公开(公告)号：US20140033728A1

公开(公告)日：2014-02-06

申请号：US14048878

申请日：2013-10-08

Applicant: ALSTOM Technologies Ltd

Inventor： Robert MARMILIC ,  Jaan HELLAT ,  Ewald FREITAG ,  Adnan EROGLU

IPC: F02C3/00

CPC classification number: F02C3/00 ,  F02C7/141 ,  F02C7/228 ,  F05D2220/722 ,  F23R3/346 ,  F23R2900/03341 ,  Y02E20/16 ,  Y02E20/18 ,  Y02T50/671 ,  Y02T50/675

Abstract: The invention relates to a gas turbine assembly which substantially includes at least one compressor, at least one first burner, at least one second burner that is connected downstream of the first burner, and at least one turbine that is connected downstream of the second burner. At least the first and second burner form a component of a tubular or quasi-tubular combustion chamber element in the flow direction of the combustion path of the burners. The combustion chamber element being closed or quasi-closed and extending between the compressor and the turbine. The combustion chamber elements are arranged around the rotor of the gas turbine assembly in the shape of a ring.

Abstract translation: 本发明涉及一种燃气轮机组件，其基本上包括至少一个压缩机，至少一个第一燃烧器，连接在第一燃烧器下游的至少一个第二燃烧器和连接在第二燃烧器下游的至少一个涡轮机。 至少第一和第二燃烧器在燃烧器的燃烧路径的流动方向上形成管状或准管状燃烧室元件的部件。 燃烧室元件被关闭或准闭合并且在压缩机和涡轮机之间延伸。 燃烧室元件以环形的形式布置在燃气轮机组件的转子周围。