Fuel nozzle assembly for a gas turbine engine
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F23R-003/20
F02C-007/22
F23R-003/14
F23R-003/28
F23M-020/00
출원번호
US-0498494
(2009-07-07)
등록번호
US-9200571
(2015-12-01)
발명자
/ 주소
Bailey, Donald Mark
Simmons, Scott R.
Huffman, Marcus B.
출원인 / 주소
General Electric Company
대리인 / 주소
Armstrong Teasdale LLP
인용정보
피인용 횟수 :
9인용 특허 :
10
초록▼
A fuel nozzle assembly for a gas turbine engine includes a flange and a pre-mix tube. The flange includes a first end that is configured to couple to an end cover of the combustor, and a second end that is opposite said first end. The pre-mix tube is coupled at a first end to the flange second end.
A fuel nozzle assembly for a gas turbine engine includes a flange and a pre-mix tube. The flange includes a first end that is configured to couple to an end cover of the combustor, and a second end that is opposite said first end. The pre-mix tube is coupled at a first end to the flange second end. The flange and the pre-mix tube are fabricated to operate at a natural frequency that is different from an operating frequency of the gas turbine engine.
대표청구항▼
1. A fuel nozzle assembly for a gas turbine engine including a rotor and a combustor, said fuel nozzle assembly comprising: a flange that extends from a flange first end to a flange second end, said flange first end comprises a mounting portion configured to couple to an end cover of the combustor,
1. A fuel nozzle assembly for a gas turbine engine including a rotor and a combustor, said fuel nozzle assembly comprising: a flange that extends from a flange first end to a flange second end, said flange first end comprises a mounting portion configured to couple to an end cover of the combustor, said flange comprises an integrally formed substantially frusto-conical shaped body that extends between said mounting portion and said flange second end, wherein said flange defines a first pre-determined length between said flange first and second ends that facilitates raising a first frequency of said flange during operation above an operating frequency of the rotor, such that a multiple of the first frequency is different from a multiple of the operating frequency of the rotor; anda pre-mix tube that extends from a tube first end to a tube second end, said tube first end coupled to said flange at a first joint proximate said flange second end, said pre-mix tube defines a second pre-determined length between said tube first and second ends that facilitates raising a second frequency of said pre-mix tube during operation above the operating frequency of the rotor, such that a multiple of the second frequency is different from a multiple of the operating frequency of the rotor, wherein said tube second end is inwardly tapered. 2. A fuel nozzle assembly in accordance with claim 1, wherein said first joint comprises an electron beam weld. 3. A fuel nozzle assembly in accordance with claim 1, wherein said substantially frusto-conical shaped body includes an angle of convergence to facilitate controlling a natural frequency of said flange. 4. A fuel nozzle assembly in accordance with claim 1, wherein said flange and said pre-mix tube are fabricated to operate between a whole number frequency of the operating frequency of the rotor. 5. A fuel nozzle assembly in accordance with claim 4, wherein said flange is fabricated to operate at a natural frequency of about 175 Hz to about 180 Hz. 6. A fuel nozzle assembly in accordance with claim 1, further comprising an end cap assembly coupled to said tube second end. 7. A fuel nozzle assembly in accordance with claim 6, wherein said end cap assembly is coupled to said tube second end via an electron beam weld. 8. A fuel nozzle assembly in accordance with claim 6, further comprising: a swirler assembly coupled to said tube second end via an electron beam weld; anda tip tube coupled to said swirler assembly via an electron beam weld. 9. A fuel nozzle assembly in accordance with claim 8, further comprising a tip assembly coupled to a downstream end of said tip tube via an electron beam weld. 10. A gas turbine engine comprising: a rotor;a combustor comprising an end cover surface; anda fuel nozzle assembly comprising:a flange that extends from a flange first end to a flange second end, said flange first end comprises a mounting portion configured to couple to said end cover surface, said flange comprises an integrally formed substantially frusto-conically shaped body that extends between said mounting portion and said flange second end, wherein said flange defines a first pre-determined length between said flange first and second ends that facilitates raising a first frequency of said flange during operation above an operating frequency of said rotor, such that a multiple of the first frequency is different from a multiple of the operating frequency of said rotor; anda pre-mix tube that extends from a tube first end to a tube second end, said tube first end coupled to said flange at a first joint proximate said flange second end, said pre-mix tube defines a second pre-determined length between said tube first and second ends that facilitates raising a second frequency of said pre-mix tube during operation above the operating frequency of said rotor, such that a multiple of the second frequency is different from a multiple of the operating frequency of said rotor, and wherein said pre-mix tube second end is inwardly tapered. 11. A gas turbine engine in accordance with claim 10, wherein said first joint comprises an electron beam weld. 12. A gas turbine engine in accordance with claim 10, wherein said substantially frusto-conical shaped body includes an angle of convergence to facilitate controlling a natural frequency of said flange. 13. A gas turbine engine in accordance with claim 10, wherein said flange and said pre-mix tube are fabricated to operate between a whole number frequency of the operating frequency of said rotor. 14. A gas turbine engine in accordance with claim 13, wherein said flange is fabricated to operate at a natural frequency of about 175 Hz to about 180 Hz. 15. A gas turbine engine in accordance with claim 10, further comprising an end cap assembly coupled to said tube second end. 16. A gas turbine engine in accordance with claim 15, wherein said end cap assembly is coupled to said tube second end via an electron beam weld. 17. A gas turbine engine in accordance with claim 15, further comprising: a swirler assembly coupled to said tube second end via an electron beam weld; anda tip tube coupled to said swirler assembly via an electron beam weld. 18. A gas turbine engine in accordance with claim 17, further comprising a tip assembly coupled to a downstream end of said tip tube via an electron beam weld.
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