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US 4,891,936 AGranted
Turbine combustor with tangential fuel injection and bender jets
AssigneeSundstrand Corporation
InventorsJack R. Shekleton, Richard T. LeCren
Life of this patent
Estimating the term…
Abstract
The cost of fuel injection nozzles 50 and their tendency to clog in a gas turbine having an annular combustor 26 can be reduced by alternating the fuel injection nozzles 50 with bender jets 56 configured to introduce a combustion supporting gas into an annular combustion zone 40 at locations between the fuel injectors 50 to achieve uniform turbine inlet temperature distribution while requiring fewer of the nozzles 50 and allowing those nozzles 50 that are utilized to have larger fluid flow paths that are less prone to clogging.
Claims9
A gas turbine comprising:
- a rotor including compressor blades and turbine blades;
- an inlet adjacent one side of said compressor blades;
- a diffuser adjacent the other side of said compressor blades;
- a nozzle adjacent said turbine blades for directing hot gasses at said turbine blades to cause rotation of said rotor;
- and
- an annular combustor about said rotor and having an outlet connected to said nozzle and a primary combustion annulus remote from said outlet, a plurality of fuel injectors to said primary combustion annulus and being substantially equally angular spaced therearound and configured to inject fuel into said primary combustion annulus in a nominally tangential direction and at least an equal number of combustion supporting gas jets located about said primary combustion annulus in alternating relation with said fuel injectors, said jets being configured to introduce a combustion supporting gas into said primary combustion annulus in a nominally tangential direction, combustion supporting gas from said jets uniformly distributing burning fuel about said annulus to thereby enable the use of fewer fuel injectors while avoiding the presence of hot spots.
3 more elements
A gas turbine comprising
- a rotor including compressor blades and turbine blades;
- an inlet adjacent one side of said compressor blades;
- a diffuser adjacent the other side of said compressor blades;
- a nozzle adjacent said turbine blades for directing hot gasses at said turbine blades to cause rotation of said rotor;
- and
- an annular combustor about said rotor and having an outlet to said nozzle, an inner wall and an outer wall spaced therefrom, a plurality of fuel injectors at substantially equally angularly spaced locations about said outer wall and oriented generally tangentially to said inner wall, and a plurality of combustion supporting gas jets in said outer wall and located in alternating fashion with said fuel injectors.
3 more elements
A gas turbine comprising
- a rotor including compressor blades and turbine blades;
- an inlet adjacent one side of said compressor blades;
- a diffuser adjacent the other side of said compressor blades;
- a nozzle adjacent said turbine blades for directing hot gasses at said turbine blades to cause rotation of said rotor;
- and
- an annular combustor about said rotor and having first, second and third, generally concentric, spaced walls centered about said rotor, said first wall being radially inwardly of said second and third walls and said second wall being radially inwardly of said third wall, said first and second walls defining an annular combustor or combustion space having an outlet to said nozzle and said second and third walls defining an annular manifold for receiving compressed gas from said diffuser for combustion or for combustion and dilution and for cooling said second wall, a plurality of fuel injection nozzles ror injecting fuel at spaced locations into said space in a non radial generally non axial direction and a similar number of combustion supporting gas jets communicating between said space and said manifold and located between said injectors in alternating fashion therewith, said jets introducing gas into said space in a non radial, generally non axial direction.
3 more elements
Dependencies are inferred from the claim text.