Patent ID: 8402769

Claim:
A section of a gas turbine engine, the casing surrounding a combustor and comprising: a casing, surrounding the combustor and comprising: a radial spoke, the radial spoke includes an aerodynamic shape and comprises: an upstream leading side, a downstream trailing side, a first side, a second side opposite to the first side, and a flow guiding element arranged on at least the first side, wherein the radial spoke is used as a support for a carrier ring of a turbine guide vane ring, whereby cooling air exiting a compressor diffuser flows between the spoke and a transition duct of the combustor, wherein the first side and the second side extend from the upstream leading side to the downstream trailing side, and wherein the flow guiding element is formed is such a way that a flow of cooling air exiting the compressor diffuser is deflected and turned circumferentially about the axis of the gas turbine engine, and wherein at least a portion of the downstream trailing side comprises a concave surface in the form of a chute that extends in the circumferential direction about the axis of the gas turbine engine.