Patent ID: 9506653
Filing Date: 2016-11-29
CPC Classification: F23R

Claim Text:
1. A combustion chamber of a gas turbine, comprising: a combustion chamber head positioned at a front area of the combustion chamber with respect to a flow direction; an external combustion chamber wall; an internal combustion chamber wall including a frontal end area and a back end area with respect to the flow direction, a base plate arranged in an area of the combustion chamber head; a groove formed at the front area of the combustion chamber, the groove extending in an axial direction of the combustion chamber; wherein the frontal end area of the internal combustion chamber wall is supported and is longitudinally slidable inside the groove and the back end area of the internal combustion chamber wall is fixedly attached to the external combustion chamber wall; at least one chosen from radially arranged screws and axially arranged screws engaging the back end area of the internal combustion chamber wall and the external combustion chamber wall to fixedly attach the back end area of the internal combustion chamber wall to the external combustion chamber wall; a heat shield positioned downstream of the base plate and spaced apart from the base plate to create an air gap between the base plate and the heat shield, the heat shield having an outer periphery having a smaller external dimension than an internal dimension of the external combustion chamber wall, the outer periphery being spaced inwardly away from the external combustion chamber wall to form the groove therebetween, with the heat shield forming a radially inner surface of the groove and the external combustion chamber forming a radially outer surface of the groove; a support ring radially extending from the outer periphery, wherein the support ring is configured to directly support and guide in a longitudinal slidable manner the internal combustion chamber inside the groove.