Gas turbine with secondary cooling means
US4136516A · kind A · utility
Assignee
Inventor
Key dates
| Filing date | Jun 3, 1977 |
| Grant date | Jan 30, 1979 |
| Priority date | — |
| Expiry date | Jun 3, 1997 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
The blades of a gas turbine are primarily cooled by the circulation of a coolant through the hollow interiors thereof by the thermosiphon principle. Each hollow blade interior is also placed in fluid communication with a secondary coolant source, but secondary coolant flow is precluded by a plug filling the inlet fluid passage. Similar plugs fill apertures in the form of casting holes through each blade airfoil portion, the holes serving to discharge the secondary coolant from the blade interior. The plugs are fabricated of a material having a lower melting point temperature than that of the remainder of the blade airfoil portion such that, in the event of failure in the primary cooling system, the plugs will melt, thereby permitting the secondary coolant to rush through the blade and provide internal cooling thereof.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.