Flow body for a gas turbine, gas turbine, method for manufacturing a flow body for a gas turbine, and method for repairing a flow body of a gas turbine
US-2024376825-A1 · Nov 14, 2024 · US
Method and apparatus for cooling gas turbine rotor blades
US9033652B2 · US · B2
| Field | Value |
|---|---|
| Publication number | US-9033652-B2 |
| Application number | US-201113250345-A |
| Country | US |
| Kind code | B2 |
| Filing date | Sep 30, 2011 |
| Priority date | Sep 30, 2011 |
| Publication date | May 19, 2015 |
| Grant date | May 19, 2015 |
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Abstract
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An airfoil for a gas turbine engine includes a first sidewall and a second sidewall coupled together at a leading edge and a trailing edge, such that a cavity is defined therebetween. A plurality of cooling circuits are defined within the cavity. Each cooling circuit channels cooling fluid through at least one cooling chamber to facilitate cooling the airfoil. More specifically, a cascade impingement circuit, a down pass circuit, a flag tip circuit, and a trailing edge circuit are provided. The cascade impingement circuit includes a central chamber and a plurality of impingement chambers.
First claim
Opening claim text (preview).
What is claimed is: 1. An airfoil for a gas turbine engine, said airfoil comprising: a first sidewall and a second sidewall coupled together at a leading edge and a trailing edge, such that a cavity is defined therebetween; a first cooling circuit defined within said cavity, said first cooling circuit comprising a central chamber and at least one impingement chamber having a leading edge chamber, a first cascade impingement chamber, and a second cascade impingement chamber, said…
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Cross-Sectional Technologies · mapped topic
- F01D5/187Primary
Mechanical Engineering · mapped topic
Mechanical Engineering · mapped topic
Mechanical Engineering · mapped topic
Cross-Sectional Technologies · mapped topic
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Frequently asked questions
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- What does patent US9033652B2 cover?
- An airfoil for a gas turbine engine includes a first sidewall and a second sidewall coupled together at a leading edge and a trailing edge, such that a cavity is defined therebetween. A plurality of cooling circuits are defined within the cavity. Each cooling circuit channels cooling fluid through at least one cooling chamber to facilitate cooling the airfoil. More specifically, a cascade impin…
- Who is the assignee on this patent?
- Molter Steve Mark, Brassfield Steven Robert, Jendrix Richard William, and 5 more
- 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 Tue May 19 2015 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).