Dual fuel nozzle tip assembly with impingement cooled nozzle tip
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F23R-003/28
F23R-003/14
F23R-003/36
출원번호
US-0077557
(2013-11-12)
등록번호
US-9383107
(2016-07-05)
우선권정보
RU-2013102451 (2013-01-10)
발명자
/ 주소
Shershnyov, Borys Borysovych
Ginessin, Leonid Yulyevich
출원인 / 주소
GENERAL ELECTRIC COMPANY
대리인 / 주소
Dority & Manning, PA
인용정보
피인용 횟수 :
0인용 특허 :
11
초록▼
A fuel nozzle for a combustor includes a burner tube and a center nozzle assembly disposed within the burner tube. The center nozzle assembly includes a center body that at least partially defines a cooling air flow passage through the center nozzle assembly. A premix flow passage is defined between
A fuel nozzle for a combustor includes a burner tube and a center nozzle assembly disposed within the burner tube. The center nozzle assembly includes a center body that at least partially defines a cooling air flow passage through the center nozzle assembly. A premix flow passage is defined between the burner tube and the center nozzle assembly. A tip assembly is disposed at a downstream end of the center body. The tip assembly includes an impingement plate, and a cap that is disposed downstream from the impingement plate. The impingement plate and the cap at least partially define a cooling plenum therebetween. An insert passage extends through the impingement plate and a cooling flow outlet extends through the cap. A plurality of cooling ports extends through the impingement plate to provide for fluid communication between the cooling air flow passage and the cooling plenum.
대표청구항▼
1. A fuel nozzle for a combustor, the fuel nozzle comprising: a burner tube component;a center nozzle assembly concentrically disposed within the burner tube component, the center nozzle assembly having center body that at least partially defines a cooling air flow passage through the center nozzle
1. A fuel nozzle for a combustor, the fuel nozzle comprising: a burner tube component;a center nozzle assembly concentrically disposed within the burner tube component, the center nozzle assembly having center body that at least partially defines a cooling air flow passage through the center nozzle assembly, the center body having a downstream end;a premix flow passage defined between the burner tube component and the center nozzle assembly;a tip assembly disposed at the downstream end of the center body, the tip assembly having an impingement plate that extends radially across the downstream end of the center body, and a radially extending cap disposed downstream from the impingement plate, the impingement plate and the cap at least partially defining a cooling plenum therebetween;an insert passage that extends through the impingement plate;a cooling flow outlet that extends through the cap, the cooling flow outlet being coaxially aligned with the insert passage;a plurality of cooling ports that extend through the impingement plate to provide for fluid communication between the cooling air flow passage and the cooling plenum; an annular heat shield concentrically disposed within the insert passage; andone of a liquid fuel cartridge or a purge air bypass cartridge concentrically disposed within the insert passage of the impingement plate and that extends through the heat shield. 2. The fuel nozzle as in claim 1, wherein the plurality of cooling ports are angled with respect to a longitudinal axis of the impingement plate within a plane defined between the longitudinal axis and a tangential axis of the impingement plate to impart swirl about the longitudinal axis to a compressed working fluid that passes therethrough. 3. The fuel nozzle as in claim 2, further comprising a plurality of swirler vanes that extend between the burner tube component and the center nozzle assembly within the premix flow passage, the swirler vanes being configured to impart swirl about a longitudinal axis of the fuel nozzle to a compressed working fluid that passes therethrough. 4. The fuel nozzle as in claim 3, wherein the plurality of cooling ports are angled to impart swirl that is opposite to the swirl imparted by the swirler vanes. 5. The fuel nozzle as in claim 1, wherein the cap includes a cool side and a hot side, the cooling flow outlet converging radially inward from the cool side towards the hot side of the cap. 6. The fuel nozzle as in claim 1, wherein the fuel nozzle includes the liquid fuel cartridge and the liquid fuel cartridge includes a fuel injection tip portion that extends through the heat shield and at least partially through the cooling flow passage of the cap. 7. The fuel nozzle as in claim 6, further comprising a cartridge tip cooling plenum that is at least partially defined between the heat shield and the fuel injection tip portion of the liquid fuel cartridge. 8. The fuel nozzle as in claim 1, wherein the fuel nozzle includes the purge air bypass cartridge, the purge air bypass cartridge including a plurality of cooling air holes that are in fluid communication with the cooling plenum. 