초록 ▼

A support assembly for a turbine system is disclosed. The support assembly includes a transition duct extending between a fuel nozzle and a turbine section. The transition duct has an inlet, an outlet, and a passage extending between the inlet and the outlet and defining a longitudinal axis, a radia

A support assembly for a turbine system is disclosed. The support assembly includes a transition duct extending between a fuel nozzle and a turbine section. The transition duct has an inlet, an outlet, and a passage extending between the inlet and the outlet and defining a longitudinal axis, a radial axis, and a tangential axis. The outlet of the transition duct is offset from the inlet along the longitudinal axis. The support assembly further includes an annular contact member extending from the transition duct. The contact member is configured to allow movement of the transition duct about at least one axis.

대표청구항 ▼

1. A support assembly for a turbine system, the support assembly comprising: a transition duct extending between a fuel nozzle and a turbine section, the transition duct having an inlet, an outlet, and a passage extending between the inlet and the outlet and defining a longitudinal axis, a radial ax

1. A support assembly for a turbine system, the support assembly comprising: a transition duct extending between a fuel nozzle and a turbine section, the transition duct having an inlet, an outlet, and a passage extending between the inlet and the outlet and defining a longitudinal axis, a radial axis, and a tangential axis, the outlet of the transition duct offset from the inlet along the longitudinal axis, the radial axis, and the tangential axis;an annular contact member extending from the transition duct, the contact member configured to allow movement of the transition duct about at least two axes, wherein the contact member extends from a head end of the transition duct; anda support structure contacting the contact member and configured to locate the transition duct within the turbine system, the support structure connected to a combustor casing generally surrounding, the transition duct. 2. The support assembly of claim 1, wherein the contact member is configured to allow movement of the transition duct about the tangential axis. 3. The support assembly of claim 1, wherein the contact member is configured to allow movement of the transition duct about the longitudinal axis. 4. The support assembly of claim 1, wherein the contact member has a generally curvilinear outer surface. 5. The support assembly of claim 1, wherein the contact member has a generally arcuate cross-sectional profile. 6. The support assembly of claim 5, wherein the generally arcuate cross-sectional profile extends along the longitudinal axis. 7. The support assembly of claim 1, wherein the support structure has a generally curvilinear inner surface. 8. The support assembly of claim 1, wherein the support structure has a thickness, and wherein the thickness increases along the longitudinal axis towards the outlet. 9. A turbine system, comprising: a fuel nozzle;a turbine section;a transition duct extending between a fuel nozzle and a turbine section, the transition duct having an inlet, an outlet, and a passage extending between the inlet and the outlet and defining a longitudinal axis, a radial axis, and a tangential axis, the outlet of the transition duct offset from the inlet along the longitudinal axis, the radial axis, and the tangential axis;an annular contact member extending from the transition duct, the contact member configured to allow movement of the transition duct about at least two axes, wherein the contact member extends from a head end of the transition duct; anda support structure contacting the contact member and configured to locate the transition duct within the turbine system, the support structure connected to a combustor easing generally surrounding the transition duct. 10. The turbine system of claim 9, wherein the contact member has a generally curvilinear outer surface. 11. The turbine system of claim 9, wherein the contact member has a generally arcuate cross-sectional profile. 12. The turbine system of claim 9, wherein the support structure has a generally curvilinear inner surface.