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US 8,505,304 B2Granted
Fuel nozzle detachable burner tube with baffle plate assembly
AssigneeGeneral Electric Company
InventorsGeoffrey D. Myers, Scott Simmons, Stephen R. Thomas, Donald Mark Bailey, David Martin Johnson
Life of this patent
Estimating the term…
Abstract
A fuel nozzle for use with a combustion chamber defined within a gas turbine engine and a method for assembling the same are provided. The fuel nozzle includes a swirler assembly and a burner tube that is coupled to a support flange in a detachable manner such that an inner surface of the burner tube circumscribes an outer surface of the swirler assembly during fuel nozzle operation.
Claims11
A method for assembling a fuel nozzle for use with a combustion chamber defined within a gas turbine engine, said method comprising:
- providing a support flange;
- providing a swirler assembly;
- providing a burner tube, including a base region, a side wall, and a plurality of air passage openings formed in the side wall adjacent to the base region;
- providing a baffle plate assembly including a baffle plate and an air guide vane coupled downstream of the baffle plate and located radially inward from the burner tube;
- coupling the burner tube to the support flange in a detachable manner, such that an inner surface of the burner tube circumscribes an outer surface of the swirler assembly during fuel nozzle operation;
- and
- coupling the baffle plate assembly to a stem that is radially inward from the burner tube, wherein the baffle plate assembly is oriented to channel airflow within the fuel nozzle towards the swirler assembly,
- wherein the swirler assembly is fabricated from a first material having a first coefficient of thermal expansion and the burner tube is fabricated from a second material having a second coefficient of thermal expansion that is different from the first coefficient of thermal expansion, and
- wherein at resting temperature, the burner tube is axially slidable towards and away from the support flange.
6 more elements
A fuel nozzle configured to channel fluid toward a combustion chamber defined within a gas turbine, said fuel nozzle comprising:
- a support flange;
- a swirler assembly;
- a burner tube comprising a base region, a side wall, and a plurality of air passage openings formed in the side wall adjacent to said base region;
- and
- a baffle plate assembly comprising a baffle plate and an air guide vane coupled downstream of the baffle plate and located radially inward from said burner tube,
- wherein said baffle plate assembly is oriented to channel airflow within said fuel nozzle towards the swirler assembly,
- wherein said burner tube is coupled to said support flange in a detachable manner, such that an inner surface of said burner tube circumscribes an outer surface of said swifter assembly during fuel nozzle operation,
- wherein said swirler assembly is fabricated from a first material having a first coefficient of thermal expansion and said burner tube is fabricated from a second material having a second coefficient of thermal expansion that is different from the first coefficient of thermal expansion, and
- wherein at resting temperature, said burner tube is axially slidable towards and away from said support flange.
6 more elements
A gas turbine engine comprising:
- a combustion chamber;
- and
- a fuel nozzle configured to channel fluid toward said combustion chamber, said fuel nozzle comprising:
- a swirler assembly;
- a burner tube comprising a base region, a side wall, and a plurality of air passage openings formed in the side wall adjacent to said base region;
- a support flange;
- and
- a baffle plate assembly comprising a baffle plate and an air guide vane coupled downstream of the baffle plate and located radially inward from said burner tube,
- wherein said baffle plate assembly is oriented to channel airflow within said fuel nozzle towards the swirler assembly,
- wherein said burner tube is coupled to said support flange in a detachable manner, such that an inner surface of said burner tube circumscribes an outer surface of said swirler assembly during fuel nozzle operation,
- wherein said swirler assembly is fabricated from a first material having a first coefficient of thermal expansion and said burner tube is fabricated from a second material having a second coefficient of thermal expansion that is different from the first coefficient of thermal expansion, and
- wherein at resting temperature, said burner tube is axially slidable towards and away from said support flange.
9 more elements
Dependencies are inferred from the claim text.