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US08689933B2 Helmholtz resonator for a gas turbine combustion chamber 失效
用于燃气轮机燃烧室的亥姆霍兹共振器

  • Patent Title: Helmholtz resonator for a gas turbine combustion chamber
  • Patent Title (中): 用于燃气轮机燃烧室的亥姆霍兹共振器
  • Application No.: US13497091
    Application Date: 2010-09-14
  • Publication No.: US08689933B2
    Publication Date: 2014-04-08
  • Inventor: Ghenadie Bulat
  • Applicant: Ghenadie Bulat
  • Applicant Address: DE München
  • Assignee: Siemens Aktiengesellschaft
  • Current Assignee: Siemens Aktiengesellschaft
  • Current Assignee Address: DE München
  • Priority: EP09012116 20090923
  • International Application: PCT/EP2010/063487 WO 20100914
  • International Announcement: WO2011/036073 WO 20110331
  • Main IPC: F01N1/12
  • IPC: F01N1/12 F02C7/24 F02K1/00 F02K1/82
Helmholtz resonator for a gas turbine combustion chamber
Abstract:
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.
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