Patent ID: 9366444
Filing Date: 2016-06-14
CPC Classification: F01D,F05D,F23R

Claim Text:
1. A transition seal assembly for a gas turbine engine, along which exhaust gas generated in a combustion chamber can flow toward a turbine of the gas turbine engine, the transition seal assembly comprising: first and second opposing ends with a U-shape body member at the a first end and a seal flange extending along a second end, the transition seal assembly positionable between a transition section downstream of the combustion chamber and an inlet flange attached to an inlet section of the turbine, wherein the inlet flange extends circumferentially about an axis of rotation of the turbine, the seal flange extending away from the first end and along an axial direction defined by the axis of rotation; and a flexible member affixed to the transition seal assembly and extending along the seal flange so that, when the transition seal assembly is positioned between the transition section and the inlet flange of the inlet section, the flexible member is positioned radially outward from the seal flange with the flexible member comprising a bend making contact with the inlet flange of the turbine inlet section, wherein the inlet flange has an inner surface and an outer surface opposite to the inner surface with the inner surface facing a flow path of the exhaust gas between the transition section and the inlet section and the outer surface faces away from the flow path, and wherein the flexible member is a spring seal including a first end attached to the transition seal assembly and a second end opposite to the first end, wherein the second end comprises the bend and wherein the bend comprises a bead configured to elastically press on the outer surface of the inlet flange such that sealing contact is maintained along a line of contact between the bead and the outer surface of the inlet flange.