Fuel nozzle detachable burner tube with baffle plate assembly
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F23R-003/14
출원번호
US-0325559
(2008-12-01)
등록번호
US-8505304
(2013-08-13)
발명자
/ 주소
Myers, Geoffrey D.
Simmons, Scott
Thomas, Stephen R.
Bailey, Donald Mark
Johnson, David Martin
출원인 / 주소
General Electric Company
대리인 / 주소
Armstrong Teasdale LLP
인용정보
피인용 횟수 :
9인용 특허 :
11
초록▼
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 tub
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.
대표청구항▼
1. 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 forme
1. 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; andcoupling 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, andwherein at resting temperature, the burner tube is axially slidable towards and away from the support flange. 2. A method for assembling a fuel nozzle in accordance with claim 1, wherein the burner tube is fabricated from the second material and a third material, wherein the third material is capable of withstanding a higher material temperature than the second material. 3. A method for assembling a fuel nozzle in accordance with claim 1, wherein said coupling the burner tube further comprises: coupling the burner tube such that the burner tube loosely circumscribes the swirler assembly at the resting temperature and firmly circumscribes the swirler assembly at an operating temperature. 4. 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; anda 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, andwherein at resting temperature, said burner tube is axially slidable towards and away from said support flange. 5. A fuel nozzle in accordance with claim 4, wherein said first coefficient of thermal expansion is higher than said second coefficient of thermal expansion. 6. A fuel nozzle in accordance with claim 4, wherein said burner tube is fabricated from the second material and a third material, wherein said third material is capable of withstanding a higher material temperature than said second material. 7. A fuel nozzle in accordance with claim 4, wherein said burner tube loosely circumscribes said swirler assembly at the resting temperature and firmly circumscribes said swirler assembly at an operating temperature. 8. A gas turbine engine comprising: a combustion chamber; anda 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; anda 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, andwherein at resting temperature, said burner tube is axially slidable towards and away from said support flange. 9. A gas turbine engine in accordance with claim 8, wherein said first coefficient of thermal expansion is higher than said second coefficient of thermal expansion. 10. A gas turbine engine in accordance with claim 8, wherein said burner tube is fabricated from the second material and a third material, and wherein said third material is capable of withstanding a higher material temperature than said second material. 11. A gas turbine engine in accordance with claim 8, wherein said burner tube loosely circumscribes said swirler assembly at a resting temperature and firmly circumscribes said swirler assembly at an operating temperature.
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