The invention relates to a turbine blade, including a blade having a front edge and a rear edge, which blade transitions by means of a shaft into a blade root designed for fastening the turbine blade, and including a platform, which is arranged at the lower end of the blade in order to bound a flow
The invention relates to a turbine blade, including a blade having a front edge and a rear edge, which blade transitions by means of a shaft into a blade root designed for fastening the turbine blade, and including a platform, which is arranged at the lower end of the blade in order to bound a flow channel. The platform is designed as a separate component and can be connected to the blade in a form-fit manner. Flexible application is achieved in that the platform is composed of several individual platform elements, which enclose the blade in the assembled state.
대표청구항▼
1. A turbine blade or vane, comprising: a blade or vane airfoil with a leading edge and a trailing edge, the blade or vane airfoil merging via a shaft into a blade or vane root, the blade or vane root formed for fastening of the turbine blade or vane;a platform, arranged at a lower end of the blade
1. A turbine blade or vane, comprising: a blade or vane airfoil with a leading edge and a trailing edge, the blade or vane airfoil merging via a shaft into a blade or vane root, the blade or vane root formed for fastening of the turbine blade or vane;a platform, arranged at a lower end of the blade or vane airfoil to delimit a flow channel, wherein the platform is formed as a separate component and can be connected to the blade or vane airfoil with a positive fit, wherein the platform is composed of a plurality of individual platform elements, which, when assembled, enclose the blade or vane airfoil and wherein the platform elements are each provided with recesses which proceed from a separating plane and, when assembled, form an opening adapted to a profile of the blade or vane airfoil for the blade or vane airfoil passing through the platform; andwherein each platform element includes a protruding portion, a protruding portion of one platform element protruding in a direction of and overlapping with a non-protruding portion of the other platform element and the protruding portion of the other platform element protruding in a direction of and overlapping with a non-protrudinq portion of the one platform element, wherein the protruding elements are offset from one another and a locking channel is formed in the protruding portions and the non-protruding portion of the platform elements facing the protruding portions, the locking channel being filled with a filling. 2. The turbine blade or vane as claimed in claim 1, wherein the platform is composed of two platform elements. 3. The turbine blade or vane as claimed in claim 1, comprising: a circumferential sealing groove, for receiving a seal, in each platform element for sealing off with respect to the blade or vane airfoil along the opening; anda seal arranged in the circumferential sealing grooves of the platform elements. 4. The turbine blade or vane as claimed in claim 1, wherein the two platform elements are sealed off with respect to one another in the separating plane. 5. The turbine blade or vane as claimed in claim 1, wherein the two platform elements are releasably connected to one another. 6. The turbine blade or vane as claimed in claim 1, wherein the platform is fastened to the turbine blade or vane. 7. The turbine blade or vane as claimed in claim 6, wherein the platform is hooked to the turbine blade or vane. 8. The turbine blade or vane as claimed in claim 7, wherein the platform or the platform elements comprise hooks, for being hooked into a groove in the region of the shaft of the turbine blade or vane. 9. The turbine blade or vane as claimed in claim 6, wherein the platform or the platform elements is integrally connected to the turbine blade or vane. 10. The turbine blade or vane as claimed in claim 9, wherein the blade or vane airfoil or blade or vane shaft and the platform elements are each provided with a groove-like recess, and these groove-like recesses are arranged so as to lie opposite one another in such a manner that they form a locking channel, and this locking channel is filled with a filling. 11. The turbine blade or vane as claimed in claim 10, wherein the locking channel is formed continuously over the circumference of the blade or vane airfoil or blade or vane shaft. 12. The turbine blade or vane as claimed in claim 10, wherein the filling is a castable metal which assumes the solid state under the conditions of the intended use of the turbine blade or vane.
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이 특허에 인용된 특허 (5)
Brown, Wesley; Matheny, Alfred P., Composite blade and platform assembly.
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