Tip shroud for cooled blade of gas turbine
US6146098A · kind A · utility
Assignee
Inventors
Key dates
| Filing date | Feb 22, 1999 |
| Grant date | Nov 14, 2000 |
| Priority date | — |
| Expiry date | Feb 22, 2019 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2240/81
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A tip shroud for a moving blade that is made thin and light for use at a gas turbine downstream stage. Cooling air holes (13 to 16) having a slot shape, are formed in a tip shroud (11) of the moving blade (10). The cooling holes are opened in two side faces of the tip shroud to release the cooling air from the inside of the moving blade (10). In the upper face of the tip shroud 11, there are formed cooling air holes 20, which communicate with the higher pressure side in a combustion gas flow direction R to release the cooling air so that the cooling air flows from the higher pressure side to the lower pressure side so as to cool a high stress portion Y. A high stress portion X is likewise cooled with the cooling air coming from an adjoining moving blade. The slot shapes of the cooling air holes (13 to 16) allow the cooling air to flow widely, thereby cooling the face of the tip shroud (11), and the cooling air holes 20 cool the high stress portions X and Y effectively.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.