Attachment Faces for Clamped Turbine Stator of a Gas Turbine Engine
US-2018010473-A1 · Jan 11, 2018 · US
Gas turbine vane
US10221709B2 · US · B2
| Field | Value |
|---|---|
| Publication number | US-10221709-B2 |
| Application number | US-201514974831-A |
| Country | US |
| Kind code | B2 |
| Filing date | Dec 18, 2015 |
| Priority date | Dec 18, 2014 |
| Publication date | Mar 5, 2019 |
| Grant date | Mar 5, 2019 |
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- Title
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- Abstract
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Abstract
Official abstract text for this publication.
The present invention generally relates to a vane for a gas turbine, and more in particular it provides an innovative vane with improved flexibility leading to a reduction of stresses at the transition from the vane trailing edge to the vane platform, without interfering into the cooling scheme of such component. The present invention can increase flexibility of the vane platform by introducing on the vane platform a material cutback confined in the proximity of the trailing edge portion of the vane airfoil.
First claim
Opening claim text (preview).
The invention claimed is: 1. A gas turbine vane, comprising: a vane platform including a wedge face pressure side, a wedge face suction side and a circumferential groove extending from said wedge face pressure side to said wedge face suction side; a vane airfoil connected to said vane platform, the vane airfoil having a vane trailing edge and a vane leading edge; and a material cutback formed on said vane platform confined at said vane trailing edge, wherein the material cutback is a chamfer that declines from the leading edge toward the trailing edge and declines from a portion proximate an outer surface of the vane platform to a portion proximate the vane airfoil, the chamfer being formed on a base wall of the circumferential groove. 2. The gas turbine vane according to claim 1 , wherein said chamfer is formed on a free end portion of said base wall. 3. The gas turbine vane according to claim 1 , wherein said chamfer is formed on said base wall to create a stepped region there along. 4. The gas turbine vane according to claim 3 , wherein said chamfer has a depth in a range of 5-20 mm. 5. The gas turbine vane according to claim 1 , wherein said chamfer has a depth in a range of 5-20 mm. 6. The gas turbine blade according to claim 1 , wherein said vane platform comprises: a sealing slot extending along said wedge face pressure side.
Assignees
Inventors
Classifications
Platforms for stationary or moving blades · CPC title
related to the trailing edge of a stator vane · CPC title
- F01D9/041Primary
using blades (F01D5/148 takes precedence) · CPC title
- F01D9/02Primary
Nozzles; Nozzle boxes; Stator blades; Guide conduits {, e.g. individual nozzles (nozzle boxes F01D9/047)} · CPC title
particularly aimed at mechanical or thermal stress reduction · CPC title
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Frequently asked questions
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- What does patent US10221709B2 cover?
- The present invention generally relates to a vane for a gas turbine, and more in particular it provides an innovative vane with improved flexibility leading to a reduction of stresses at the transition from the vane trailing edge to the vane platform, without interfering into the cooling scheme of such component. The present invention can increase flexibility of the vane platform by introducing…
- Who is the assignee on this patent?
- Ansaldo Energia Switzerland AG
- What technology area does this patent fall under?
- Primary CPC classification F01D9/041. Mapped technology areas include Mechanical Engineering.
- When was this patent published?
- Publication date Tue Mar 05 2019 00:00:00 GMT+0000 (Coordinated Universal Time) (B2). Legal status and post-grant events are not shown on this page.
- What related patents are in patentsdb?
- We list 7 related publications on this page (citations in our corpus or others sharing the same primary CPC).