Abstract: A system for managing fuel temperature in an engine includes a source of hot pressurized air and a turbine for converting hot pressurized air into cool expanded air. The system further includes a fuel tank for storing fuel, a fuel conduit fluidly connected to the fuel tank, and a first heat exchanger located on the fuel conduit. The first heat exchanger places the cool expanded air from the turbine in a heat exchange relationship with the fuel, thereby cooling the fuel.

Abstract: An emergency power system is useable on an aircraft having a gas turbine engine with a low pressure spool and a high pressure spool. The emergency power system includes an emergency electrical generator coupled to the low pressure spool during an emergency for generating emergency electrical power and one or more additional electrical power sources. A plurality of electrical loads are electrically connected to the emergency electrical generator and the one or more additional electrical power sources. Aircraft sensors provide data regarding emergency electrical power availability and emergency electrical power demand. A controller for controlling the emergency electrical generator determines emergency electrical power demand and emergency electrical power availability based upon data from the aircraft sensors. The controller controls the emergency electrical generator based upon the emergency electrical power demand and the emergency electrical power availability.

Abstract: A method for managing heat in an airplane includes extracting hot bleed air from a gas turbine engine, and cooling the hot bleed air in a first heat exchanger thereby forming warm bleed air. The method further includes expanding the warm bleed air with a turbine thereby forming cool bleed air, and using the cool bleed air as a heat sink in a second heat exchanger associated with an environmental control system and thereby forming used bleed air.

Abstract: An aircraft power distribution architecture including an Auxiliary Power Unit, a power distributor, and an electric generator distributes power to multiple aircraft systems.

Abstract: A system and method are disclosed for supplying fuel to an auxiliary power unit of an aircraft. The system includes a primary fuel source, a secondary fuel source, and a secondary valve. The primary fuel source is in fluid communication with the auxiliary power unit to provide a primary fuel thereto. Similarly, the secondary fuel source is in fluid communication with the auxiliary power unit to provide a secondary fuel thereto. The secondary valve regulates flow of the secondary fuel from the secondary fuel source to the auxiliary power unit. The method provides a secondary fuel from a secondary fuel source to the auxiliary power unit if an emergency operating condition experienced by the aircraft results from either exhaustion or contamination of a primary fuel.

Abstract: A method for controlling an aircraft power system having a plurality of generators includes determining a load set for controlling aircraft power as a function of a number of generators providing power and as a function of a health status of a load to be included in said load set.

Abstract: A disclosed emergency power system includes multiple emergency power devices that are each sized to provide partial power during emergency operation and/or full power for a portion of emergency operation.

Abstract: A gas turbine engine includes a main compressor section for compressing air, a main combustor section positioned downstream of the main compressor section, a main turbine section positioned downstream of the main combustor section, and a spool extending from the main compressor section to the main turbine section. A second turbine is fluidically connected to the main compressor section by a bleed passage. An electrical generator is mechanically driven by both the spool and the second turbine.

Abstract: A cooling system includes a compressor for compressing a refrigerant from a subcritical state to a supercritical state, a cooler for transferring heat from the refrigerant, an expander for expanding the refrigerant in the supercritical state, an expansion valve for expanding the refrigerant from the supercritical state to the subcritical state and an evaporator for transferring heat from a cooling fluid to the refrigerant in the subcritical state. Work extracted by the expander provides power to the compressor. A method for cooling a vehicle includes compressing a refrigerant from a subcritical state to a supercritical state, cooling the refrigerant, expanding the refrigerant in the supercritical state where work produced by expanding the refrigerant is used to compress the refrigerant, expanding the refrigerant from the supercritical state to the subcritical state, cooling a cooling fluid with the refrigerant in the subcritical state and cooling vehicle components with the cooling fluid.

Abstract: A gas turbine engine includes a main compressor section for compressing air, a main combustor section positioned downstream of the main compressor section, a main turbine section positioned downstream of the main combustor section, and a spool extending from the main compressor section to the main turbine section. A second turbine is fluidically connected to the main compressor section by a bleed passage. An electrical generator is mechanically driven by both the spool and the second turbine.