9. A tip assembly for a fuel nozzle, comprising: an annular impingement plate, the impingement plate at least partially defining an insert passage that extends concentrically through the impingement plate along a longitudinal axis of the tip assembly;an annular cap disposed coaxially downstream from the impingement plate, the cap at least partially defining a cooling flow outlet, the cooling flow outlet being aligned with the insert passage, the cap having an outer portion that extends between the impingement plate and the cap, the outer portion, the cap and the impingement plate at least partially defining a cooling plenum therebetween; anda plurality of angled cooling ports extending through the impingement plate to provide fluid communication into the cooling plenum, the plurality of cooling ports being set at an angle with respect to the longitudinal axis of the impingement plate within a plane defined between the longitudinal axis and a tangential axis of the impingement plate; and one of a liquid fuel cartridge or a purge air bypass cartridge concentrically disposed within the insert passage of the impingement plate and that extends axially through the cap. 10. The tip assembly as in claim 9, wherein the cap includes a cool side and a hot side, the cooling flow outlet converging radially inward from the cool side towards the hot side of the cap. 11. The tip assembly as in claim 9, wherein the tip assembly includes the liquid fuel cartridge, the tip assembly further comprising an annular heat shield concentrically disposed within the insert passage, wherein the liquid fuel cartridge extends coaxially through the heat shield. 12. The tip assembly as in claim 11, wherein the heat shield extends through the cap. 13. The tip assembly as in claim 11, wherein the liquid fuel cartridge includes a fuel injection tip portion that extends within the heat shield and at least partially through the cooling flow passage of the cap. 14. The tip assembly as in claim 13, further comprising a cartridge tip cooling plenum that is at least partially defined between the heat shield and the fuel injection tip portion of the liquid fuel cartridge. 15. A gas turbine comprising: a compressor at an upstream end of the gas turbine, a combustor positioned downstream from the compressor, and a turbine positioned downstream from the combustor, the combustor being in fluid communication with a fuel supply and a compressed air supply, the combustor having an end cover coupled to a casing, the casing at least partially surrounds the combustor, a fuel nozzle extends downstream from the end cover, the fuel nozzle comprising: a burner tube component;a center nozzle assembly concentrically disposed within the burner tube component, the center nozzle assembly having an annular center body that at least partially defines a cooling air flow passage through the center nozzle assembly, the center body having a downstream end;a premix flow passage defined between the burner tube component and the center body assembly;a tip assembly disposed at the downstream end of the center body, the tip assembly having an impingement plate that extends radially across the downstream end of the center body and a radially extending cap disposed coaxially downstream from the impingement plate, the impingement plate and the cap at least partially defining a cooling plenum therebetween, the impingement plate at least partially defining an insert passage and the cap at least partially defining a cooling flow outlet that is aligned with the insert passage;a plurality of angled cooling ports that extend through the impingement plate to provide for fluid communication between the cooling air flow passage and the cooling plenum; and one of a liquid fuel cartridge or a purge air bypass cartridge concentrically disposed within the insert passage of the impingement plate and that extends axially through the cap. 16. The gas turbine as in claim 15, wherein the plurality of cooling ports of the impingement plate are arranged in an annular array around the insert passage. 17. The gas turbine as in claim 15, wherein the plurality of cooling ports of the impingement plate are angled with respect to a longitudinal axis of the impingement plate within a plane defined between the longitudinal axis and a tangential axis of the impingement plate to impart swirl about the longitudinal axis to a cooling medium that passes therethrough. 18. The gas turbine as in claim 15, wherein the tip assembly further comprises an annular heat shield concentrically disposed within the insert passage and the liquid fuel cartridge, wherein the liquid fuel cartridge that extends through the heat shield, the heat shield and the liquid fuel cartridge at least partially defining a cartridge tip cooling plenum therebetween.
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이 특허에 인용된 특허 (11)
Bechtel ; II William Theodore ; Black Stephen Hugh ; Dean Anthony John ; Luts Andrew, Anti-coking dual-fuel nozzle for a gas turbine combustor.
Loprinzo Anthony J. ; Maughan James R. ; Morton H. Lindsay ; Black Stephen Hugh ; Dean Anthony John ; Bechtel ; II William Theodore ; Luts Andrew, Dual-fuel nozzle for inhibiting carbon deposition onto combustor surfaces in a gas turbine.
Richard Sterling Tuthill ; William Theodore Bechtel, II ; Jeffrey Arthur Benoit ; Stephen Hugh Black ; Robert James Bland ; Guy Wayne DeLeonardo ; Stefan Martin Meyer ; Joseph Charles Taura ;, Swozzle based burner tube premixer including inlet air conditioner for low emissions combustion.
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