Turbine system
A turbine system is disclosed. The turbine system includes a 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 is offset from the inlet along the longitudinal axis and the tangential axis. The turbine system further includes a turbine section connected to the transition duct. The turbine section includes a plurality of shroud blocks at least partially defining a hot gas path, a plurality of buckets at least partially disposed in the hot gas path, and a plurality of nozzles at least partially disposed in the hot gas path. At least one of a shroud block, a bucket, or a nozzle includes means for withstanding high temperatures.
1. A turbine system, comprising:
a 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 and the tangential axis; and
a turbine section connected to the transition duct, the turbine section comprising a plurality of shroud blocks at least partially defining a hot gas path, a plurality of buckets at least partially disposed in the hot gas path, and a plurality of nozzles at least partially disposed in the hot gas path,
wherein at least one shroud block is formed from one ceramic matrix composite, and wherein a passage with one inlet and one outlet is defined in the at least one shroud block, wherein the passage makes a plurality of passes in the at least one shroud block along a width or length of the at least one shroud block, and wherein steam flows through the passage.
2. The turbine system of claim 1 , Wherein the outlet of the transition duct is further offset from the inlet along the radial axis.
3. The turbine system of claim 1 , wherein at least one of a stage of shroud blocks, a stage of buckets, or a stage of nozzles is formed from a ceramic matrix composite.
4. The turbine system of claim 1 , further comprising a plurality of transition ducts, each of the plurality of transition ducts disposed annularly about the longitudinal axis and connected to the turbine section.
5. The turbine system of claim 1 , wherein the plurality of buckets includes a first stage bucket assembly and a second stage bucket assembly, each of the first stage bucket assembly and second stage bucket assembly comprising a plurality of buckets disposed in a generally annular array.
6. The turbine system of claim 5 , wherein the plurality of nozzles includes a second stage nozzle assembly comprising a plurality of nozzles disposed in a generally annular array and positioned between the first stage bucket assembly and second stage bucket assembly.
7. The turbine system of claim 5 , wherein no nozzles are disposed upstream of the first stage bucket assembly.
8. The turbine system of claim 1 , wherein the transition duct extends from a fuel nozzle.
9. The turbine system of claim 1 , wherein the transition duct extends from a combustor liner.