GB716263A - Improvements in or relating to gas turbine engines - Google Patents
Improvements in or relating to gas turbine enginesInfo
- Publication number
- GB716263A GB716263A GB428052A GB428052A GB716263A GB 716263 A GB716263 A GB 716263A GB 428052 A GB428052 A GB 428052A GB 428052 A GB428052 A GB 428052A GB 716263 A GB716263 A GB 716263A
- Authority
- GB
- United Kingdom
- Prior art keywords
- plant
- blades
- starting
- air
- gas turbine
- 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
- 230000008878 coupling Effects 0.000 abstract 4
- 238000010168 coupling process Methods 0.000 abstract 4
- 238000005859 coupling reaction Methods 0.000 abstract 4
- 238000002485 combustion reaction Methods 0.000 abstract 1
- 230000004048 modification Effects 0.000 abstract 1
- 238000012986 modification Methods 0.000 abstract 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/26—Starting; Ignition
- F02C7/268—Starting drives for the rotor, acting directly on the rotor of the gas turbine to be started
- F02C7/27—Fluid drives
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Control Of Turbines (AREA)
Abstract
716,263. Gas turbine plant. BRISTOL AEROPLANE CO., Ltd. Feb. 6, 1953 [Feb. 18, 1952], No. 4280/52. Class 110(3) [Also in Group XXVIII] A gas turbine plant comprises a ring of starting blades 27, which are carried by the compressor rotor 15 of the plant and are disposed co-axial therewith, and means to conduct air from a coupling member to a nozzle adapted to direct the air on to said blades for starting the plant, said coupling member and means for conducting air being carried by a fixed structure of the plant and said coupling member being adapted for attachment to, or detachment from, a source of compressed air. Compressed air from a bottle 37 is fed through a pipe 36, an aerofoil member 21, ducts 33, 34 and a manifold 31 to the blades 27, the manifold being provided with nozzle outlets. The ducting 21, 33, 34 is duplicated and the pipe 36 is connected to the more conveniently situated member 21 by a releasable coupling 35. The bottle has pressurereducing and starting valves 38, 39 either or both of which may be' carried within the compressor casing 10 and disposed' between the members 31, 35. In a modification, the plant comprises a centrifugal compressor having' inward-radial flow starting blades mounted on the back thereof, the exhaust from said starting blades being discharged separately from or being mixed with the main airstream fed to the combustion equipment of the plant.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB428052A GB716263A (en) | 1953-02-06 | 1953-02-06 | Improvements in or relating to gas turbine engines |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB428052A GB716263A (en) | 1953-02-06 | 1953-02-06 | Improvements in or relating to gas turbine engines |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB716263A true GB716263A (en) | 1954-09-29 |
Family
ID=9774143
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB428052A Expired GB716263A (en) | 1953-02-06 | 1953-02-06 | Improvements in or relating to gas turbine engines |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB716263A (en) |
Cited By (20)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE1009438B (en) * | 1955-11-23 | 1957-05-29 | Power Jets Res & Dev Ltd | Method and device for carrying out the method for operating a jet engine |
| DE1043721B (en) * | 1955-10-05 | 1958-11-13 | Power Jets Res & Dev Ltd | Jet engine |
| DE1062987B (en) * | 1956-01-05 | 1959-08-06 | Power Jets Res & Dev Ltd | Gas turbine jet engine |
| EP1331379A3 (en) * | 2002-01-17 | 2005-02-09 | The Boeing Company | Tip impingement turbine air starter for turbine engine |
| WO2006112807A3 (en) * | 2004-12-01 | 2006-12-07 | United Technologies Corp | Turbine engine and method for starting a 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 |
| US8087885B2 (en) | 2004-12-01 | 2012-01-03 | United Technologies Corporation | Stacked annular components for turbine engines |
| US8096753B2 (en) | 2004-12-01 | 2012-01-17 | United Technologies Corporation | Tip turbine engine and operating method with reverse core airflow |
| US8104257B2 (en) | 2004-12-01 | 2012-01-31 | United Technologies Corporation | Tip turbine engine with multiple fan and turbine stages |
| US8561383B2 (en) | 2004-12-01 | 2013-10-22 | United Technologies Corporation | Turbine engine with differential gear driven fan and compressor |
| EP2267288A3 (en) * | 2009-06-25 | 2014-05-21 | Hamilton Sundstrand Corporation | Lightweight start system for a gas turbine engine |
| US9003759B2 (en) | 2004-12-01 | 2015-04-14 | United Technologies Corporation | Particle separator for tip turbine engine |
-
1953
- 1953-02-06 GB GB428052A patent/GB716263A/en not_active Expired
Cited By (25)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE1043721B (en) * | 1955-10-05 | 1958-11-13 | Power Jets Res & Dev Ltd | Jet engine |
| DE1009438B (en) * | 1955-11-23 | 1957-05-29 | Power Jets Res & Dev Ltd | Method and device for carrying out the method for operating a jet engine |
| DE1062987B (en) * | 1956-01-05 | 1959-08-06 | Power Jets Res & Dev Ltd | Gas turbine jet engine |
| EP1331379A3 (en) * | 2002-01-17 | 2005-02-09 | The Boeing Company | Tip impingement turbine air starter for turbine engine |
| US7976272B2 (en) | 2004-12-01 | 2011-07-12 | United Technologies Corporation | Inflatable bleed valve for a turbine engine |
| US8087885B2 (en) | 2004-12-01 | 2012-01-03 | United Technologies Corporation | Stacked annular components for turbine engines |
| 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 |
| US7882695B2 (en) | 2004-12-01 | 2011-02-08 | United Technologies Corporation | Turbine blow down starter for 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 |
| WO2006112807A3 (en) * | 2004-12-01 | 2006-12-07 | United Technologies Corp | Turbine engine and method for starting 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 |
| US7845157B2 (en) | 2004-12-01 | 2010-12-07 | United Technologies Corporation | Axial compressor for tip turbine engine |
| US8096753B2 (en) | 2004-12-01 | 2012-01-17 | United Technologies Corporation | Tip turbine engine and operating method with reverse core airflow |
| US8104257B2 (en) | 2004-12-01 | 2012-01-31 | United Technologies Corporation | Tip turbine engine with multiple fan and turbine stages |
| 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 |
| US9541092B2 (en) | 2004-12-01 | 2017-01-10 | United Technologies Corporation | Tip turbine engine with reverse core airflow |
| US8950171B2 (en) | 2004-12-01 | 2015-02-10 | United Technologies Corporation | Counter-rotating gearbox for tip turbine engine |
| US9003768B2 (en) | 2004-12-01 | 2015-04-14 | United Technologies Corporation | Variable fan inlet guide vane assembly, turbine engine with such an assembly and corresponding controlling method |
| US9003759B2 (en) | 2004-12-01 | 2015-04-14 | United Technologies Corporation | Particle separator for tip turbine engine |
| EP2267288A3 (en) * | 2009-06-25 | 2014-05-21 | Hamilton Sundstrand Corporation | Lightweight start system for a gas turbine engine |
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