Patent ID: 8821114

Claim:
An axial flow gas turbine engine arranged about a central axis, comprising: a compressor section; a combustor section; a turbine section having a plurality flow path components forming a plurality of guide vane rings and ring segments arranged in axial succession to define a boundary of a hot gas duct that contains a hot gas flow from the combustor section; a vane carrier; and a sealing element including axially facing sides extending radially between a circumferentially extending groove in the vane carrier and a groove in the flow path components, the sealing element including inner and outer ends extending into respective grooves and the ends terminating at radially inner and outer edges, and each of the axially facing sides defining a chamfered portion extending to a respective one of the edges to accommodate axial movement of the sealing element about the edges within the grooves; and each end of the sealing element includes an axially facing parallel side and an opposing chamfered side defined by a respective chamfered portion, wherein: a) the chamfered portion of the inner end is formed by an upstream axially facing side oriented at an angle to a central longitudinal axis of the sealing element, the central longitudinal axis extending from the inner edge to the outer edge of the sealing element, and the parallel side of the inner end is formed by a downstream axially facing side oriented parallel to the central longitudinal axis; and b) the chamfered portion of the outer end is formed by a downstream axially facing side oriented at an angle to the central longitudinal axis of the sealing element, and the parallel side of the outer end is formed by an upstream axially facing side oriented parallel to the central longitudinal axis.