Seal assembly between a transition duct and the first row vane assembly for use in turbine engines
US-2017248027-A1 · Aug 31, 2017 · US
Slots for turbomachine structures
US2016169039A1 · US · A1
| Field | Value |
|---|---|
| Publication number | US-2016169039-A1 |
| Application number | US-201514969426-A |
| Country | US |
| Kind code | A1 |
| Filing date | Dec 15, 2015 |
| Priority date | Dec 15, 2014 |
| Publication date | Jun 16, 2016 |
| Grant date | — |
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- Title
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- Abstract
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Abstract
Official abstract text for this publication.
A component for a turbomachine includes an annular body defining an inner diameter portion and an outer diameter portion, and a crack guiding slot defined in a surface of the annular body extending from the inner diameter portion radially outward toward the outer diameter portion or extending from the outer diameter portion radially inward toward the inner diameter portion. The outer diameter portion can be mountable to a stationary structure of a turbomachine. The inner diameter portion can be mountable to a turbine vane.
First claim
Opening claim text (preview).
What is claimed is: 1 . A component for a turbomachine, comprising: an annular body defining an inner diameter portion and an outer diameter portion; and a crack guiding slot defined in a surface of the annular body extending from the inner diameter portion radially outward toward the outer diameter portion or extending from the outer diameter portion radially inward toward the inner diameter portion. 2 . The component of claim 1 , wherein the outer diameter portion is mountable to a stationary structure of the turbomachine. 3 . The component of claim 1 , wherein the inner diameter portion is mountable to a turbine vane. 4 . The component of claim 1 , wherein the crack guiding slot is V-shaped in cross-section. 5 . The component of claim 1 , wherein the crack guiding slot includes one flat surface and one curved surface in cross-section. 6 . The component of claim 1 , wherein the crack guiding slot is U-shaped in cross-section. 7 . The component of claim 1 , wherein the crack guiding slot extends into the surface of the annular body to a depth of up to about 80% of the thickness of the annular body proximate the crack guiding slot. 8 . The component of claim 1 , further including a crack arresting hole defined at a radially outward terminus of the crack guiding slot. 9 . The component of claim 8 , wherein the crack arresting hole is defined in the annular body to the same depth as the crack guiding slot. 10 . The component of claim 9 , wherein the crack arresting hole is defined through the entire thickness of the annular body. 11 . The component of claim 1 , wherein the crack guiding slot is one of a plurality of crack guiding slots, each spaced apart in a predetermined circumferential pattern. 12 . The component of claim 11 , further comprising a plurality of crack arresting holes for each crack guiding slot defined at a radially outward terminus of each crack guiding slot. 13 . A method, comprising: forming a turbomachine component support, the component support including an annular body defining an inner diameter portion and an outer diameter portion; and defining a crack guiding slot in a surface of the annular body extending from the inner diameter portion radially outward toward the outer diameter portion or extending from the outer diameter portion radially inward toward the inner diameter portion. 14 . The method of claim 13 , wherein the component support is a vane support. 15 . The method of claim 13 , wherein defining the crack guiding slot includes defining a V-shaped slot in cross-section. 16 . The method of claim 13 , wherein defining the crack guiding slot includes defining one flat surface and one curved surface in the slot. 17 . The method of claim 13 , wherein defining the crack guiding slot includes defining a U-shaped slot in cross-section. 18 . The method of claim 13 , wherein defining the crack guiding slot includes defining the slot into the surface of the annular body to a depth of up to about 80% of the thickness of the annular body proximate the crack guiding slot. 19 . The method of claim 13 , further including disposing a crack arresting hole at a radially outward terminus of the crack guiding slot. 20 . The method of claim 19 , wherein disposing the crack arresting hole includes defining the crack arresting hole in the annular body to the same depth as the crack guiding slot.
Assignees
Inventors
Classifications
particularly aimed at mechanical or thermal stress reduction · CPC title
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using stator or rotor components with predetermined thermal response, e.g. selective insulation, thermal inertia, differential expansion · CPC title
- F01D9/04Primary
forming ring or sector · CPC title
- F01D25/12Primary
Cooling · CPC title
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- What does patent US2016169039A1 cover?
- A component for a turbomachine includes an annular body defining an inner diameter portion and an outer diameter portion, and a crack guiding slot defined in a surface of the annular body extending from the inner diameter portion radially outward toward the outer diameter portion or extending from the outer diameter portion radially inward toward the inner diameter portion. The outer diameter p…
- Who is the assignee on this patent?
- United Technologies Corp
- What technology area does this patent fall under?
- Primary CPC classification F01D9/04. Mapped technology areas include Mechanical Engineering.
- When was this patent published?
- Publication date Thu Jun 16 2016 00:00:00 GMT+0000 (Coordinated Universal Time) (A1). Legal status and post-grant events are not shown on this page.
- What related patents are in patentsdb?
- We list 3 related publications on this page (citations in our corpus or others sharing the same primary CPC).