Patent ID: 8534076

Claim:
A combustor-turbine seal interface for deployment within a gas turbine engine, the combustor-turbine assembly comprising: a combustor; a turbine nozzle downstream of the combustor; and a first compliant dual seal assembly, comprising: a compliant seal wall sealingly coupled between the combustor and the turbine nozzle; a first compression seal sealingly disposed between the compliant seal wall and the turbine nozzle; and a first bearing seal generally defined by the interface between the turbine nozzle and a first end portion of the compliant seal wall abutting the turbine nozzle, the first end portion of the compliant seal wall fixedly coupled to the downstream end of the combustor, the first bearing seal fluidly coupled in series with the first compression seal and allowing sliding movement between the combustor and the turbine nozzle in a radial direction.