Curtiss-Wright Corporation

Anthony Leto

Rossa W Cole

Emmett S Harrison

A combustion chamber for burning low BTU fuel comprising a generally cylindrical casing having adjacent outer and inner annular spaces defined by outer, intermediate and inner walls, the spaces intercommunicating at the downstream end of the casing thereby providing a U-shaped flow path. The outer annular space traverses the entire length of the casing while the inner space extends to the approximate mid-point of the casing, thereby communicating with internally disposed combustion units. In operation, fuel as coolant is fed to the outer space at the upstream end, traverses the U-shaped flow-path thus making a double pass around the combustion zone of the combustion chamber and thence to the combustion units for ignition. Improved cooling is obtained.

Low BTU gas combustor

A fuel burner and combustor assembly for a gas turbine engine has a housing within the casing of the gas turbine engine which housing defines a combustion chamber and at least one fuel burner secured to one end of the housing and extending into the combustion chamber. The other end of the fuel burner is arranged to slidably engage a fuel inlet connector extending radially inwardly from the engine casing so that fuel is supplied, from a source thereof, to the fuel burner. The fuel inlet connector and fuel burner coact to anchor the housing against axial movement relative to the engine casing while allowing relative radial movement between the engine casing and the fuel burner and, at the same time, providing fuel flow to the fuel burner. For dual fuel capability, a fuel injector is provided in said fuel burner with a flexible fuel supply pipe so that the fuel injector and fuel burner form a unitary structure which moves with the fuel burner.

Fuel burner and combustor assembly for a gas turbine engine

A turbojet afterburner engine has an expendable nozzle portion which can be jettisoned when the afterburner is placed in operation.

Turbojet afterburner engine with two-position exhaust nozzle

The dual-fuel feed system for a gas turbine engine, having a plurality of fuel nozzles arranged to effect admixture of air and fuel in a combustor of the engine for combustion of fuel, comprises a fuel feed conduit means communicating with each of the fuel nozzles and separate sources of different fuels and flow control means for alternating flow of fuel from one source or the other to the fuel nozzles.

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Franklin Lakes, NJ, United States of America

Anthony Leto