Cooling hole for a gas turbine engine component
US-2015377033-A1 · Dec 31, 2015 · US
Gas turbine engine component having suction side cutback opening
US9790801B2 · US · B2
| Field | Value |
|---|---|
| Publication number | US-9790801-B2 |
| Application number | US-201213728342-A |
| Country | US |
| Kind code | B2 |
| Filing date | Dec 27, 2012 |
| Priority date | Dec 27, 2012 |
| Publication date | Oct 17, 2017 |
| Grant date | Oct 17, 2017 |
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- Title
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- Abstract
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Abstract
Official abstract text for this publication.
An airfoil for a gas turbine engine, according to an exemplary aspect of the present disclosure includes, among other things, a pressure side wall and a suction side wall spaced apart from the pressure side wall and each extending between a leading edge portion and a trailing edge portion. A plurality of cutback openings are spaced along a radial axis of the suction side wall.
First claim
Opening claim text (preview).
What is claimed is: 1. An airfoil for a gas turbine engine, comprising: a pressure side wall and a suction side wall spaced apart from said pressure side wall and each extending between a leading edge portion and a trailing edge portion; a plurality of cutback openings formed in said suction side wall and that are spaced along a radial axis of said suction side wall such that a distal most portion of said suction side wall is offset from a distal most portion of said pressure side wall at each of said plurality of cutback openings; said pressure side wall excluding any cutback openings at said trailing edge portion; and wherein a gas path decelerating region of said suction side wall does not include film cooling holes. 2. The airfoil as recited in claim 1 , wherein said plurality of cutback openings are positioned at said trailing edge portion of said suction side wall. 3. The airfoil as recited in claim 1 , wherein at least a portion of said plurality of cutback openings are slots. 4. The airfoil as recited in claim 1 , wherein said plurality of cutback openings are positioned along an entire radial span of said suction side wall. 5. The airfoil as recited in claim 1 , wherein a rib extends between adjacent cutback openings of said plurality of cutback openings. 6. The airfoil as recited in claim 1 , comprising at least one film cooling hole at said trailing edge portion of said pressure side wall. 7. The airfoil as recited in claim 1 , comprising at least one film cooling hole in a gas path accelerating region of said suction side wall. 8. The airfoil as recited in claim 1 , wherein said distal most portion of said pressure side wall extends distally further than said distal most portion of said suction side wall.
Assignees
Inventors
Classifications
related to the trailing edge of a rotor blade · CPC title
Convection cooling · CPC title
- F01D5/186Primary
Film cooling (F01D5/187 takes precedence) · CPC title
Outlet · CPC title
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- What does patent US9790801B2 cover?
- An airfoil for a gas turbine engine, according to an exemplary aspect of the present disclosure includes, among other things, a pressure side wall and a suction side wall spaced apart from the pressure side wall and each extending between a leading edge portion and a trailing edge portion. A plurality of cutback openings are spaced along a radial axis of the suction side wall.
- Who is the assignee on this patent?
- Spangler Brandon W, United Technologies Corp
- What technology area does this patent fall under?
- Primary CPC classification F01D5/186. Mapped technology areas include Mechanical Engineering.
- When was this patent published?
- Publication date Tue Oct 17 2017 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 8 related publications on this page (citations in our corpus or others sharing the same primary CPC).