Turbine blade for gas turbine engine
US4462754A · kind A · utility
Assignee
Inventor
Key dates
| Filing date | Jun 22, 1982 |
| Grant date | Jul 31, 1984 |
| Priority date | — |
| Expiry date | Jun 22, 2002 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF01D5/187
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
The blade has an aerofoil portion (16) having a first (23), a second (24), a third (25) and a fourth (26) internal spanwise passage for cooling air arranged in chordwise succession with the first passage being at the leading edge wall (17) of the blade. The first and third passages are connected to respective a cooling air supplies (14A,14B) at the root end (11) of the blade. At the tip (28) of the blade the third passage is connected to the second passage to introduce air, warmed on passing through the third passage, into the second passage and ameliorate undue cooling of the internal walls (19,20) between the first, second and third passages. The third passage is also connected to the fourth passage for supply of cooling air to the trailing region of the blade. The second passage has outlets (24A) to the exterior of the blade whereby the flow through the second passage is controllable independently of the air supply to the fourth passage, i.e. to the trailing region of the blade.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.