In a gas turbine engine compressor power unit fuel is supplied at an essentially constant pressure to a fuel nozzle for injection into the combustion liner of the power unit's combustor. Nozzle fuel flow is modulated solely by bleeding off combustor supply air to vary the internal liner pressure, thereby altering the fuel pressure drop across the nozzle.

Compressor power unit fuel flow control

An improved augmentor fuel supply system including a fuel source, a pump for pressurizing the fuel, a flow control means for controlling the flow and pressure of fuel to a fuel disbursement means (e.g., an augmentor) and a return path for recirculating unburned fuel. The flow control means includes a restrictor means such as a small orifice in parallel with a controllable valve. The restrictor means allows fuel to flow to the fuel disbursement means when the controllable valve is shut off. Further, according to the present invention, a second restrictor means, such as a small orifice is included in the return path. Finally, a check valve is included in the return path to ensure that fuel does not flow into the augmentor through the return path.

Continuous flow fuel circulation system

A method and apparatus for heating fuel in an aircraft gas turbine engine, for example to provide fuel anti-icing to the fuel, comprises directing a fuel flow through a heat exchanger associated with a generator power conditioning unit as a sole means for providing anti-icing heating to fuel supplied for engine combustion. The method and apparatus permits the heat exchanger to heat the fuel sufficiently so that other dedicated heating means may be unnecessary.

Fuel system for gas turbine engine

An auxiliary gas turbine in an aircraft is driven by adding dimethyl-hydrazine to Kerosine and producing propellant gas by adding HNO 3 or N 2 O 4 as oxidizer. Additional Kerosine is injected into the resulting gas for matching the gas constant of that gas to the gas constant of regular combustion gas which normally drives the turbine.

Formation of auxiliary drive gas for turbine

In a gas turbine power plant, pressurized fuel gas undergoes pressure reduction and gas expansion before being provided to a gas turbine. Condensations, which can damage the turbine, can form as the fuel gas cools when the fuel gas undergoes the pressure reduction and expansion. An electric startup heater is used to superheat the fuel gas to substantially prevent the condensations from forming. The electric startup heater includes band heaters wrapped externally to a fuel gas pipe to heat the fuel gas from outside in. Compared to conventional heaters which provide superheating through internal heating elements, the electric startup heater reduces costs and provides increased safety, flexibility, operational efficiency and ability to adapt to varying fuel gas characteristics.

System and method for applying energy externally for fuel gas for dew point heating in gas turbine power plant

An arrangement and method to heat fuel under constant volume to a temperature at which it will flash at the ambient pressure in the combustion chamber and then admit the fuel through a valve to the combustion chamber where the fuel mixes with air and spontaneously flashes into flame.

Spontaneous ignition of fuel in a combustion chamber

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Spontaneous ignition of fuel in a combustion chamber