Controlling cooling flow in a cooled turbine vane or blade using an impingement tube
US10502071B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Mar 10, 2015 |
| Grant date | Dec 10, 2019 |
| Priority date | — |
| Expiry date | May 20, 2036 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2260/201
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
An airfoil for a gas turbine having an outer shell with an inner volume and an inner shell arranged within the inner volume of the outer shell, wherein the inner shell has an aerodynamic profile having an inner nose section and an inner tail section. A first cooling channel and a second cooling channel merge into a common cooling channel at an inner tail section. A first tail fin is arranged between the first cooling channel and the common cooling channel such that a first mass flow rate of the cooling fluid flowing through the first cooling channel is controllable. A second tail fin is arranged between the second cooling channel and the common cooling channel such that a second mass flow rate of the cooling fluid flowing through the second cooling channel is controllable.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.