Patent ID: 9470422
Filing Date: 2016-10-18
CPC Classification: F01D,F05D,F23R

Claim Text:
1. A gas turbine engine ducting arrangement, comprising: a ducting arrangement comprising a plurality of discrete ducts, each duct disposed between a respective combustor can and an annular chamber, the annular chamber configured to receive a combustion gas flow from each of the plurality of discrete ducts and to deliver the combustions gas flows to a turbine inlet annulus; an outer diameter mounting arrangement at a location radially outward of the annular chamber with respect to a central axis of the annular chamber configured to permit relative radial movement and to prevent relative axial movement between an outer wall of the annular chamber and a turbine vane carrier; and an inner diameter mounting arrangement comprising a bracket secured to the turbine vane carrier at a location radially outward of the annular chamber with respect to the central axis of the annular chamber, discrete from the outer diameter mounting arrangement, and in a way that permits relative radial movement and prevents relative axial movement between an inner wall of the annular chamber and the turbine vane carrier, wherein the bracket is configured as a cantilever support with radial freedom for the inner wall.