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Durable Turbine Vanes, Durable Gas Turbine Vanes and Durable Turbine Nozzle Vanes

A gas turbine and turbine nozzle technology, which is applied in the field of durable turbine vane and durable turbine nozzle vane, can solve the problems of not being able to fully provide pressurized air holes, and not being able to successfully manufacture pressurized air holes at will

Active Publication Date: 2017-03-08
GENERAL ELECTRIC CO
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0010] In the past, there was an unmet need to not adequately provide pressurized air orifices to allow higher temperature operation due to the curvature near the vane leading edge
Furthermore, because of the vane curvature in this region, pressurized air holes cannot be successfully fabricated at will, and as a result, the cooling film will often not necessarily be sufficiently "attached" to the vane surface, exposing the vane to high temperature combustion gas flow path

Method used

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  • Durable Turbine Vanes, Durable Gas Turbine Vanes and Durable Turbine Nozzle Vanes
  • Durable Turbine Vanes, Durable Gas Turbine Vanes and Durable Turbine Nozzle Vanes
  • Durable Turbine Vanes, Durable Gas Turbine Vanes and Durable Turbine Nozzle Vanes

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Embodiment Construction

[0022] Reference will now be made in detail to the provided embodiments, one or more examples of which are illustrated in the accompanying drawings. The various embodiments are provided by way of illustration, not limitation of the disclosed embodiments. In fact, it will be apparent to those skilled in the art that various modifications and variations can be made in the present invention without departing from the spirit and scope of the present disclosure. For example, features illustrated or described as part of one embodiment can be used with another embodiment to yield still a further embodiment. Thus, it is intended that the present invention covers such modifications and variations as come within the scope of the appended claims and their equivalents.

[0023] This embodiment applies to gas turbine engines, such as aviation, power generation, industrial or marine, where the combustor burns fuel and discharges the hot combustion gases into a high pressure turbine. The s...

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Abstract

A durable nozzle vane includes a leading edge where hot combustion gas impinges on the vane, a pressure side extending from the leading edge to a trailing edge and a suction side extending from the leading edge to the trailing edge, a blunt region along the suction side between the leading edge and a high curvature region, the blunt region having small curvature in the length between the leading edge and the high curvature region allowing for at least two rows of cooling apertures.

Description

[0001] Cross References to Related Applications [0002] This application claims the benefit of U.S. Provisional Application No. 61 / 639,303, filed April 27, 2012, and U.S. Provisional Application No. 61 / 790,885, filed March 15, 2013, both of which are incorporated by reference in their entirety incorporated. Background technique [0003] The present embodiments generally relate to devices, methods, and / or systems for improving durability of nozzle segments for turbine engines. More specifically, without limitation, the present embodiments relate to more durable blades for nozzles of gas turbine engines that have improved cooling capabilities and allow higher temperature operation without negatively impacting aerodynamic performance. [0004] A gas turbine engine typically includes a compressor, combustor, and turbine. Compressors and turbines typically include rows of airfoils that are staged and axially stacked. Each stage includes a set of circumferentially spaced stator ...

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F01D5/18
CPCF01D5/186F01D5/187F05D2240/303F05D2260/202Y02T50/60F01D9/02
Inventor J.S.巴布尼克R.J.巴茨D.E.德默斯R.A.弗里德里克T.S.赫夫伦S.M.莫尔森
Owner GENERAL ELECTRIC CO