초록 ▼

The invention relates to a gas turbine, for energy generation, with a compressor, arranged coaxially to a rotor, mounted such as to rotate, for the compression of an inlet gaseous fluid, at least partly serving for combustion of a fuel in a subsequent annular combustion chamber, with generation of a

The invention relates to a gas turbine, for energy generation, with a compressor, arranged coaxially to a rotor, mounted such as to rotate, for the compression of an inlet gaseous fluid, at least partly serving for combustion of a fuel in a subsequent annular combustion chamber, with generation of a hot working medium, with an annular diffuser arranged coaxially to the rotor, between the compressor and the annular combustion chamber, for distribution and deflection of the fluid, whereby a part of the fluid is diverted as cooling fluid for the turbine stages after the combustion chamber, by means of a dividing element, arranged in the fluid flow. According to the invention, a compact diffuser and an economical gas turbine with an improved flow for the diversion of cooling air may be achieved, whereby the annular dividing element, arranged coaxially to the rotor, comprises at least one opening, facing the fluid flow and the dividing element is supported on the diffuser, by means of several hollow rib-like support elements, by means of which the cooling fluid, diverted through the opening, is first directed towards the rotor.

대표청구항 ▼

1. A diffuser for extracting cooling air for turbine stages of a gas turbine, comprising: an inner wall forming a radially inner side of the diffuser;an outer wall forming a radially outer side of the diffuser that provides a flow passage having an inlet and an outlet where the inner and outer walls

1. A diffuser for extracting cooling air for turbine stages of a gas turbine, comprising: an inner wall forming a radially inner side of the diffuser;an outer wall forming a radially outer side of the diffuser that provides a flow passage having an inlet and an outlet where the inner and outer walls increasingly diverge along the direction of fluid flow;an annular passage bypassing extracted cooling air around a combustion chamber and to the turbine stages, wherein the annular passage is located radially inward of the inner wall;an annular distribution element arranged coaxially along a longitudinal axis and between the inner and outer walls of the diffuser having a centrally located opening that creates a cooling air part-stream of the compressor discharge fluid flow, where the distribution element opening is arranged on a leading edge of the distribution element and forms an annular opening in a central region between the outer wall and the inner wall; anda plurality of hollow lower and upper supporting elements arranged between the inner and outer walls, respectively, of the diffuser and the annular distribution element wherein at least one of the hollow lower supporting elements is in fluid communication with the annular passage. 2. The diffuser as claimed in claim 1, wherein the distribution element creates a radially outward and a radially inward streams that coaxially surround the centrally located cooling air part stream. 3. The diffuser as claimed in claim 1, wherein a tube including a nozzle is routed through one of the plurality of hollow upper supporting elements, where the nozzle is arranged within the annular opening of the distribution element and injects a cooling fluid into the cooling air part-stream. 4. The diffuser as claimed in claim 3, wherein the cooling fluid is water. 5. The diffuser as claimed in claim 2, wherein a wall of the distribution element is located opposite the inner wall to form a radially inner part-passage and a fuel supply tube extends through a hollow upper supporting element of the plurality of hollow upper supporting elements and wherein the fuel supply tube connects to a passage in the distribution element connected to the radially inner part-passage that defines the radially inward stream and introduces a fuel into the radially inner part-passage. 6. The diffuser as claimed in claim 1, wherein the annular opening is segmented along a circumference of the annular distribution element. 7. The diffuser as claimed in claim 1, wherein the annular distribution element is arranged centrally between the two diverging walls of the diffuser and has a wedge shape defined by two walls such that each distribution element wall and the adjacent diffuser wall form two annular part-passages for the fluid. 8. The diffuser as claimed in claim 7, wherein each of the two annular part-passages have a substantially constant cross section over each flow length of the two annular part-passages. 9. The diffuser as claimed in claim 1, wherein the hollow lower supporting elements route a cooling fluid through an interior of the hollow lower supporting elements and are supported against the diffuser inner wall. 10. The diffuser as claimed in claim 1, wherein the cooling air part-stream is routed toward a rotor of the gas turbine by the hollow lower supporting elements.