An oil cooling system for an aircraft engine, a bypass valve and an associate method of cooling aircraft engine oil are provided. The oil cooling system includes a heat exchanger having an inlet and an outlet. The inlet is in fluid communication with a first oil conduit to receive a first oil flow from the first oil conduit. The heat exchanger facilitates heat transfer from the first oil flow to another fluid. A flow restrictor defining a constriction is operatively disposed to restrict the first oil flow through the heat exchanger. A second oil conduit receives the first oil flow from the heat exchanger. A bypass oil passage provides fluid communication between the first oil conduit and the second oil conduit to allow a second oil flow received from the first oil conduit to flow to the second oil conduit and bypass the heat exchanger.

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 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 fuel conditioning and control system provides dynamic control and steady state operations of a gas turbine provided fueled by supercritical liquefied petroleum gas (LPG). The fuel conditioning and control system comprises a storage for LPG fuel; a fuel delivery sub-system connecting the storage to turbomachinery; and a control system. The gas turbine includes a gas turbine core control that provides at least one operational data of the gas turbine to the control system. The fuel delivery sub-system includes at least one sensor for sensing at least one property of the LPG fuel in the fuel delivery sub-system, where the at least one sensor providing data on the at least one property of the LPG fuel to the control system. The control system analyzes the data on the at least one property of the LPG fuel and at least one operational data of the gas turbine for dynamic control of LPG fuel to the gas turbine under dynamic and steady state conditions.

A fuel conditioning and control system provides dynamic control and steady state operations of a gas turbine provided fueled by supercritical liquefied petroleum gas (LPG). The fuel conditioning and control system comprises a storage for LPG fuel; a fuel delivery sub-system connecting the storage to turbomachinery; and a control system. The gas turbine includes a gas turbine core control that provides at least one operational data of the gas turbine to the control system. The fuel delivery sub-system includes at least one sensor for sensing at least one property of the LPG fuel in the fuel delivery sub-system, where the at least one sensor providing data on the at least one property of the LPG fuel to the control system. The control system analyzes the data on the at least one property of the LPG fuel and at least one operational data of the gas turbine for dynamic control of LPG fuel to the gas turbine under dynamic and steady state conditions.

A propulsion assembly for an aircraft, comprising a nacelle, a propulsion system housed in the nacelle and comprising a fairing, a rotary assembly that has a combustion chamber and is housed in the fairing, an exhaust nozzle delimited by a nozzle wall of the fairing, a fuel tank, a supply duct which connects the tank and the combustion chamber, and a heat exchanger system ensuring, during operation of the propulsion system, an exchange of heat energy between the hot combustion gases circulating in the nozzle and the colder fuel circulating in the supply duct by thermal radiation through the nozzle wall.

A gas turbine engine includes a primary gas path having, in fluid series communication: a primary air inlet, a compressor fluidly connected to the primary air inlet, a combustor fluidly connected to an outlet of the compressor, and a turbine fluidly connected to an outlet of the combustor. The turbine is operatively connected to the compressor to drive the compressor. A turbine cooling air conduit extends from an air inlet of the turbine cooling air conduit to an air outlet of the turbine cooling air conduit.

A gas turbine engine includes a primary gas path having, in fluid series communication: a primary air inlet, a compressor fluidly connected to the primary air inlet, a combustor fluidly connected to an outlet of the compressor, and a turbine fluidly connected to an outlet of the combustor. The turbine is operatively connected to the compressor to drive the compressor. A turbine cooling air conduit extends from an air inlet of the turbine cooling air conduit to an air outlet of the turbine cooling air conduit.

Disclosed is a hybrid power generation facility. The hybrid power generation facility includes a gas turbine including a compressor configured to compress air introduced from an outside, a combustor configured to mix the compressed air with fuel and to combust the air and fuel mixture, and a turbine configured to produce power with first combustion gas discharged from the combustor, a boiler including a combustion chamber and a burner installed in the combustion chamber and into which the first combustion gas discharged from the turbine of the gas turbine is introduced, a steam turbine through which steam generated in the combustion chamber passes, a first GT (gas turbine) pipeline connected between the turbine of the gas turbine and the burner, a first air pipeline connected to the first GT pipeline to supply oxygen to the burner, a first oxygen sensor installed at an inlet of the burner to measure an oxygen concentration of a fluid flowing into the burner, and a first GT damper installed in the first GT pipeline to control a flow rate of the fluid flowing through the first GT pipeline according to the oxygen concentration measured by the first oxygen sensor.

Disclosed is a hybrid power generation facility. The hybrid power generation facility includes a gas turbine including a compressor configured to compress air introduced from an outside, a combustor configured to mix the compressed air with fuel and to combust the air and fuel mixture, and a turbine configured to produce power with first combustion gas discharged from the combustor, a boiler including a combustion chamber and a burner installed in the combustion chamber and into which the first combustion gas discharged from the turbine of the gas turbine is introduced, a steam turbine through which steam generated in the combustion chamber passes, a first GT (gas turbine) pipeline connected between the turbine of the gas turbine and the burner, a first air pipeline connected to the first GT pipeline to supply oxygen to the burner, a first oxygen sensor installed at an inlet of the burner to measure an oxygen concentration of a fluid flowing into the burner, and a first GT damper installed in the first GT pipeline to control a flow rate of the fluid flowing through the first GT pipeline according to the oxygen concentration measured by the first oxygen sensor.