Helmholtz resonator for a gas turbine combustion chamber
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F01N-001/12
F02C-007/24
F02K-001/00
F02K-001/82
출원번호
US-0497091
(2010-09-14)
등록번호
US-8689933
(2014-04-08)
우선권정보
EP-09012116 (2009-09-23)
국제출원번호
PCT/EP2010/063487
(2010-09-14)
§371/§102 date
20120508
(20120508)
국제공개번호
WO2011/036073
(2011-03-31)
발명자
/ 주소
Bulat, Ghenadie
출원인 / 주소
Siemens Aktiengesellschaft
인용정보
피인용 횟수 :
0인용 특허 :
4
초록▼
A resonator is provided, having an adaptable resonator frequency for absorbing sound generated by a gas stream of a gas turbine. The resonator includes a neck section, a chamber and a deformable element being deformable under influence of a change of a gas turbine temperature of the gas stream. The
A resonator is provided, having an adaptable resonator frequency for absorbing sound generated by a gas stream of a gas turbine. The resonator includes a neck section, a chamber and a deformable element being deformable under influence of a change of a gas turbine temperature of the gas stream. The shape of the deformable element is predetermined with respect to a respective gas turbine temperature. The neck section and the chamber form a volume of the resonator. The neck section forms a passage coupling the volume with the gas turbine. The deformable element is thermally coupled to the gas turbine in such a way that the shape of the deformable element depends on the respective gas turbine temperature. The deformable element forms a spiral and is installed to the neck section in such a way that an effective diameter of the neck section depends on the gas turbine temperature.
대표청구항▼
1. A resonator with an adaptable resonator frequency for absorbing sound generated by a gas stream of a gas turbine, the resonator comprising: a neck section,a chamber, anda deformable element being deformable under influence of a change of a gas turbine temperature, wherein the deformable element i
1. A resonator with an adaptable resonator frequency for absorbing sound generated by a gas stream of a gas turbine, the resonator comprising: a neck section,a chamber, anda deformable element being deformable under influence of a change of a gas turbine temperature, wherein the deformable element is a bimetallic element and forms a spiral,wherein the shape of the deformable element is predetermined with respect to a respective gas turbine temperature,wherein the neck section and the chamber form a volume of the resonator,wherein the neck section forms a passage coupling the volume with the gas turbine,wherein the deformable element is thermally coupleable to the gas turbine in such a way that the shape of the deformable element depends on the respective gas turbine temperature,wherein the deformable element is installed in the neck section in such a way that an effective diameter of the neck section depends on the gas turbine temperature, andwherein a shape of the spiral depends on the respective gas turbine temperature for selectively adapting the effective diameter of the neck section. 2. The resonator of claim 1, wherein the deformable element is thermally coupled to a wall of the gas turbine in such a way that the shape of the deformable element depends on the respective wall temperature. 3. The resonator of claim 1, wherein the deformable element is thermally coupled to a gas stream of the gas turbine in such a way that the shape of the deformable element depends on the gas stream temperature. 4. The resonator of claim 1, wherein the deformable element is installed to the neck section in such a way that a length of the neck section depends on the respective gas turbine temperature. 5. The resonator of claim 1, wherein the deformable element is installed to the neck section in such a way, that a volume of the neck section depends on the respective gas turbine temperature. 6. The resonator of claim 1, further comprising a cooling hole, wherein the cooling hole is adapted for coupling the volume of the resonator to a cooling fluid stream. 7. The resonator of claim 1, further comprising a plurality of deformable elements. 8. A gas turbine generating a gas stream, comprising: at least one resonator according to claim 1. 9. A method of producing a resonator with an adaptable resonator frequency for absorbing sound generated by a gas stream of a gas turbine, the method comprising: forming a volume of the resonator by a neck section and a chamber,forming a passage by the neck section coupling the volume to the gas turbine,thermally coupling a deformable bimetallic element forming a spiral to the gas turbine in such a way that the shape of the deformable bimetallic element depends on the respective gas turbine temperature,wherein the deformable bimetallic element is installed to the neck section in such a way that an effective diameter of the neck section depends on the gas turbine temperature,wherein a shape of the spiral depends on the respective gas turbine temperature for selectively adapting the effective diameter of the neck section.
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이 특허에 인용된 특허 (4)
Suenaga, Kiyoshi; Mandai, Shigemi; Ono, Masaki; Tanaka, Katsunori, Gas turbine combustor, gas turbine, and jet engine.
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