Abstract: A plurality of vessels contains pressurized gas. Each vessel fluidly communicates with an adjacent vessel through a line. A heat exchanger is positioned in a heat conducting relationship with each line. The system includes an exhaust valve communicating with lower pressure. In one embodiment, the vessels communicate in series and only one of the vessels communicates with the exhaust valve. Alternatively, the vessels are arranged in a loop configuration with two of the vessels communicating with the exhaust valve through respective lines each containing a shutoff valve. The two shutoff valves are opened and closed in concert to cause the flow in the system to alternate directions as it is being exhausted. In a third configuration, two vessels communicate through a singular line in accordance with the most basic embodiment, but the vessel communicating with the exhaust valve encloses the other vessel. Heat transfer fins are located in the enclosed vessel, and extend into the enclosing vessel.

Abstract: A system for starting an APU, including an air control valve assembly located in the air flow passageway extending between a source of pressurized air and a turbine power modulator. The system further includes a fuel control valve assembly located in the fuel flow passageway extending between a source of jet fuel and the turbine power modulator. Upon energizing the air control and fuel control valves, a mixture of compressed air and jet fuel entering the turbine power module is ignited, creating a flow steam of hot gases for driving a gas turbine to power the APU.

Abstract: A plurality of vessels contains pressurized gas. Each vessel fluidly communicates with an adjacent vessel through a line. A heat exchanger is positioned in a heat conducting relationship with each line. The system includes an exhaust valve communicating with lower pressure. In one embodiment, the vessels communicate in series and only one of the vessels communicates with the exhaust valve. Alternatively, the vessels are arranged in a loop configuration with two of the vessels communicating with the exhaust valve through respective lines each containing a shutoff valve. The two shutoff valves are opened and closed in concert to cause the flow in the system to alternate directions as it is being exhausted. In a third configuration, two vessels communicate through a singular line in accordance with the most basic embodiment, but the vessel communicating with the exhaust valve encloses the other vessel. Heat transfer fins are located in the enclosed vessel, and extend into the enclosing vessel.

Abstract: A system for starting an APU, including an air control valve assembly located in the air flow passageway extending between a source of pressurized air and a turbine power modulator. The system further includes a fuel control valve assembly located in the fuel flow passageway extending between a source of jet fuel and the turbine power modulator. Upon energizing the air control and fuel control valves, a mixture of compressed air and jet fuel entering the turbine power module is ignited, creating a flow steam of hot gases for driving a gas turbine to power the APU.

Abstract: A multifunction secondary power system (10) for use aboard an aircraft or other vehicle provides the functions both of an auxiliary power unit and of an emergency power unit. The power system (10) includes two turbine engines (12, 22) operable under differing conditions, a gearbox (34) receiving power from the two engines (12, 22) selectively through overrunning clutches (74,84), and a plurality of accessory devices (36, 38, 40) receiving shaft power from either of the two engines (12, 22) through the gearbox (34). The gear box (34) includes a third clutch (64) operably interposed between the clutches (74, 84) which selectively delivers shaft power from the engine (22) to the engine (12) to affect the start thereof.

Abstract: A multifunction secondary power system (10) for use aboard an aircraft or other vehicle provides the functions both of an auxiliary power unit and of an emergency power unit. The power system (10) includes two turbine engines (12, 22) operable under differing conditions, a gearbox (34) receiving power from the two engines (12, 22) selectively through overrunning clutches (74,84), and a plurality of accessory devices (36, 38, 40) receiving shaft power from either of the two engines (12, 22) through the gearbox (34). The gear box (34) includes a third clutch (64) operably interposed between the clutches (74, 84) which selectively delivers shaft power from the engine (22) to the engine (12) to affect the start thereof.

Abstract: An aircraft emergency power unit having a high pressure air storage tank, an aviation fuel storage tank, and a combustor which combusts pressurized air and aviation fuel in a stoichiometrically fuel rich ratio to produce a motive combustion gas.

Abstract: An aircraft emergency power unit having a high pressure air storage tank, an aviation fuel storage tank, and a combustor which combusts pressurized air and aviation fuel in a stoichiometrically fuel rich ratio to produce a motive combustion gas.

Abstract: An aircraft emergency power unit having a high pressure air storage tank, an aviation fuel storage tank, and a combustor which combusts pressurized air and aviation fuel in a stochiometrically fuel rich ratio to produce a motive combustion gas.