Patent ID: 8596074
Filing Date: 2013-12-03
Classification: F23C,F23D,F23R

Abstract:
1. A gas turbine combustor, comprising: a combustion chamber having an axial direction and a radial direction that comprises a pre-chamber and a main chamber following the pre-chamber in the axial direction, the pre-chamber having a smaller diameter than the main chamber; a swirler comprising a plurality of vanes arranged in a circle with at least one air passage defined between a pair of adjacent vanes, wherein the air passage feeds an air stream into the pre-chamber, the air passage being configured to guide a flow between said adjacent vanes from a radially outer inlet to a radially inner outlet, and a fuel injection opening that is located in the air passage, wherein the vanes are configured such that the air passage is curved in the axial direction and the radial direction, the air passage being oriented so that a flowing direction of the air stream flowing into the pre-chamber comprises an angle with the radial direction to introduce a swirl in the air stream and an angle with the axial direction of at least 60°; and wherein the air passage is configured to define a turning flow path with a turning between 70° and 150° in the radial direction and a turning between 0° and 235° in the axial direction.