초록 ▼

The invention relates to a gas turbine. The aim of the invention is to provide an axial sealing between a vane ring and a moving blade ring, which has an excellent sealing effect, is easy to install and inexpensive to produce. For this purpose, a sealing element is used that extends across at least

The invention relates to a gas turbine. The aim of the invention is to provide an axial sealing between a vane ring and a moving blade ring, which has an excellent sealing effect, is easy to install and inexpensive to produce. For this purpose, a sealing element is used that extends across at least a fourth of the hot gas channel circumference. Preferably, said sealing element extends across approximately half the circumference and is inserted in grooves of the vane support and the vane platforms.

대표청구항 ▼

The invention claimed is: 1. An axial flow gas turbine engine arranged about a central axis, comprising: a compressor section; a combustion chamber; a turbine section having a plurality of guide vane rings and rotor blade rings arranged in axial succession in a hot-gas duct that contains a hot gas

The invention claimed is: 1. An axial flow gas turbine engine arranged about a central axis, comprising: a compressor section; a combustion chamber; a turbine section having a plurality of guide vane rings and rotor blade rings arranged in axial succession in a hot-gas duct that contains a hot gas flow; a cooling air flow for cooling the guide vane rings and the rotor blade rings, where the pressure of the cooling air flow decreases in the direction of the hot gas flow; a guide vane carrier a flat sealing element arranged between a groove in the guide vane ring and a groove in the guide vane carrier which seals the different pressure levels associated with respective adjacent rings and extends as a single piece around at least a quarter of a circle concentric with the central axis of the engine; and means for urging the sealing element against the grooves in the guide vane ring and guide vane carrier and applying pressure against the middle of the sealing element so as to evenly apply the pressure to both the grooves. 2. The gas turbine as claimed in claim 1, wherein the sealing element extends half of the circle. 3. The gas turbine as claimed in claim 2, wherein the sealing element is formed as an annular metal sheet with a surface extending in the radial direction and having an outer and an inner edge. 4. The gas turbine as claimed in claim 3, wherein the sealing element inner edge is arranged in grooves within a guide vane ring that is located in the side furthest from the hot-gas duct and the outer edge is arranged in a carrier groove in the guide vane carrier, the guide vane carrier having a predetermined groove side wall. 5. The gas turbine as claimed in claim 4, wherein the sealing element is clamped to the groove side wall using a screw which presses the sealing element onto the opposite platform groove side wall and predetermined carrier groove side wall, the screw pressing against the middle of the sealing element on the surface thereof. 6. The gas turbine as claimed in claim 5, wherein the guide vanes each have an axial fixed point at which they are fixed against axial displacement in the guide vane carrier by a hooked formation, with the sealing element being arranged in the region of the axial fixed points. 7. The gas turbine as claimed in claim 3, wherein the guide vanes each have an axial fixed point at which they are fixed against axial displacement in the guide vane carrier by a hooked formation, with the sealing element being arranged opposite the region of the axial fixed points. 8. An axial flow gas turbine engine sealing system, comprising: a guide vane ring having a groove; a guide vane carrier having a groove; a sealing element arranged between the guide vane ring and the guide vane carrier which seals the different pressure levels associated with the respective adjacent rings and extends as a single piece around at least a quarter of a circle concentric with the central axis of the engine and means for urging the sealing element against the grooves in the guide vane ring and guide vane carrier and applying pressure against the middle of the sealing element so as to evenly apply the pressure to both the grooves. 9. A semi-annular turbine blade and vane stage seal, comprising: an inner seal edge arranged in a guide vane groove that is located distal a hot gas duct; an outer seal edge arranged in a vane carrier groove; a metallic seal sheet positioned within the grooves of the guide vane and vane carrier and having an arc length between 90째 and 180 째; wherein the stage seal isolates different cooling flow pressure levels associated with an adjacent stage; and means for urging the sealing element against the grooves in the guide vane ring and guide vane carrier and applying pressure against the middle of the sealing element so as to evenly apply the pressure to both the grooves.