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
- 239000007789 gas Substances 0.000 abstract 2
- 238000002485 combustion reaction Methods 0.000 abstract 1
- 238000001816 cooling Methods 0.000 abstract 1
- 239000002184 metal Substances 0.000 abstract 1
- 238000005192 partition Methods 0.000 abstract 1
Landscapes
- Toys (AREA)
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB766728A true GB766728A (enrdf_load_stackoverflow) | 1900-01-01 |
Family
ID=1751799
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB766728D Expired GB766728A (enrdf_load_stackoverflow) |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB766728A (enrdf_load_stackoverflow) |
Cited By (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE1118538B (de) * | 1957-04-03 | 1961-11-30 | Rolls Royce | Nebenschlussgasturbinenstrahltriebwerk |
| 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 |
| US7607286B2 (en) | 2004-12-01 | 2009-10-27 | United Technologies Corporation | Regenerative turbine blade and vane cooling for a tip turbine engine |
| US7845157B2 (en) | 2004-12-01 | 2010-12-07 | United Technologies Corporation | Axial compressor for tip turbine engine |
| US7854112B2 (en) | 2004-12-01 | 2010-12-21 | United Technologies Corporation | Vectoring transition duct for turbine engine |
| US7882694B2 (en) | 2004-12-01 | 2011-02-08 | United Technologies Corporation | Variable fan inlet guide vane assembly for gas turbine engine |
| US7921635B2 (en) | 2004-12-01 | 2011-04-12 | United Technologies Corporation | Peripheral combustor for tip turbine engine |
| US7934902B2 (en) | 2004-12-01 | 2011-05-03 | United Technologies Corporation | Compressor variable stage remote actuation for turbine engine |
| US7937927B2 (en) | 2004-12-01 | 2011-05-10 | United Technologies Corporation | Counter-rotating gearbox for tip turbine engine |
| US7976272B2 (en) | 2004-12-01 | 2011-07-12 | United Technologies Corporation | Inflatable bleed valve for a turbine engine |
| US7980054B2 (en) | 2004-12-01 | 2011-07-19 | United Technologies Corporation | Ejector cooling of outer case for tip turbine engine |
| US8024931B2 (en) | 2004-12-01 | 2011-09-27 | United Technologies Corporation | Combustor for turbine engine |
| US8561383B2 (en) | 2004-12-01 | 2013-10-22 | United Technologies Corporation | Turbine engine with differential gear driven fan and compressor |
-
0
- GB GB766728D patent/GB766728A/en not_active Expired
Cited By (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE1118538B (de) * | 1957-04-03 | 1961-11-30 | Rolls Royce | Nebenschlussgasturbinenstrahltriebwerk |
| 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 |
| US7607286B2 (en) | 2004-12-01 | 2009-10-27 | United Technologies Corporation | Regenerative turbine blade and vane cooling for a tip turbine engine |
| US7845157B2 (en) | 2004-12-01 | 2010-12-07 | United Technologies Corporation | Axial compressor for tip turbine engine |
| US7854112B2 (en) | 2004-12-01 | 2010-12-21 | United Technologies Corporation | Vectoring transition duct for turbine engine |
| US7882694B2 (en) | 2004-12-01 | 2011-02-08 | United Technologies Corporation | Variable fan inlet guide vane assembly for gas turbine engine |
| US7921635B2 (en) | 2004-12-01 | 2011-04-12 | United Technologies Corporation | Peripheral combustor for tip turbine engine |
| US7934902B2 (en) | 2004-12-01 | 2011-05-03 | United Technologies Corporation | Compressor variable stage remote actuation for turbine engine |
| US7937927B2 (en) | 2004-12-01 | 2011-05-10 | United Technologies Corporation | Counter-rotating gearbox for tip turbine engine |
| US7976272B2 (en) | 2004-12-01 | 2011-07-12 | United Technologies Corporation | Inflatable bleed valve for a turbine engine |
| US7980054B2 (en) | 2004-12-01 | 2011-07-19 | United Technologies Corporation | Ejector cooling of outer case for tip turbine engine |
| US8024931B2 (en) | 2004-12-01 | 2011-09-27 | United Technologies Corporation | Combustor for turbine engine |
| US8276362B2 (en) | 2004-12-01 | 2012-10-02 | United Technologies Corporation | Variable fan inlet guide vane assembly, turbine engine with such an assembly and corresponding controlling method |
| US8561383B2 (en) | 2004-12-01 | 2013-10-22 | United Technologies Corporation | Turbine engine with differential gear driven fan and compressor |
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