Abstract: An anti-icing system for an engine section stator of a gas turbine engine. The system includes an environmental control system pre-cooler heat exchange system and a conduit. The environmental control system pre-cooler heat exchange system is configured to exchange heat between air bled from a compressor of the engine and bypass duct air. The conduit is configured to exchange heat from the pre-cooler heat exchange system to a heat transfer medium. The conduit is also configured to transfer the heat from the heat transfer medium to the engine section stator.

Abstract: A cooling system for a gas turbine engine. The system includes a fuel air heat exchanger with a fuel passage that is in thermal contact with an engine cooling air passage. The system further includes a fuel deoxygenator located upstream of the fuel air heat exchanger and configured to deliver deoxygenated fuel to the fuel air heat exchanger fuel passage. The system also includes a valve configured to moderate engine cooling air flow to the engine cooling air passage.

Abstract: A fluid heat management system for an aircraft gas turbine engine. The system includes an oil to air heat exchanger configured to transfer heat from engine oil to bypass air, an oil to fuel heat exchanger configured to transfer heat from engine oil to fuel, and a phase change material in thermal contact with the oil upstream of the oil to fuel heat exchanger. The phase change material has a phase change temperature at a predetermined fuel target temperature.

Abstract: The invention relates to a heat exchanger 10, comprising: a first unit 12 having a first conduit 16 for passing a flow of a first fluid through the first unit 12; a second unit 14 having a second conduit 28 for passing a flow of a second fluid through the second unit 28, wherein the flow of the first fluid is isolated from the second unit 14 and the flow of the second fluid is isolated from the first unit 12; and, a third conduit 40 connecting the first 12 and second 14 units, wherein the third conduit 40 is for carrying a flow of an intermediate fluid between the first 12 and second 14 units so as to transfer heat between the first fluid and the second fluid, when in use.

Abstract: An anti-icing system (100) for an engine section stator (26) of a gas turbine engine (10), the system (100) comprising: an environmental control system pre-cooler heat exchange system (116) configured to exchange heat between air bled from a compressor (14, 16) of the engine (10) and bypass duct air; and a conduit (132) configured to exchange heat from the pre-cooler heat exchange system (116) to a further a heat transfer medium, the conduit (132) being configured to transfer the heat from the heat transfer medium to the engine section stator (26).

Abstract: A cooling system for a gas turbine engine (10). The system is comprises a fuel air heat exchanger (78) comprising a fuel passage (80) in thermal contact with an engine cooling air passage (82). The system further comprises a fuel deoxygenator (72) located upstream of the fuel air heat exchanger (78) configured to deliver deoxygenated fuel to the fuel air heat exchanger fuel passage (80). The system includes a valve (84) configured to moderate engine cooling air flow to the engine cooling air passage (82).

Abstract: The invention relates to a heat exchanger 10, comprising: a first unit 12 having a first conduit 16 for passing a flow of a first fluid through the first unit 12; a second unit 14 having a second conduit 28 for passing a flow of a second fluid through the second unit 28, wherein the flow of the first fluid is isolated from the second unit 14 and the flow of the second fluid is isolated from the first unit 12; and, a third conduit 40 connecting the first 12 and second 14 units, wherein the third conduit 40 is for carrying a flow of an intermediate fluid between the first 12 and second 14 units so as to transfer heat between the first fluid and the second fluid, when in use.