleed air to control a catalyst temperature. The bleed air is directed from a bleed port of a compressor of an engine system.

An annular fluid flow control or metering device comprises: first and second annular plates disposed in an annular flow path, the first annular plate and second annular plates being made of different first and second materials, the first annular plate having a lower first coefficient of thermal expansion than a second coefficient of thermal expansion of the second annular plate, the first annular plate abutting or in contact with the second annular plate, the first annular plate including at least one first metering aperture, and the second annular plate being more thermally responsive than the first annular plate wherein the second annular plate being configured to radially grow and shrink to at least partly obstruct the at least one first metering aperture for metering or controlling a flow of fluid through the at least one first metering aperture.

A control system for turbine systems configured to utilize an intelligent model of particulate presence and accumulation within turbine systems to address engine maintenance, erosion, corrosion, and parts failure mitigation is disclosed. The control system may build an intelligent model of fluid flow based on the data value measured by at least one sensor and based on a database of known data values to provide an estimation of amount of ingress of air intake particles into the turbine system, fouling within the turbine system, erosion of at least a portion of the turbine system, and performance degradation rate of the turbine system.

A method of detecting an airflow fault condition in a gas turbine engine, the method including: operating the gas turbine engine with a thermal transport bus having an intermediary heat exchange fluid flowing therethrough; determining a performance characteristic of the intermediary heat exchange fluid in the thermal transport bus is outside of a predetermined range, wherein the performance characteristic includes a temperature, a pressure, a flowrate, or a combination thereof; and indicating an airflow fault condition in response to determining the performance characteristic is outside of the predetermined range.

A controller includes: a control unit configured to calculate a control command value of an opening degree of a solenoid valve to control an opening degree of the solenoid valve; and an acquisition unit configured to acquire an estimated amount and a target amount of a working fluid in a labyrinth chamber, and a rotation speed of a drive shaft. The control unit calculates a final control command value based on a feedback control command value and a feedforward control command value, and controls the solenoid valve, the feedback control command value being calculated based on deviation between the estimated amount and the target amount, the feedforward control command value being used to maintain a rotation speed of a fan constant based on the estimated amount and the rotation speed of the drive shaft.

An adaptive thermal management system for a gas turbine engine includes a heat exchanger transferring heat into a coolant, a temperature sensor measuring a temperature of the coolant, and a sensor assembly that measures a parameter of the coolant during operation of the gas turbine engine. The parameter measured by the sensor assembly is indicative of a capacity of the coolant to accept heat from the hot flow. A control valve governs a flow of coolant into the heat exchanger. A controller adjusts the control valve to communicate coolant to the heat exchanger based on a determined capacity of the coolant to accept heat in view of the measured temperature of the coolant and that the measured parameter of the coolant is within a predefined range.

A control system for turbine systems configured to utilize an intelligent model of particulate presence and accumulation within turbine systems to address engine maintenance, erosion, corrosion, and parts failure mitigation is disclosed. The control system may build an intelligent model of fluid flow based on the data value measured by at least one sensor and based on a database of known data values to provide an estimation of amount of ingress of air intake particles into the turbine system, fouling within the turbine system, erosion of at least a portion of the turbine system, and performance degradation rate of the turbine system.

A turbomachine including a turbine shaft supported by at least one bearing, at least one enclosure, housing the bearing of the turbine shaft, an oil cooling circuit of the enclosure including at least one jet configured to inject oil from the cooling circuit into the enclosure, and a regulator configured to regulate the flow of oil in the cooling circuit as a function of an oil temperature at output of the enclosure and a pressure difference at the level of the jet.