GB803994A - Improvements in power units of the gas turbine type - Google Patents
Improvements in power units of the gas turbine typeInfo
- Publication number
- GB803994A GB803994A GB2194954A GB2194954A GB803994A GB 803994 A GB803994 A GB 803994A GB 2194954 A GB2194954 A GB 2194954A GB 2194954 A GB2194954 A GB 2194954A GB 803994 A GB803994 A GB 803994A
- Authority
- GB
- United Kingdom
- Prior art keywords
- rotor
- combustion chamber
- air
- combustion
- vanes
- 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
- 238000002485 combustion reaction Methods 0.000 abstract 14
- 239000007789 gas Substances 0.000 abstract 4
- 238000006243 chemical reaction Methods 0.000 abstract 1
- 239000000567 combustion gas Substances 0.000 abstract 1
- 238000001816 cooling Methods 0.000 abstract 1
- 238000007599 discharging Methods 0.000 abstract 1
- 239000000446 fuel Substances 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
- F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
- F02C3/14—Gas-turbine plants characterised by the use of combustion products as the working fluid characterised by the arrangement of the combustion chamber in the plant
- F02C3/16—Gas-turbine plants characterised by the use of combustion products as the working fluid characterised by the arrangement of the combustion chamber in the plant the combustion chambers being formed at least partly in the turbine rotor or in an other rotating part of the plant
- F02C3/165—Gas-turbine plants characterised by the use of combustion products as the working fluid characterised by the arrangement of the combustion chamber in the plant the combustion chambers being formed at least partly in the turbine rotor or in an other rotating part of the plant the combustion chamber contributes to the driving force by creating reactive thrust
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
803,994. Gas turbine plant. MORTON, P. P. H. Oct. 27, 1955 [July 27, 1954], No. 21949/54. Class 110 (3). A gas turbine power unit comprises two coaxial rotors, the first having a combustion chamber, or combustion chambers and the second having reaction surfaces on to which the products of combustion are directed, a centrifugal air compressor being provided to supply air under pressure to the combustion chamber or chambers. In Figs. 1 and 2, the rotor 1 is secured on a shaft 2 and is formed with an annular combustion chamber 4. Fuel is supplied to the chamber through passages 3, 3<SP>1</SP> and air is supplied between diffuser vanes 6 through openings 7. The combustion gases issue through nozzle guide vanes 12 and impinge on blades 11 carried by the turbine rotor 10 which is rotatably mounted on the shaft 3 and surrounds the combustion chamber rotor. The turbine rotor 10 is provided with two centrifugal-type air compressors 8, 9, one on either side of the rotor 1, air from the compressors discharging between the vanes 6 to the combustion chamber 4. The two rotors therefore rotate in opposite directions, power being supplied by the combustion chamber rotor through the shaft 2. In a second embodiment, Fig. 3, the combustion chamber rotor is in two parts 1, 1 disposed on either side of the bladed turbine rotor 10 and carries two annular combustion chambers 4, 4 which each receive air from between the diffuser vanes 6 through openings 7. Gases from the combustion chambers issue through nozzle guide vanes 12, 12 and impinge on the vanes 11 of the turbine rotor 10. The gases finally discharge through another set of vanes 14 carried by the combustion chamber rotor 1, 1. The turbine rotor 10 drives the centrifugal air compressors 8, 9 which are rotatably mounted therewith, the compressors supplying air to the two combustion chambers 4, 4. The combustion chamber rotor 1, 1 is secured on a shaft 2 and supplies power while the turbine rotor 10 and compressors 8, 9 are rotatably mounted on the shaft 2. The rotor discs 10 and turbine blades 11 may be hollow to permit flow of cooling air.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB2194954A GB803994A (en) | 1954-07-27 | 1954-07-27 | Improvements in power units of the gas turbine type |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB2194954A GB803994A (en) | 1954-07-27 | 1954-07-27 | Improvements in power units of the gas turbine type |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB803994A true GB803994A (en) | 1958-11-05 |
Family
