Cooled turbine vane platform comprising forward, midchord and aft cooling chambers in the platform
US-9874102-B2 · Jan 23, 2018 · US
Turbomachine blade with generally radial cooling conduit to wheel space
US2017152752A1 · US · A1
| Field | Value |
|---|---|
| Publication number | US-2017152752-A1 |
| Application number | US-201514955563-A |
| Country | US |
| Kind code | A1 |
| Filing date | Dec 1, 2015 |
| Priority date | Dec 1, 2015 |
| Publication date | Jun 1, 2017 |
| Grant date | — |
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- Title
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Abstract
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A turbomachine blade is disclosed including an airfoil including a cooling fluid plenum extending therein and a trailing edge cooling opening extending from the cooling fluid plenum through a trailing edge of the airfoil. A platform may couple the airfoil to a shank, the platform including a trailing edge root extending downstream relative to the shank. At least one cooling conduit delivers a cooling fluid radially inward from at least one of the cooling fluid plenum and the trailing edge cooling opening to a wheel space that is adjacent the shank and radially inward from the trailing edge root. A related turbomachine is also disclosed.
First claim
Opening claim text (preview).
What is claimed is: 1 . A turbomachine blade, comprising: an airfoil including a cooling fluid plenum extending therein and a trailing edge cooling opening extending from the cooling fluid plenum through a trailing edge of the airfoil; a platform for coupling the airfoil to a shank, the platform including a trailing edge root extending downstream relative to the shank; and at least one cooling conduit delivering a cooling fluid radially inward from at least one of the cooling fluid plenum and the trailing edge cooling opening to a wheel space that is adjacent the shank and radially inward from the trailing edge root. 2 . The turbomachine blade of claim 1 , wherein the at least one cooling conduit includes at least two cooling conduits, wherein at least one of the at least two cooling conduits extends from the cooling fluid plenum and at least one of the at least two cooling conduits extends from the trailing edge cooling opening. 3 . The turbomachine blade of claim 2 , wherein one cooling conduit extends from the cooling fluid plenum and two cooling conduits extend from the trailing edge cooling opening. 4 . The turbomachine blade of claim 1 , wherein each cooling conduit extends at an angle relative to radial between approximately 0° to approximately 45°. 5 . The turbomachine blade of claim 1 , wherein the airfoil is coupled to the trailing edge root by a fillet, and wherein the at least one cooling conduit extends through the trailing edge root. 6 . The turbomachine blade of claim 1 , wherein the trailing edge cooling opening is a radially innermost cooling opening of a plurality of trailing edge cooling openings radially spaced along the trailing edge of the airfoil. 7 . A turbomachine, comprising: a rotor including a plurality of turbomachine blade, each turbomachine blade including: an airfoil including a cooling fluid plenum extending therein and a trailing edge cooling opening extending from the cooling fluid plenum through a trailing edge of the airfoil; a platform for coupling the airfoil to a shank, the platform including a trailing edge root extending downstream relative to the shank; and at least one cooling conduit delivering a cooling fluid radially inward from at least one of the cooling fluid plenum and the trailing edge cooling opening to a wheel space that is adjacent the shank and radially inward from the trailing edge root. 8 . The turbomachine of claim 7 , wherein the at least one cooling conduit includes at least two cooling conduits, wherein at least one of the at least two cooling conduits extends from the cooling fluid plenum and at least one of the at least two cooling conduits extends from the trailing edge cooling opening. 9 . The turbomachine of claim 8 , wherein one cooling conduit extends from the cooling fluid plenum and two cooling conduits extend from the trailing edge cooling opening. 10 . The turbomachine of claim 8 , wherein each cooling conduit extends at an angle relative to radial between approximately 0° to approximately 45°. 11 . The turbomachine of claim 7 , wherein the airfoil is coupled to the trailing edge root by a fillet, and wherein the at least one cooling conduit extends through the trailing edge root. 12 . The turbomachine of claim 7 , wherein the trailing edge cooling opening is a radially innermost cooling opening of a plurality of trailing edge cooling openings radially spaced along the trailing edge of the airfoil.
Assignees
Inventors
Classifications
- F01D5/187Primary
Convection cooling · CPC title
related to the trailing edge of a rotor blade · CPC title
Platforms for stationary or moving blades · CPC title
on the side of the rotor disc · CPC title
Heat transfer, e.g. cooling · CPC title
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Frequently asked questions
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- What does patent US2017152752A1 cover?
- A turbomachine blade is disclosed including an airfoil including a cooling fluid plenum extending therein and a trailing edge cooling opening extending from the cooling fluid plenum through a trailing edge of the airfoil. A platform may couple the airfoil to a shank, the platform including a trailing edge root extending downstream relative to the shank. At least one cooling conduit delivers a c…
- Who is the assignee on this patent?
- Gen Electric
- What technology area does this patent fall under?
- Primary CPC classification F01D5/187. Mapped technology areas include Mechanical Engineering.
- When was this patent published?
- Publication date Thu Jun 01 2017 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 5 related publications on this page (citations in our corpus or others sharing the same primary CPC).