GB766728A - - Google Patents
Info
- Publication number
- GB766728A GB766728A GB766728DA GB766728A GB 766728 A GB766728 A GB 766728A GB 766728D A GB766728D A GB 766728DA GB 766728 A GB766728 A GB 766728A
- Authority
- GB
- United Kingdom
- Prior art keywords
- rotor
- passages
- fan
- duct
- jet
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired
Links
Abstract
766,728. Gas turbine, jet propulsion engines. GARRETT CORPORATION. Oct. 12, 1954, No. 29408/54. Class 110 (3). In an aircraft propulsion system compressed air from the turbo-jet 1 is fed through a pipe 6 to an annular combustion chamber 23 feeding a rotor 18 with turbine passages leading to hollow fan blades 16 exhausting to the duct 13. The fan blades are made of sheet metal, are provided with internal partitions 40, and are welded to the rotor. The fan sucks air through the duct to mix with the exhaust gases, and an afterburner 51 controlled by a valve 50<SP>1</SP> is provided downstream of the fan. Cooling air passes through passages 27 in the wall 26 to the space around the rotor shaft 17 and escapes through passages 28 in the rotor.
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB766728A true GB766728A (en) | 1900-01-01 |
Family
ID=1751799
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB766728D Expired GB766728A (en) |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB766728A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE1118538B (en) * | 1957-04-03 | 1961-11-30 | Rolls Royce | Bypass gas turbine jet engine |
| WO2006059996A1 (en) * | 2004-12-01 | 2006-06-08 | United Technologies Corporation | Balanced turbine rotor fan blade for a tip turbine engine |
| WO2006060002A1 (en) * | 2004-12-01 | 2006-06-08 | United Technologies Corporation | Fan blade with a multitude of internal flow channels |
-
0
- GB GB766728D patent/GB766728A/en not_active Expired
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE1118538B (en) * | 1957-04-03 | 1961-11-30 | Rolls Royce | Bypass gas turbine jet engine |
| WO2006059996A1 (en) * | 2004-12-01 | 2006-06-08 | United Technologies Corporation | Balanced turbine rotor fan blade for a tip turbine engine |
| WO2006060002A1 (en) * | 2004-12-01 | 2006-06-08 | United Technologies Corporation | Fan blade with a multitude of internal flow channels |
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