초록 ▼

A combustor-turbine seal interface is provided for deployment within a gas turbine engine. In one embodiment, the combustor-turbine assembly a combustor, a turbine nozzle downstream of the combustor, and a first compliant dual seal assembly. The first compliant dual seal assembly includes a complian

A combustor-turbine seal interface is provided for deployment within a gas turbine engine. In one embodiment, the combustor-turbine assembly a combustor, a turbine nozzle downstream of the combustor, and a first compliant dual seal assembly. The first compliant dual seal assembly includes 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 compliant seal wall and the turbine nozzle. The first bearing seal is sealingly disposed in series with the first compression seal.

대표청구항 ▼

1. 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; anda first compliant dual seal assembly, comprising: a compliant seal wall sealingly coupled between the combustor an

1. 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; anda 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; anda 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. 2. A combustor-turbine seal interface according to claim 1 wherein the first compression seal is disposed upstream of the first bearing seal as taken along a combustor leakage path. 3. A combustor-turbine seal interface according to claim 1 wherein the combustor includes an outlet, and wherein the first bearing seal generally resides between the outlet and the first compression seal. 4. A combustor-turbine seal interface according to claim 1 wherein the first bearing seal resides closer to the longitudinal axis of the gas turbine engine than does the first compression seal. 5. A combustor-turbine seal interface according to claim 1 wherein the first bearing seal resides radially displaced from the first compression seal. 6. A combustor-turbine seal interface according to claim 1 further comprising a seal retainer coupled between the compliant seal wall and the turbine nozzle. 7. A combustor-turbine seal interface according to claim 6 wherein the seal retainer comprises a substantially annular body, the compression seal sealingly compressed between the substantially annular body and the turbine nozzle. 8. A combustor-turbine seal interface according to claim 7 wherein the gas turbine engine includes an engine casing, and wherein seal retainer further comprises a plurality of axially-elongated flanges fixedly coupled to the engine casing. 9. A combustor-turbine seal interface according to claim 8 wherein the seal retainer further comprises a plurality of flow passages formed therethrough, the plurality of flow passages interspersed with the plurality of axially-elongated flanges. 10. A combustor-turbine seal interface according to claim 6 wherein the compliant seal wall comprises: a second end portion fixedly coupled to the seal retainer. 11. A combustor-turbine seal interface according to claim 10 wherein the compliant seal wall further comprises an axially-overlapping portion intermediate the first end portion and the second end portion, the axially overlapping portion providing a radial compliance between the combustor and the seal retainer. 12. A combustor-turbine seal interface according to claim 11 wherein the combustor includes a liner wall, and wherein the axially-overlapping portion is radially offset from the liner wall to define an effusion cooling path extending toward the downstream end of the combustor. 13. A combustor-turbine seal interface according to claim 6 further comprising a nozzle wall coupled to the turbine nozzle, the first compression seal sealingly deformed between the seal retainer and the nozzle wall. 14. A combustor-turbine seal interface according to claim 6 further comprising a second compliant dual seal assembly, the second compliant dual seal assembly coupled between an inner portion of the combustor and the turbine nozzle, and the first compliant dual seal assembly coupled between an outer portion of the combustor and the turbine nozzle. 15. A combustor-turbine seal interface according to claim 14 wherein the second compliant dual seal assembly comprises: a first beam structure having a downstream end portion fixedly coupled to a downstream end portion of the combustor;a second beam structure having a downstream end portion abutting the turbine nozzle, the second beam structure axially overlapping with the first beam structure to provide a radial compliance between the combustor and the turbine nozzle; anda second compression seal sealingly compressed between an upstream end portion of the first beam structure and an upstream end portion of the second beam structure. 16. A combustor-turbine seal interface according to claim 15 wherein the downstream end portion of the first beam structure abuts the turbine nozzle to form a second bearing seal in series with the second compression seal. 17. 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; anda compliant dual seal assembly, comprising: a compliant seal wall having a first end portion and a second end portion, the first end portion fixedly coupled to a downstream end portion of the combustor and abutting the turbine nozzle to define a bearing seal allowing radial sliding movement between the turbine nozzle and the combustor, the compliant seal wall further having a generally conical intermediate portion between the first end portion and the second end portion and extending around the downstream end portion of the combustor;a seal retainer coupled between the turbine nozzle and the second end portion of the compliant seal wall; anda compression seal sealingly coupled between the seal retainer and the turbine nozzle, the compression seal disposed upstream of the bearing seal as taken along a combustor leakage path. 18. A combustor-turbine seal interface according to claim 17 wherein the compliant seal wall is sealingly coupled between a downstream portion of the turbine nozzle and the seal retainer so as to substantially prevent airflow from bypassing the compression seal and the compliant seal wall. 19. A combustor-turbine seal interface for deployment within a gas turbine engine including an engine casing, the combustor-turbine assembly comprising: a combustor;a turbine nozzle downstream of the combustor; anda compliant dual seal assembly, comprising: a seal retainer, comprising: a generally annular body disposed adjacent the turbine nozzle;a plurality of axially-elongated flanges extending from the generally annular body in an upstream direction, the plurality of axially-elongated flanges configured to be mounted to the engine casing and to provide a radial compliancy between the generally annular body and the engine casing; anda plurality of airflow channels formed through the seal retainer proximate the plurality of axially-elongated flanges;a compression seal sealingly compressed between the annular body and the turbine nozzle;a compliant seal wall sealingly coupled between a downstream end portion of the combustor and the seal retainer, the compliant seal wall having an end portion fixedly coupled to the downstream end portion of the combustor and further having a generally conical intermediate portion extending around the downstream end portion of the combustor; anda bearing seal generally defined by the interface between the compliant seal wall and an upstream end portion of the turbine nozzle, the bearing seal coupled in series with the compression seal and allowing sliding movement between the combustor and the turbine nozzle in a radial direction.