The invention proposes a cooling system (42) for a gas turbine (1), with an annular duct extending axially in the compressor (5). In the annular duct, a ring (15) of compressor guide blades (14, 28, 33) and a ring (17) of moving blades (16) fastened to a rotor disk (19) of the rotor (3) are provided
The invention proposes a cooling system (42) for a gas turbine (1), with an annular duct extending axially in the compressor (5). In the annular duct, a ring (15) of compressor guide blades (14, 28, 33) and a ring (17) of moving blades (16) fastened to a rotor disk (19) of the rotor (3) are provided, with at least one cooling-air extraction point (34), arranged on the rotor (3), for diverting a cooling-air stream into a cooling-duct system arranged in the rotor (3), and with a turbine unit (8), in which, when the gas turbine (1) is in operation, components subjected to thermal stress by a hot gas (20) can be cooled by the divertible cooling-air stream, and also with a feed line (46) for feeding a liquid (45) into the cooling-air stream. In order to make it possible to feed a liquid into the cooling-air stream simply and cost-effectively, the invention proposes that the feed line (46) extend with a subduct (44) through at least one of the compressor guide blades (28, 33) of the ring (15), and the orifice (48, 49) for the outlet of the liquid (45) be connected in the region of the cooling-air extraction point (34).
대표청구항▼
The invention claimed is: 1. A cooling system for a gas turbine, comprising: an annular duct extending axially along a compressor portion of a rotor; at least one ring of a plurality of compressor guide blades fastened fixedly in terms of rotation, the compressor guide blades comprising: a securabl
The invention claimed is: 1. A cooling system for a gas turbine, comprising: an annular duct extending axially along a compressor portion of a rotor; at least one ring of a plurality of compressor guide blades fastened fixedly in terms of rotation, the compressor guide blades comprising: a securable blade root on which a blade profile and, following the latter, a blade head are formed; at least one cooling-air extraction point, arranged on the rotor, for diverting a cooling-air stream into a cooling-duct system arranged in the rotor and with a turbine unit; and at least one ring of moving blades fastened to a rotor disk of the rotor are provided, where each ring of moving blades is associated with one ring of compressor guide blades in each case, wherein when the gas turbine is in operation, components subjected to thermal stress by a hot gas cooled are by the divertible cooling-air stream, and also with a feed line for feeding a liquid into the cooling-air stream, the feed line having at least one orifice for the outlet of the liquid such that the feed line extends with a subduct through at least one of the compressor guide blades of the ring, and the orifice for the outlet of the liquid is connected in the region of the cooling-air extraction point, wherein the rotor has at least two directly adjacent rotor disks, between which is provided a radially outwardly open disk interspace, into which the blade heads of the compressor guide blades of the ring project. 2. The cooling system as claimed in claim 1, wherein a Plurality of compressor guide blades of the ring which are distributed symmertrically over the circumference have a subduct of the feed line and orfices for the outlet of the liquid. 3. The cooling system as claimed in claim 1, wherein the blade heads of the compressor guide blades of the ring are secured to a fastening ring which has for the liquid at least one passage duct with the orfice for the outlet of the liquid into the disk interspace. 4. The cooling system as claimed in claim 3, wherein the fastening ring has a number of passages and orifices for the outlet of the liquid which are distributed symmetrically over the circumference. 5. The cooling system as claimed in claim 1, wherein each orifice issuing into the disk interspace is located opposite the cooling-air extraction point. 6. The cooling system as claimed in claim 1, wherein each orifice issuing into the disk interspace is of nozzle-shaped design. 7. The cooling system as claimed in claim 1, characterized in that the orifice is shaped in such a way that the liquid has a flow component which is directed in the circumferential direction of the rotor and which is identical to a direction-of-rotation component of the rotor. 8. The cooling system as claimed in claim 1, wherein the feed line for feeding the liquid comprises a setting member, by means of which the fed quantity of liquid per unit time can be set. 9. The cooling system as claimed in claim 8, wherein the fed quantity of liquid can be adapted by a controller acting on the setting member.
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이 특허를 인용한 특허 (6)
Beeck, Alexander R., Air cooled turbine component having an internal filtration system.
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