ID=10171468
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB2194954A Expired GB803994A (en) | 1954-07-27 | 1954-07-27 | Improvements in power units of the gas turbine type |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB803994A (en) |
Cited By (16)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2385899A1 (en) * | 1977-03-29 | 1978-10-27 | Hedrick Lewis | Combined gas turbine and jet IC engine - has combustion chamber in rotor with exhaust producing reaction jet turning effect |
| WO1995005063A3 (en) * | 1993-08-08 | 1995-05-18 | Yanovsky Ilya Yakovlevich | Method of converting thermal energy to mechanical energy and a device for carrying out the same |
| US6145296A (en) * | 1998-09-25 | 2000-11-14 | Alm Development, Inc. | Gas turbine engine having counter rotating turbines and a controller for controlling the load driven by one of the turbines |
| US6189311B1 (en) | 1999-03-11 | 2001-02-20 | Alm Development, Inc. | Gas turbine engine |
| US6212871B1 (en) | 1999-03-11 | 2001-04-10 | Alm Development, Inc. | Method of operation of a gas turbine engine and a gas turbine engine |
| US6272844B1 (en) | 1999-03-11 | 2001-08-14 | Alm Development, Inc. | Gas turbine engine having a bladed disk |
| US6305157B1 (en) | 1998-09-25 | 2001-10-23 | Alm Development, Inc. | Gas turbine engine |
| US6363708B1 (en) | 1999-10-12 | 2002-04-02 | Alm Development, Inc. | Gas turbine engine |
| US6397576B1 (en) | 1999-10-12 | 2002-06-04 | Alm Development, Inc. | Gas turbine engine with exhaust compressor having outlet tap control |
| WO2002059469A1 (en) * | 2001-01-26 | 2002-08-01 | Academy Projects Limited | Turbine engine |
| US6442945B1 (en) | 2000-08-04 | 2002-09-03 | Alm Development, Inc. | Gas turbine engine |
| US6460343B1 (en) | 1998-09-25 | 2002-10-08 | Alm Development, Inc. | Gas turbine engine |
| US6460324B1 (en) | 1999-10-12 | 2002-10-08 | Alm Development, Inc. | Gas turbine engine |
| US6557337B1 (en) | 1998-09-25 | 2003-05-06 | Alm Development, Inc. | Gas turbine engine |
| WO2007129032A1 (en) * | 2006-05-05 | 2007-11-15 | Academy Projects Limited | Reaction turbine engine |
| GB2451704A (en) * | 2007-08-10 | 2009-02-11 | Keven Chappell | Gas turbine engine with compressor formed from a plurality of stacked surfaces |
-
1954
- 1954-07-27 GB GB2194954A patent/GB803994A/en not_active Expired
Cited By (16)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2385899A1 (en) * | 1977-03-29 | 1978-10-27 | Hedrick Lewis | Combined gas turbine and jet IC engine - has combustion chamber in rotor with exhaust producing reaction jet turning effect |
| WO1995005063A3 (en) * | 1993-08-08 | 1995-05-18 | Yanovsky Ilya Yakovlevich | Method of converting thermal energy to mechanical energy and a device for carrying out the same |
| US6460343B1 (en) | 1998-09-25 | 2002-10-08 | Alm Development, Inc. | Gas turbine engine |
| US6145296A (en) * | 1998-09-25 | 2000-11-14 | Alm Development, Inc. | Gas turbine engine having counter rotating turbines and a controller for controlling the load driven by one of the turbines |
| US6305157B1 (en) | 1998-09-25 | 2001-10-23 | Alm Development, Inc. | Gas turbine engine |
| US6557337B1 (en) | 1998-09-25 | 2003-05-06 | Alm Development, Inc. | Gas turbine engine |
| US6189311B1 (en) | 1999-03-11 | 2001-02-20 | Alm Development, Inc. | Gas turbine engine |
| US6212871B1 (en) | 1999-03-11 | 2001-04-10 | Alm Development, Inc. | Method of operation of a gas turbine engine and a gas turbine engine |
| US6272844B1 (en) | 1999-03-11 | 2001-08-14 | Alm Development, Inc. | Gas turbine engine having a bladed disk |
| US6397576B1 (en) | 1999-10-12 | 2002-06-04 | Alm Development, Inc. | Gas turbine engine with exhaust compressor having outlet tap control |
| US6460324B1 (en) | 1999-10-12 | 2002-10-08 | Alm Development, Inc. | Gas turbine engine |
| US6363708B1 (en) | 1999-10-12 | 2002-04-02 | Alm Development, Inc. | Gas turbine engine |
| US6442945B1 (en) | 2000-08-04 | 2002-09-03 | Alm Development, Inc. | Gas turbine engine |
| WO2002059469A1 (en) * | 2001-01-26 | 2002-08-01 | Academy Projects Limited | Turbine engine |
| WO2007129032A1 (en) * | 2006-05-05 | 2007-11-15 | Academy Projects Limited | Reaction turbine engine |
| GB2451704A (en) * | 2007-08-10 | 2009-02-11 | Keven Chappell | Gas turbine engine with compressor formed from a plurality of stacked surfaces |
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