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US 7,185,497 B2Granted
Rich quick mix combustion system
AssigneeHoneywell International Inc.
InventorsRodolphe Dudebout, Terrel E. Kuhn, Paul R. Yankowich, Frank J. Zupanc
Life of this patent
Estimating the term…
Abstract
A premix chamber for a combustor of a gas turbine engine comprises a cylindrical chamber having a premix chamber wall, the cylindrical chamber having a chamber inlet end longitudinally separated from a chamber outlet end along a central axis, a chamber inlet plate in communication with the premix chamber wall at the chamber inlet end, the chamber inlet plate having a fuel nozzle inlet hole disposed through the chamber inlet plate, the chamber inlet plate further comprising a plurality of swirler passages disposed through the chamber inlet plate, and the chamber outlet end being open. A method of producing turbine gas is also disclosed.
Claims15
A combustor for a gas turbine engine, comprising:
- a combustor inlet end longitudinally separated from a combustor outlet end along a combustor centerline;
- a premix chamber disposed at said combustor inlet end, said premix chamber in fluid communication with a primary combustion chamber,
- said primary combustion chamber in fluid communication with a secondary combustion chamber disposed at said combustor outlet end,
- said premix chamber comprising a cylindrical chamber having a premix chamber wall coaxially disposed about said combustor centerline,
- said cylindrical chamber having a chamber inlet end longitudinally separated from a chamber outlet end along said combustor centerline by a chamber length;
- a chamber inlet plate in communication with said premix chamber wall at said chamber inlet end;
- a fuel nozzle inlet hole disposed through said chamber inlet plate;
- a plurality of swirler passages disposed through said chamber inlet plate;
- and a fuel nozzle engaged with said chamber inlet plate within said fuel nozzle inlet hole,
- said chamber outlet end comprising a flair outlet opening expanding radially away from said combustor centerline into said primary combustion chamber,
- said primary combustion chamber comprising a combustor liner having a first frustoconical portion attached to a cylindrical portion,
- said cylindrical portion attached to a second frustoconical portion serially disposed along said combustor central axis,
- wherein a radius of said first frustoconical portion increases in an axial direction from said combustor inlet end to said combustor outlet end,
- wherein a radius of said cylindrical portion remains constant longitudinally along said combustor centerline,
- wherein a radius of said second frustoconical portion decreases in an axial direction along said combustor centerline from said combustor inlet end to said combustor outlet end,
- said secondary combustor disposed within said combustor liner, wherein a radius of said secondary combustor remains constant in an axial direction,
- wherein said primary combustor comprises a frustoconical heat shield disposed between said first frustoconical portion and said combustor centerline,
- wherein said secondary combustor comprises a plurality of intermediate jets disposed through said combustor liner,
- wherein said secondary combustor comprises a plurality of dilution holes disposed through said combustor liner, and
- wherein said plurality of dilution holes are located between said intermediate jets and said combustor outlet end.
17 more elements
A gas turbine engine comprising:
- a compressor in operable communication with a combustor module,
- said combustor module in operable communication with a turbine module,
- said combustor module comprising a combustor inlet end longitudinally separated from a combustor outlet end along a combustor centerline,
- a premix chamber disposed at said combustor inlet end,
- said premix chamber in fluid communication with a primary combustion chamber, said primary combustion chamber in fluid communication with a secondary combustion chamber disposed at said combustor outlet end,
- said premix chamber comprising a cylindrical chamber having a premix chamber wall disposed about said combustor centerline,
- said cylindrical chamber having a chamber inlet end longitudinally separated from a chamber outlet end along said combustor centerline,
- said chamber inlet end comprising a chamber inlet plate in communication with said premix chamber wall,
- said chamber inlet plate having a fuel nozzle inlet hole disposed through said chamber inlet plate,
- said chamber inlet plate further comprising a plurality of swirler passages disposed through said chamber inlet plate,
- a fuel nozzle engaged with said chamber inlet plate within said fuel nozzle inlet hole, and
- said chamber outlet end being open.
9 more elements
A gas turbine engine comprising:
- a compressor in operable communication with a combustor module,
- said combustor module in operable communication with a turbine module,
- said combustor module comprising a combustor inlet end longitudinally separated from a combustor outlet end along a combustor centerline,
- a premix chamber disposed at said combustor inlet end,
- said premix chamber in fluid communication with a primary combustion chamber, said primary combustion chamber in fluid communication with a secondary combustion chamber disposed at said combustor outlet end,
- said premix chamber comprising a cylindrical chamber having a premix chamber wall disposed about said combustor centerline,
- said cylindrical chamber having a chamber inlet end longitudinally separated from a chamber outlet end along said combustor centerline,
- said chamber inlet end comprising a chamber inlet plate in communication with said premix chamber wall,
- said chamber inlet plate having a fuel nozzle inlet hole disposed through said chamber inlet plate,
- said chamber inlet plate further comprising a plurality of swirler passages disposed through said chamber inlet plate,
- a fuel nozzle engaged with said chamber inlet plate within said fuel nozzle inlet hole, and
- said chamber outlet end comprising a flair outlet opening expanding radially away from said combustor centerline into said primary combustion chamber.
9 more elements
A method for producing turbine gas from a combustor, comprising the steps of:
- a) atomizing a fuel into a premix chamber of said combustor,
- b) premixing said fuel with a quantity of air, wherein said fuel and said air are mixed within said premix chamber for a residence time to produce an air fuel mixture,
- c) performing a primary combusting step, wherein said air fuel mixture is combusted in a primary combustion chamber of said combustor to produce a partial combustion mixture,
- d) performing a secondary combusting step, wherein said partial combustion mixture is directed through a necked down portion of said primary combustion chamber into a secondary combustion chamber, wherein a plurality of intermediate jets provide secondary combustion air to produce exhaust gas, followed by:
- e) diluting said exhaust gas, wherein dilution holes disposed through said secondary combustor provide dilution air, wherein said exhaust gas is diluted with said dilution air to produce turbine gas.
2 more elements
Dependencies are inferred from the claim text.