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US 5,263,316 AGranted
Turbine engine with airblast injection
AssigneeSundstrand Corporation
InventorJack R. Shekleton
Life of this patent
Estimating the term…
Abstract
Improved fuel atomization for turbine engines utilizing high viscosity fuels is accomplished in an engine having an annular combustor (26) by providing an air injector (52) which produces an air stream (50) generally tangentially directed into the combustor (26) to intersect a fuel spray or film (46) also generally tangentially directed into the combustor (26) by a fuel injector (48) to atomize fuel for ignition by an igniter (60) in an annular outer wall (34) of the combustor (26).
Claims26
A turbine engine, comprising:
- a rotary compressor;
- a turbine wheel coupled to said compressor for driven movement thereof;
- an annular combustor defining an annular combustion space disposed about said turbine wheel and in fluid communication with both said compressor and said nozzle, said combustor having at least one igniter mounted therein, said combustor being adapted to receive fuel from a source and air from said compressor and to combust fuel and air in said combustion space to generate said gases of combustion;
- impingement pressure fuel injection means for injecting fuel from said source into said combustor in a manner producing fuel spray or film within said combustor;
- and
- jet stream atomization means for injecting air from said compressor into said combustor in a manner producing an air stream within said combustor;
- said jet stream atomization means being positioned such that said air stream intersects said fuel spray or film of said impingement pressure fuel injection means at an acute angle to atomize the fuel.
4 more elements
A turbine engine, comprising:
- a rotary compressor;
- a turbine wheel coupled to said compressor for driven movement thereof;
- an annular nozzle proximate said turbine wheel for directing gases of combustion thereat;
- an annular combustor defining an annular combustion space disposed about said turbine wheel and in fluid communication with both said compressor and said nozzle, said combustor having an annular outer wall with at least one igniter mounted therein, said combustor being adapted to receive fuel from a source and air from said compressor and to combust fuel and air in said combustion space to generate said gases of combustion;
- a plurality of impingement pressure atomization fuel injectors for injecting fuel from said source into said combustor, each of said fuel injectors including means for producing a fuel spray or film, said fuel sprays or films being generally tangentially directed into said combustor;
- and
- a plurality of jet stream atomization air injectors for injecting air from said compressor into said combustor, each of said air injectors including means for producing an air stream, said air stream being generally tangentially directed into said combustor;
- said air injectors means being positioned such that at least one of said air streams intersects each of said fuel sprays or films of said fuel injectors at an acute angle to atomize the fuel.
5 more elements
A turbine engine, comprising:
- a rotary compressor;
- a turbine wheel coupled to said compressor for driven movement thereof;
- an annular nozzle proximate said turbine wheel for directing gases of combustion thereat;
- an annular combustor defining an annular combustion space disposed about said turbine wheel and in fluid communication with both said compressor and said nozzle, said combustor having an annular outer wall with at least one igniter mounted therein, said combustor being adapted to receive fuel from a source and air from said compressor and to combust fuel and air in said combustion space to generate said gases of combustion;
- a plurality of impingement pressure atomization fuel injectors for injecting fuel from said source into said combustor, each of said fuel injectors including means for producing a fuel spray or film directed generally tangentially into said combustor, each of said fuel injectors being integral with said annular outer wall of said combustor;
- and
- a plurality of jet stream atomization air injectors for injecting air from said compressor into said combustor, each of said air injectors including means for producing an air stream directed generally tangentially into said combustor, each of said air injectors being integral with said annular outer wall of said combustor;
- said air injectors being greater in number than said fuel injectors;
- said air injectors being positioned such that at least one of said air streams intersects each of said fuel sprays or films of said fuel injectors at an acute angle to atomize the fuel.
6 more elements
Dependencies are inferred from the claim text.