Impingement cooling of gas turbine blades or vanes
US9500087B2 · kind B2 · utility
3Cited by
14References
8Claims
0Family size
Assignee
Inventor
Key dates
| Filing date | Dec 2, 2011 |
| Grant date | Nov 22, 2016 |
| Priority date | — |
| Expiry date | Apr 20, 2033 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY10T29/49359
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A turbine component includes a hollow aerofoil and an impingement tube located within the hollow aerofoil. The impingement tube is formed from at least two separate sections each extending span wise through the hollow aerofoil. Adjacent sections of the impingement tube are connected together by a locking device. The locking device is insertable into the hollow aerofoil and locks the impingement tube into place in the hollow aerofoil. The locking device is a roll pin being located in an axially direction between said sections and has a main extension which extends in a radial direction of the hollow aerofoil.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.