Chevron platform turbine vane
a technology of turbine vane and platform, which is applied in the direction of liquid fuel engines, vessel construction, marine propulsion, etc., can solve the problems of platform overheating and erosion
Inactive Publication Date: 2013-01-10
ALSTOM TECH LTD
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Benefits of technology
The present invention is about gas turbine vanes and a gas turbine vane assembly. The gas turbine vane has an inner arc-shaped platform, an outer arc-shaped platform, and an airfoil extending between them. The inner platform has a pressure side radial face and a suction side radial face, while the outer platform has a pressure side radial face and a suction side radial face. The airfoil is designed to have a planar wall on both suction side radial faces. In an alternate embodiment, the gas turbine vane has a relief cut on the pressure side radial face of the inner platform and on the suction side radial face of the outer platform. The gas turbine vane assembly is made of two vane assemblies fastened together by a fastener mechanism. This design provides improved performance and efficiency of gas turbine engines.
Problems solved by technology
Depending on the supply pressure of the cooling air within the platform region and the strength of the bow wave, the hot combustion gases of the bow wave may penetrate into the joint between adjacent vanes, causing overheating and erosion of the platform.
Method used
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[0020]The subject matter of the present invention is described with specificity herein to meet statutory requirements. However, the description itself is not intended to limit the scope of this patent. Rather, the inventors have contemplated that the claimed subject matter might also be embodied in other ways, to include different components, combinations of components, steps, or combinations of steps similar to the ones described in this document, in conjunction with other present or future technologies.
[0021]A gas turbine vane assembly 200 in accordance with an embodiment of the present invention is depicted in FIGS. 2-6. Referring to FIG. 2, the gas turbine vane assembly 200 comprises an inner arc-shaped platform 202 having a pressure side radial face 204 and a suction side radial face 206. The pressure side radial face comprises a first portion 204A, a second portion 204B, and a relief cut 208 located at the intersection of the first portion 204A and the second portion 204B.
[002...
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Gas turbine vanes of a gas turbine vane assembly have a reconfigured platform shape so as to reduce the ingestion of hot combustion gases into platform gaps between adjacent vane assemblies is disclosed. The vane platforms are configured so the joint between adjacent vanes is repositioned a sufficient distance away from the leading edge of the vane airfoil and the associated bow wave generated by the hot combustion gases passing over the airfoil leading edge.
Description
CROSS-REFERENCE TO RELATED APPLICATIONS[0001]Not applicable.TECHNICAL FIELD[0002]The present invention relates to gas turbine engines. More particularly, embodiments of the present invention relate to a gas turbine vane having a platform shaped in order to reduce ingestion of hot combustion gases into joints between adjacent vanes of a vane assembly.BACKGROUND OF THE INVENTION[0003]A gas turbine engine operates to produce mechanical work or thrust. For a land-based gas turbine engine, a generator is typically coupled to the engine through an axial shaft, such that the mechanical work of the engine is harnessed to generate electricity. A typical gas turbine engine comprises a compressor, at least one combustor, and a turbine, with the compressor and turbine coupled together through the axial shaft. In operation, as air passes through multiple stages of axially-spaced rotating blades and stationary vanes of the compressor, its pressure increases. The compressed air is then mixed with ...
Claims
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IPC IPC(8): F01D5/22
CPCF05D2250/183F01D11/008F01D9/041F05D2250/70F05D2240/80
Inventor MILLER, EDWARD LENWANG, YONGFIEBGIER, STEPHEN WAYNE
Owner ALSTOM TECH LTD