Transition duct with divided upstream and downstream portions
Turbine systems are provided. In one embodiment, a turbine system includes a transition duct comprising an inlet, an outlet, and a duct 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 and the tangential axis. The duct passage includes an upstream portion extending from the inlet and a downstream portion extending from the outlet. The turbine system further includes a rib extending from an outer surface of the duct passage, the rib dividing the upstream portion and the downstream portion.
1. A turbine system, comprising:
a transition duct comprising an inlet, an outlet, and a duct 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 and the tangential axis, the duct passage comprising an upstream portion extending from the inlet and a downstream portion extending from the outlet; and
a rib extending from an outer surface of the duct passage and around an entire periphery of the outer surface, the rib dividing the upstream portion and the downstream portion and partially defining and fluidly dividing an upstream cavity and a downstream cavity, the upstream cavity configured to direct a first portion of a working fluid towards the inlet, the downstream cavity configured to direct a second portion of the working fluid towards the outlet.
2. The turbine system of claim 1 , further comprising a flow sleeve generally surrounding the transition duct, the flow sleeve comprising an upstream outlet, a downstream outlet, and a sleeve passage extending between the upstream outlet and the downstream outlet, the sleeve passage comprising an upstream portion extending from the upstream outlet and a downstream portion extending from the downstream outlet, and wherein the rib further divides the upstream portion of the flow sleeve and the downstream portion of the flow sleeve.
3. The turbine system of claim 2 , wherein the upstream portions of the transition duct and the flow sleeve define the upstream cavity therebetween, wherein the downstream portions of the transition duct and the flow sleeve define the downstream cavity therebetween, and wherein the rib generally fluidly isolates the upstream cavity and the downstream cavity from each other.
4. The turbine system of claim 2 , wherein the flow sleeve is an impingement sleeve.
5. The turbine system of claim 1 , wherein the rib is integral with the passage.
6. The turbine system of claim 1 , wherein a plurality of film cooling holes are defined in the downstream portion of the duct passage.
7. The turbine system of claim 1 , wherein the outlet of the transition duct is further offset from the inlet along the radial axis.
8. The turbine system of claim 1 , wherein the downstream portion further comprises a plurality of internal pins.
9. The turbine system of claim 1 , further comprising a turbine section in communication with the transition duct, the turbine section comprising a first stage bucket assembly.
10. The turbine system of claim 9 , wherein no nozzles are disposed upstream of the first stage bucket assembly.
11. A turbine system, comprising:
a transition duct comprising an inlet, an outlet, and a duct 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 and the tangential axis;
a flow sleeve generally surrounding the transition duct, the flow sleeve comprising an upstream outlet, a downstream outlet, and a sleeve passage extending between the upstream outlet and the downstream outlet;
a cavity defined between the transition duct and the flow sleeve, the cavity comprising an upstream cavity and a downstream cavity; and
a rib positioned between the transition duct and the flow sleeve, the rib extending around an entire periphery of the duct passage and fluidly dividing the upstream cavity and the downstream cavity, wherein the upstream cavity is configured to direct a first portion of a working fluid towards the upstream outlet, and wherein the downstream cavity is configured to direct a second portion of the working fluid towards the downstream outlet.
12. The turbine system of claim 11 , wherein the rib generally fluidly isolates the upstream cavity and the downstream cavity from each other.
13. The turbine system of claim 11 , wherein the rib extends from an outer surface of the duct passage.
14. The turbine system of claim 11 , wherein the flow sleeve is an impingement sleeve.
15. The turbine system of claim 11 , wherein a plurality of film cooling holes are defined in the downstream portion of the duct passage.
16. The turbine system of claim 11 , wherein the outlet of the transition duct is further offset from the inlet along the radial axis.
17. The turbine system of claim 11 , further comprising a turbine section in communication with the transition duct, the turbine section comprising a first stage bucket assembly.
18. The turbine system of claim 17 , wherein no nozzles are disposed upstream of the first stage bucket assembly.
19. A turbomachine, comprising:
an inlet section;
an exhaust section;
a compressor section;
a combustor section, the combustor section comprising:
a transition duct comprising an inlet, an outlet, and a duct 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 and the tangential axis;
a flow sleeve generally surrounding the transition duct, the flow sleeve comprising an upstream outlet, a downstream outlet, and a sleeve passage extending between the upstream outlet and the downstream outlet;
a cavity defined between the transition duct and the flow sleeve, the cavity comprising an upstream cavity and a downstream cavity; and
a rib positioned between the transition duct and the flow sleeve, the rib extending around an entire periphery of the duct passage and fluidly dividing the upstream cavity and the downstream cavity, wherein the upstream cavity is configured to direct a first portion of a working fluid towards the upstream outlet, and wherein the downstream cavity is configured to direct a second portion of the working fluid towards the downstream outlet; and
a turbine section in communication with the transition duct, the turbine section comprising a first stage bucket assembly, wherein no nozzles are disposed upstream of the first stage bucket assembly.
20. The turbomachine of claim 19 , wherein the rib generally fluidly isolates the upstream cavity and the downstream cavity from each other.