Method and apparatus for high altitude starting of gas turbine engine

Claim 1

A method of starting a gas turbine engine at high altitude comprising the steps of: (a) introducing fuel into the combustor of the engine through at least one fuel injector including an elongated conduit having an outlet within the combustor; (b) atomizing the fuel with a burst or oxidant at elevated pressure from a source pressurized stored oxidant until ignition is obtained by introducing said burst into said elongated conduit from a location internal to the injector(s) and upstream of said outlet to atomize fuel in said elongated conduit and such that said atomized fuel is ejected from said outlet of said conduit in a spray generally tangential to an outer wall of said combustor; and (c) thereafter discontinuing the burst of oxidant from said source.

Claim 2

A method of starting a gas turbine engine at high altitude comprising the steps of: (a) introducing fuel into the combustor of the engine through at least one fuel injector including an elongated conduit having an outlet within the combustor; (b) atomizing the fuel with a burst or oxidant at elevated pressure from a source pressurized stored oxidant until ignition is obtained by introducing said burst into said elongated conduit from a location internal to the injector(s) and upstream of said outlet to atomize fuel in said elongated conduit and such that said atomized fuel is ejected from said outlet of said conduit in a spray generally tangential to an outer wall of said combustor; and (c) thereafter discontinuing the burst of oxidant from said source.

Claim 4

A method of high altitude starting a gas turbine having a rotary compressor driven by a turbine wheel, a nozzle for directing gases of combustion at the turbine wheel and connected to the outlet of an annular combustor, a plenum in fluid communication with the compressor and disposed about the combustor and a plurality of angularly spaced air blast atomization fuel injectors about said combustor and each including a housing having an outlet within the combustor, an air inlet within the plenum and an elongated fuel tube extending within the housing into proximity to the outlet and defining a fuel injection port thereat, and a fuel metering formation within said fuel tube upstream of said fuel injection port, the steps of: a) injecting fuel into said combustor through said fuel tube at a relatively low flow rate; b) momentarily subjecting the fuel in said elongated fuel tube upstream of said port to a blast of oxidant at an elevated pressure and taken from a compressed oxidant storage vessel, said blast atomizing said fuel in said fuel tube and said fuel tube ejecting said atomized fuel from said port in a spray generally tangential to an outer wall of said combustor; and c) igniting the fuel.

Claim 5

A method of high altitude starting a gas turbine having a rotary compressor driven by a turbine wheel, a nozzle for directing gases of combustion at the turbine wheel and connected to the outlet of an annular combustor, a plenum in fluid communication with the compressor and disposed about the combustor and a plurality of angularly spaced air blast atomization fuel injectors about said combustor and each including a housing having an outlet within the combustor, an air inlet within the plenum and an elongated fuel tube extending within the housing into proximity to the outlet and defining a fuel injection port thereat, and a fuel metering formation within said fuel tube upstream of said fuel injection port, the steps of: a) injecting fuel into said combustor through said fuel tube at a relatively low flow rate; b) momentarily subjecting the fuel in said elongated fuel tube upstream of said port to a blast of oxidant at an elevated pressure and taken from a compressed oxidant storage vessel, said blast atomizing said fuel in said fuel tube and said fuel tube ejecting said atomized fuel from said port in a spray generally tangential to an outer wall of said combustor; and c) igniting the fuel.

Claim 7

A method of high altitude starting an aircraft carried gas turbine having a rotary compressor driven by a turbine wheel, a nozzle for directing gases of combustion at the turbine wheel and connected to the outlet of an annular combustor, a plenum and fluid communication with the compressor and disposed about the combustor and a plurality of angularly spaced air-blast atomization fuel injectors about said combustor and each including a housing having an outlet within the combustor, an air inlet within the plenum and an elongate fuel tube extending within the housing into proximity to the outlet, the end of the fuel tube adjacent said outlet defining a fuel injection port, and a fuel metering formation within said fuel tube upstream of said fuel injection port, the steps of: a) injecting fuel into said combustor through said fuel tube at a relatively low fuel rate; b) momentarily subjecting the fuel at said port to a blast of oxidant at an elevated pressure from a compressed oxidant storage vessel, wherein said oxidant is directed by an elongated oxidant tube surrounding and substantially concentric with said fuel tube, and wherein said fuel is atomized and directed in a spray generally tangential to an outer wall of said combustor by said oxidant in said oxidant tube; and c) igniting the fuel.

Claim 8

A method of high altitude starting an aircraft carried gas turbine having a rotary compressor driven by a turbine wheel, a nozzle for directing gases of combustion at the turbine wheel and connected to the outlet of an annular combustor, a plenum and fluid communication with the compressor and disposed about the combustor and a plurality of angularly spaced air-blast atomization fuel injectors about said combustor and each including a housing having an outlet within the combustor, an air inlet within the plenum and an elongate fuel tube extending within the housing into proximity to the outlet, the end of the fuel tube adjacent said outlet defining a fuel injection port, and a fuel metering formation within said fuel tube upstream of said fuel injection port, the steps of: a) injecting fuel into said combustor through said fuel tube at a relatively low fuel rate; b) momentarily subjecting the fuel at said port to a blast of oxidant at an elevated pressure from a compressed oxidant storage vessel, wherein said oxidant is directed by an elongated oxidant tube surrounding and substantially concentric with said fuel tube, and wherein said fuel is atomized and directed in a spray generally tangential to an outer wall of said combustor by said oxidant in said oxidant tube; and c) igniting the fuel.