Cooling hole for a gas turbine engine component
US-2015377033-A1 · Dec 31, 2015 · US
US9103217B2 · US · B2
| Field | Value |
|---|---|
| Publication number | US-9103217-B2 |
| Application number | US-201213664503-A |
| Country | US |
| Kind code | B2 |
| Filing date | Oct 31, 2012 |
| Priority date | Oct 31, 2012 |
| Publication date | Aug 11, 2015 |
| Grant date | Aug 11, 2015 |
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A turbine blade having a tip including a tip shelf through which pass one or more diffuser cooling holes, the diffuser cooling holes directing the flow of cooling gas along the tip shelf, spreading the flow of cooling gas more evenly along the tip shelf and enhancing the formation of a curtain of cooling air along the tip shelf, leading to lower blade tip temperatures, reduced diversion of cooling air, and greater turbine blade life.
Opening claim text (preview).
What is claimed: 1. A gas turbine engine blade comprising: an airfoil including a first side joined to a second side at spaced apart leading and trailing edges to define therein a flow channel for channeling cooling air through said airfoil to cool said airfoil from combustion gases flowable over said first side and second side, said airfoil having a tip; said tip comprising: a tip floor extending between said first side and second side and between said leading and trailing ed…
Mechanical Engineering · mapped topic
Mechanical Engineering · mapped topic
Mechanical Engineering · mapped topic
Mechanical Engineering · mapped topic
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