Turbine rotor blade with low cooling flow
US8061990B1 · kind B1 · utility
Assignee
Inventor
Key dates
| Filing date | Mar 13, 2009 |
| Grant date | Nov 22, 2011 |
| Priority date | — |
| Expiry date | May 19, 2030 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2250/185
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A turbine rotor blade with a series of 3-pass serpentine flow near wall cooling circuits that extend along the airfoil to provide low flow cooling for the blade. the 3-pass serpentine circuits include a first channel positioned along the pressure side wall to provide near wall cooling, a third channel positioned along the suction side wall to provide near wall cooling, and a second or middle channel located between the two near wall channels in the cooler section of the airfoil. The two near wall radial extending cooling channels flow in a direction toward the blade tip so that the centrifugal force developed due to blade rotation will aid in driving the flow while the second channel is without trip strips and has a larger flow area to minimize flow loss. The first channel with cooler air provides near wall cooling to the hotter sections of the airfoil while the third channel uses the heated air to provide cooling to the cooler sections of the airfoil.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.