System and method for supplying a working fluid to a combustor via a non-uniform distribution manifold
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F23R-003/06
F23R-003/00
F23R-003/28
F23R-003/34
출원번호
US-0349906
(2012-01-13)
등록번호
US-9188337
(2015-11-17)
발명자
/ 주소
Stoia, Lucas John
Melton, Patrick Benedict
출원인 / 주소
GENERAL ELECTRIC COMPANY
대리인 / 주소
Dority & Manning, PA
인용정보
피인용 횟수 :
0인용 특허 :
33
초록▼
A system for supplying a working fluid to a combustor includes a fuel nozzle and a combustion chamber downstream from the fuel nozzle. A flow sleeve circumferentially surrounds the combustion chamber, and fuel injectors provide fluid communication to the combustion chamber. A distribution manifold c
A system for supplying a working fluid to a combustor includes a fuel nozzle and a combustion chamber downstream from the fuel nozzle. A flow sleeve circumferentially surrounds the combustion chamber, and fuel injectors provide fluid communication to the combustion chamber. A distribution manifold circumferentially surrounds the fuel injectors and defines an annular plenum. A fluid passage through the distribution manifold provides fluid communication through the distribution manifold. A radial cross-sectional area of the annular plenum varies around the flow sleeve. A method for supplying a working fluid to a combustor includes flowing a working fluid through a combustion chamber, diverting a portion of the working fluid through a distribution manifold that circumferentially surrounds fuel injectors circumferentially arranged around the combustion chamber, and changing at least one of a pressure or flow rate of the diverted portion of the working fluid.
대표청구항▼
1. A system for providing compressed air to fuel injectors within a combustor, the system comprising: an annular liner defining a combustion chamber within a casing of the combustor;a flow sleeve assembly having an inner sleeve radially spaced from and circumferentially surrounding the liner, an out
1. A system for providing compressed air to fuel injectors within a combustor, the system comprising: an annular liner defining a combustion chamber within a casing of the combustor;a flow sleeve assembly having an inner sleeve radially spaced from and circumferentially surrounding the liner, an outer sleeve radially spaced from and circumferentially surrounding the inner sleeve, the inner sleeve being fixedly connected to the outer sleeve and forming a void therebetween, wherein the liner and the inner sleeve define an annular flow passage therebetween, the flow sleeve assembly further comprising a plurality of fuel injectors circumferentially spaced around and extending radially through the outer sleeve, the inner sleeve, the annular flow passage and the liner, each fuel injector having an inlet defined along an outer surface of the outer sleeve;an upstream end of the flow sleeve assembly directly connected to the casing of the combustor, the outer sleeve, the inner sleeve, and the void therebetween all extending from the upstream end to the plurality of fuel injectors located downstream from the upstream end;a distribution manifold that extends continuously circumferentially around the outer sleeve, the distribution manifold having a forward wall axially spaced from an aft wall and an outer wall that extends axially between the forward wall and the aft wall, the outer wall substantially parallel with and radially spaced from the outer surface of the outer sleeve, the forward and aft walls being fixedly connected directly to the outer surface of the outer sleeve, wherein the forward wall, the aft wall and the outer wall define an annular flow passage within the distribution manifold and wherein the inlet of each fuel injector is disposed within the annular flow passage; anda plurality of openings circumferentially spaced along the outer wall of the distribution manifold, wherein each opening defines a fluid passage into the annular flow passage,wherein a first portion of an inner surface of the outer wall is radially spaced from the outer surface of the outer sleeve at a first radial height at a first circumferential location along the outer sleeve and a second portion of the inner surface of the outer wall is radially spaced from the outer surface at a second radial height at a second circumferential location along the outer sleeve, the second radial height is greater than the first radial height. 2. The system as in claim 1, wherein each opening is circumferentially offset from a corresponding inlet of a corresponding fuel injector of the plurality of fuel injectors. 3. The system as in claim 1, wherein the forward wall is axially spaced from the aft wall at a first axial distance at a first circumferential location along the outer surface of the outer liner and the forward wall is axially spaced from the aft wall at a second axial distance at a second circumferential location along the outer surface of the outer liner. 4. The system as in claim 3, wherein at least one opening of the plurality of openings is axially offset from a corresponding inlet of a corresponding fuel injector of the plurality of fuel injectors. 5. The system as in claim 1, further comprising a transition duct that extends axially downstream from an aft end of the liner, wherein the liner and the transition duct define a hot gas path through the combustor. 6. A system for providing compressed air to fuel injectors within a combustor, the system comprising: an annular liner defining a combustion chamber within a casing of the combustor;a flow sleeve assembly having an inner sleeve radially spaced from and circumferentially surrounding the liner, an outer sleeve radially spaced from and circumferentially surrounding the inner sleeve, the inner sleeve being fixedly connected to the outer sleeve and forming a void therebetween, wherein the liner and the inner sleeve define an annular flow passage therebetween, the flow sleeve assembly further comprising a plurality of fuel injectors circumferentially spaced around and extending radially through the outer sleeve, the inner sleeve, the annular flow passage and the liner, each fuel injector having an inlet defined along an outer surface of the outer sleeve;an upstream end of the flow sleeve assembly directly connected to the casing of the combustor, the outer sleeve, the inner sleeve, and the void therebetween all extending from the upstream end to the plurality of fuel injectors located downstream from the upstream end;a distribution manifold that extends continuously circumferentially around the outer sleeve, the distribution manifold having a forward wall axially spaced from an aft wall and an outer wall that extends axially between the forward wall and the aft wall, the outer wall substantially parallel with and radially spaced from the outer surface of the outer sleeve, the forward and aft walls being fixedly connected directly to the outer surface of the outer sleeve, wherein the forward wall, the aft wall and the outer wall define an annular flow passage within the distribution manifold and wherein the inlet of each fuel injector is disposed within the annular flow passage; anda plurality of openings circumferentially spaced along the outer wall of the distribution manifold, wherein each opening defines a fluid passage into the annular flow passage,wherein the forward wall is axially spaced from the aft wall at a first axial distance at a first circumferential location along the outer surface of the outer sleeve and the forward wall is axially spaced from the aft wall at a second axial distance at a second circumferential location along the outer surface of the outer sleeve, the second axial distance is greater than the first axial distance. 7. The system as in claim 6, wherein at least one opening of the plurality of openings is axially offset from a corresponding inlet of a corresponding fuel injector of the plurality of fuel injectors. 8. The system as in claim 6, wherein a first portion of an inner surface of the outer wall is radially spaced from the outer surface of the outer sleeve at a first radial height at a first circumferential location along the outer sleeve and a second portion of the inner surface of the outer wall is radially spaced from the outer surface at a second radial height at a second circumferential location along the outer sleeve. 9. The system as in claim 8, wherein each opening of the plurality of openings is circumferentially offset from a corresponding inlet of a corresponding fuel injector of the plurality of fuel injectors. 10. The system as in claim 6, further comprising a transition duct that extends axially downstream from an aft end of the liner, wherein the liner and the transition duct define a hot gas path through the combustor.
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