Combustion device of a gas turbine including a plurality of passages and chambers defining helmholtz resonators
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F02C-007/24
F23R-003/00
출원번호
US-0871310
(2010-08-30)
등록번호
US-8839624
(2014-09-23)
우선권정보
EP-09169091 (2009-08-31)
발명자
/ 주소
Schnell, Alexander
Noiray, Nicolas
Reinert, Felix
Lauffer, Diane
Schuermans, Bruno
출원인 / 주소
Alstom Technology Ltd.
대리인 / 주소
Buchanan Ingersoll & Rooney PC
인용정보
피인용 횟수 :
4인용 특허 :
15
초록▼
A combustion device for a gas turbine that includes a portion having first and second walls that defines an inside of the combustion device, a zone between the first and second walls and an outside of the combustion device. A plurality of first passages connect the inside of the combustion device to
A combustion device for a gas turbine that includes a portion having first and second walls that defines an inside of the combustion device, a zone between the first and second walls and an outside of the combustion device. A plurality of first passages connect the inside of the combustion device to the zone between the first and second walls and a plurality of second passages connect the zone between the first and second walls to the outside of the combustion device. A plurality of chambers are defined within the zone between the first and second walls, each chamber being connected with one first passage and at least one second passage. Each chamber defining a Helmholtz damper.
대표청구항▼
1. A combustion device for a gas turbine comprising: a portion including first and second walls and defining an inside of the combustion device, a zone between the first and second walls and an outside of the combustion device;a plurality of first passages connecting the inside of the combustion dev
1. A combustion device for a gas turbine comprising: a portion including first and second walls and defining an inside of the combustion device, a zone between the first and second walls and an outside of the combustion device;a plurality of first passages connecting the inside of the combustion device to the zone between the first and second walls;a plurality of second passages connecting the zone between the first and second walls to the outside of the combustion device; anda plurality of chambers defined within the zone between the first and second walls, each chamber being connected with one first passage and at least one second passage, and each chamber defining a Helmholtz damper,wherein each of the plurality of chambers is connected to a single second passage. 2. A combustion device for a gas turbine comprising: a portion including first and second walls and defining an inside of the combustion device, a zone between the first and second walls and an outside of the combustion device; a plurality of first passages connecting the inside of the combustion device to the zone between the first and second walls;a plurality of second passages connecting the zone between the first and second walls to the outside of the combustion device;a plurality of chambers defined within the zone between the first and second walls, each chamber being connected with one first passage and at least one second passage, and each chamber defining a Helmholtz damper;a first plate interposed between the first and second walls, wherein the plurality of chambers are defined by at least the first plate; anda second plate defining at least a side of each chamber and at least one of the plurality of first passages and the plurality of second passages. 3. A combustion device for a gas turbine comprising: a portion including first and second walls and defining an inside of the combustion device, a zone between the first and second walls and an outside of the combustion device;a plurality of first passages connecting the inside of the combustion device to the zone between the first and second walls;a plurality of second passages connecting the zone between the first and second walls to the outside of the combustion device; anda plurality of chambers defined within the zone between the first and second walls, each chamber being connected with one first passage and at least one second passage, and each chamber defining a Helmholtz damper;a first plate interposed between the first and second walls, wherein the plurality of chambers are defined by at least the first plate;wherein each of the plurality of chambers is defined by a first hole indented in the first plate, andwherein the at least one second passage passes through the first wall to the second wall, which faces the combustion chamber, and extends parallel to the second wall for cooling the second wall before feeding into at least one of the plurality of chambers. 4. The combustion device recited in claim 3, further comprising a second plate, the second plate defining at least a side of each chamber and at least one of the plurality of first passages and the plurality of second passages, wherein each first hole is a through hole. 5. The combustion device recited in claim 4, further comprising a third plate coupled to the second plate, the third plate defining at least one of the plurality of first passages and the plurality of second passages. 6. The combustion device recited in claim 5, wherein each first hole is a through hole, and wherein each second passage is formed by a second through hole in the second plate and a through slot in the third plate. 7. The combustion device recited in claim 3, wherein each first hole is a blind hole. 8. The combustion device recited in claim 3, wherein the first plate defines a spacer grid forming the plurality of chambers. 9. The combustion device recited in claim 3, wherein each of the plurality of chambers is defined by a blind hole indented into one of the first and second walls. 10. The combustion device recited in claim 3, wherein the both of the respective first and second passages corresponding to each of the plurality of chambers open to the respective chamber on a same side of the chamber. 11. The combustion device recited in claim 3, wherein each of the plurality of chambers has the same dimensions. 12. The combustion device recited in claim 3, wherein the plurality of chambers have different dimensions. 13. The combustion device recited in claim 3, wherein each of the plurality of chambers is connected to a single second passage. 14. The combustion device recited in claim 3, wherein each of the plurality of second passages include a first section normal to the first wall, a second section parallel to the second wall, and a third section normal to the second wall, the second section being arranged between the first and third sections. 15. A reheat combustion device comprising: a mixing tube including nozzles; anda combustion chamber disposed downstream of the mixing tube and configured to be fed from the mixing tube;wherein at least a portion of the mixing tube and combustion chamber includes first and second walls defining an inside of the combustion device, a zone between the first and second walls, and an outside of the combustion device, the portion including:a plurality of first passages connecting the inside of the combustion device to the zone between the first and second walls;a plurality of second passages connecting the zone between the first and second walls to the outside of the combustion device;a plurality of chambers defined within the zone between the first and second walls, each chamber being connected with one first passage and at least one second passage, and each chamber defining a Helmholtz damper; anda first plate interposed between the first and second walls, wherein the plurality of chambers are defined by at least the first plate;wherein each of the plurality of chambers is defined by a first hole indented in the first plate, andwherein the at least one second passage passes through the first wall to the second wall, which faces the combustion chamber, and extends parallel to the second wall for cooling the second wall before feeding into at least one of the plurality of chambers. 16. The combustion device recited in claim 15, wherein each of the plurality of second passages include a first section normal to the first wall, a second section parallel to the second wall, and a third section normal to the second wall, the second section being arranged between the first and third sections. 17. The combustion device recited in claim 15, wherein each first hole is a through hole.
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이 특허에 인용된 특허 (15)
Holt, Alistaire S; MacQuisten, Michael A; Whiteman, Michael; Moran, Anthony J, Acoustic damper.
Bethke,Sven; Buchal,Tobias; Huth,Michael; Nimptsch,Harald; Prade,Bernd; Glessner,John Carl, Combustion chamber for a gas turbine with at least two resonator devices.
Gulati Anil (Cincinnati OH) Dean Anthony John (Scotia NY) Holmes David Graham (Schenectady NY) Voorhees Eayre Bruce (Sloansville NY), Dynamics free low emissions gas turbine combustor.
Aigner Manfred (Wettingen CHX) Urech Raphael (Hallwil CHX) Wetter Hugo (Buchs CHX), Gas turbine combustion chamber with scavenged Helmholtz resonators.
Huber, Andreas; Noiray, Nicolas; Schuermans, Bruno; Benz, Urs, Combustion device for a gas turbine configured to suppress thermo-acoustical pulsations.
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