IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0174187
(2008-07-16)
|
등록번호 |
US-8516819
(2013-08-27)
|
발명자
/ 주소 |
- Gambacorta, Domenico
- Johnson, Clifford E.
|
출원인 / 주소 |
|
인용정보 |
피인용 횟수 :
0 인용 특허 :
9 |
초록
▼
A gas turbine combustor having a Helmholtz resonator in a post-swirler homogenization zone upstream of the combustor zone. Embodiments of the present invention provide Helmholtz resonators that include cavities that occupy a remainder of a post-swirler homogenization zone, which also includes at lea
A gas turbine combustor having a Helmholtz resonator in a post-swirler homogenization zone upstream of the combustor zone. Embodiments of the present invention provide Helmholtz resonators that include cavities that occupy a remainder of a post-swirler homogenization zone, which also includes at least one flow-directing structure that passes a fuel/oxidizer mixture from a main swirler assembly into a combustion zone of a combustor. Thus, an open annular region of the combustor is converted into a multi-purpose zone that includes at least one Helmholtz resonator.
대표청구항
▼
1. A gas turbine combustor Helmholtz resonator comprising: a cavity at least partly between a combustor base plate transverse wall and a transverse wall of a top plate structure, wherein the top plate structure additionally comprises an outer shell wall adapted to contact a liner of the combustor, w
1. A gas turbine combustor Helmholtz resonator comprising: a cavity at least partly between a combustor base plate transverse wall and a transverse wall of a top plate structure, wherein the top plate structure additionally comprises an outer shell wall adapted to contact a liner of the combustor, wherein the outer shell wall is oriented transverse to the top plate transverse wall and wherein the outer shell wall extends to the base plate transverse wall to enclose the cavity;a plurality of base plate transverse wall openings through the base plate transverse wall and into the cavity;at least two top plate transverse wall apertures through the top plate transverse wall and defining a resonator throat, having a length, and communicating with a combustion zone downstream of the top plate structure transverse wall; anda flow-directing structure between a main swirler assembly and the top plate structure transverse wall that separates a flow path from the cavity,wherein the top plate structure additionally comprises an inward conical member adapted to conform to a pilot cone of the combustor, and wherein the cavity is also partly between the inward conical member and the base plate transverse wall. 2. The gas turbine combustor Helmholtz resonator of claim 1, wherein the inward conical member comprises a plurality of cooling apertures effective to provide a cooling flow to the pilot cone. 3. The gas turbine combustor Helmholtz resonator of claim 1, additionally comprising a tube extending from at least one of the top plate transverse wall apertures into the cavity to extend the resonator throat length. 4. A gas turbine combustor comprising the Helmholtz resonator of claim 1, the cavity defined by at least two partitions that are effective to define the cavity and a second cavity, the combustor additionally comprising a second Helmholtz resonator comprising the second cavity and at least one aperture defining a second resonator throat, having a length, and communicating with the combustion zone downstream of the top plate structure transverse wall. 5. A gas turbine combustor comprising: a combustor liner defining an interior combustion chamber having a flow-based longitudinal axis,a pilot burner disposed upstream of the combustion chamber along the longitudinal axis, a plurality of main swirler assemblies disposed radially outward of the pilot burner, a base plate comprising openings for the main swirler assemblies and the pilot burner, and a pilot cone having a volume and extending downstream for a distance from the base plate, the pilot cone comprising a pilot cone downstream edge, wherein a post-swirler homogenization zone is defined within the combustor liner between the base plate and a plane including the pilot cone downstream end, and excluding the pilot cone volume;a top plate comprising a transverse wall parallel to the base plate and extending between the combustor liner and the pilot cone, thereby including at least a portion of the post-swirler homogenization zone, the top plate transverse wall comprising a plurality of top plate transverse wall apertures there through;an outer shell wall adapted to contact a liner of the combustor and the top plate, wherein the outer shell wall is oriented transverse to the top plate and the outer shell wall extends to the base plate to enclose a cavity between the top plate and the base plate; andfor each of the main swirler assemblies, a flow-directing structure extending from a downstream end of the respective main swirler assembly to a passageway in the top plate transverse wall, effective to constrain a fuel/oxidizer mixture exiting the main swirler assembly to a path defined at least in part by the flow-directing structure;wherein a Helmholtz resonator comprises the cavity comprising at least a portion of a remainder of the post-swirler homogenization zone not included in said paths, wherein the top plate transverse wall apertures provide fluid communication between the cavity and the combustion chamber, and wherein a flow directing structure aperture provides fluid communication between the cavity and the path,wherein the to plate additionally comprises an inward conical member adapted to conform to the pilot cone of the combustor, and wherein the cavity is also partly between the inward conical member and the base plate. 6. The gas turbine combustor of claim 5, wherein the top plate is aligned along the plane that includes the pilot cone downstream end. 7. The gas turbine combustor of claim 5, wherein at least one partition is provided in the remainder to divide the reminder into at least two Helmholtz resonators. 8. The gas turbine combustor of claim 5, wherein base plate apertures in the base plate communicate with and supply air to the Helmholtz resonator cavity. 9. The gas turbine combustor of claim 5, additionally comprising a tube extending into the cavity from at least one of the top plate transverse wall apertures communicating with said cavity. 10. A gas turbine combustor comprising, within a combustor liner, a plurality of main swirler assemblies disposed radially outward of a pilot burner, a base plate comprising openings for the main swirler assemblies and the pilot burner, and a pilot cone having a volume and extending downstream for a distance from the base plate and ending at a pilot cone downstream edge, and a combustion zone downstream of the pilot cone and within the combustor liner, wherein the improvement comprises: a top plate structure spaced downstream from the base plate and comprising a top plate transverse wall comprising a plurality of top plate transverse wall apertures there through, wherein the top plate structure additionally comprises an outer shell wall adapted to contact the liner of the combustor, wherein the outer shell wall is oriented transverse to the top plate transverse wall and extends to the base plate to enclose a cavity between the top plate transverse wall and the base plate; andat least one flow-directing structure extending from one of the main swirler assemblies to a passageway in the top plate structure transverse wall, the flow directing structure comprising a flow directing structure wall comprising a flow directing structure aperture there through,wherein a Helmholtz resonator comprises a cavity at least partly between the base plate and the transverse wall of the top plate structure and excluding a path defined by the at least one flow-directing structure, the Helmholtz resonator further comprising a throat defined at least in part by the plurality of top plate transverse wall apertures and communicating between the cavity and the combustion zone, and wherein the flow directing structure aperture provides fluid communication between the cavity and a flow path defined by the flow directing structure,wherein the top plate structure additionally comprises an inward conical member adapted to conform to the pilot cone of the combustor, and wherein the cavity is also partly between the inward conical member and the base plate.
※ AI-Helper는 부적절한 답변을 할 수 있습니다.