GB514620A - Improvements in or relating to gas turbine plant - Google Patents
Improvements in or relating to gas turbine plantInfo
- Publication number
- GB514620A GB514620A GB4400/38A GB440038A GB514620A GB 514620 A GB514620 A GB 514620A GB 4400/38 A GB4400/38 A GB 4400/38A GB 440038 A GB440038 A GB 440038A GB 514620 A GB514620 A GB 514620A
- Authority
- GB
- United Kingdom
- Prior art keywords
- turbine
- compressor
- air
- combustion
- fuel
- 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 6
- 239000007789 gas Substances 0.000 abstract 5
- 239000000446 fuel Substances 0.000 abstract 4
- 230000001419 dependent effect Effects 0.000 abstract 1
- 238000010438 heat treatment Methods 0.000 abstract 1
- 230000000737 periodic effect Effects 0.000 abstract 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
- F23R3/52—Toroidal combustion chambers
-
- 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
- F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use
- F02C6/003—Gas-turbine plants with heaters between turbine stages
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
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
514,620. Gas turbines; air-compressors. JENDRASSIK, ,G. Feb. 11, 1938, No. 4400. Convention date, Feb. 13, 1937. [Classes 110 (i) and 110 (iii)] In a continuous combustion, constant pressure gas turbine, the walls of the combustion chamber are spaced from the turbine casing walls, additional heat is given to the gases during expansion either by prolonging the combustion into the turbine bladings or by burning additional fuel between the stages and the last stage without such re-heating covers a pressure drop of not less than one twentieth of the total. The additional heat may produce isothermal expansion. The combustion chamber 15 is annular and co-axial with the turbine. It may be arranged externally to the gas flow, as shown, or internally. The wall 13 has a scoop 16 by which a part of the air delivered by the compressor on the left is caused to swirl into the combustion chamber. The rest passes the chamber by and mixes with the products of combustion before they enter the turbine on the right. The innermost layer of air in the compressor is extracted through ports 28, 28<1> and returned to an earlier stage of the compressor. The rotor may be cooled by air passing through ports 31. This air may be taken from the delivery of the compressor and, after passing through the rotor cavities, be mixed with the hot gases entering the turbine blading. Fuel is supplied by a pump 22 and, to avoid a periodic delivery, balancing chambers 23 may be provided. Fig. 7 shows a fuel atomizer. The pressure of the fuel in the chamber 39 is dependent upon a spring 40 which can be adjusted by a screw 41. The turbine may have a low-pressure stage of increased diameter and driving a power consumer such as an aircraft propeller by a shaft passing through the main turbine and compressor rotor. The compressor-may also have an initial stage of increased diameter carried by the same shaft. The main turbine and compressor rotor is connected by gearing to the shaft and the arrangement is such that normally the gearing runs under no load.
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| HU514620X | 1937-02-13 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB514620A true GB514620A (en) | 1939-11-14 |
Family
ID=10979438
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB4400/38A Expired GB514620A (en) | 1937-02-13 | 1938-02-11 | Improvements in or relating to gas turbine plant |
Country Status (2)
| Country | Link |
|---|---|
| FR (1) | FR833521A (en) |
| GB (1) | GB514620A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0870990A1 (en) * | 1997-03-20 | 1998-10-14 | Asea Brown Boveri AG | Gas turbine with toroidal combustor |
| CN102325978A (en) * | 2009-02-24 | 2012-01-18 | 欧洲涡轮机公司 | Method of operating gas turbine power plant and gas turbine power plant |
| US10072572B2 (en) | 2014-04-09 | 2018-09-11 | Rolls-Royce Plc | Gas turbine engine |
-
1938
- 1938-02-11 GB GB4400/38A patent/GB514620A/en not_active Expired
- 1938-02-11 FR FR833521D patent/FR833521A/en not_active Expired
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0870990A1 (en) * | 1997-03-20 | 1998-10-14 | Asea Brown Boveri AG | Gas turbine with toroidal combustor |
| US6192669B1 (en) | 1997-03-20 | 2001-02-27 | Asea Brown Boveri Ag | Combustion chamber of a gas turbine |
| CN102325978A (en) * | 2009-02-24 | 2012-01-18 | 欧洲涡轮机公司 | Method of operating gas turbine power plant and gas turbine power plant |
| US10072572B2 (en) | 2014-04-09 | 2018-09-11 | Rolls-Royce Plc | Gas turbine engine |
Also Published As
| Publication number | Publication date |
|---|---|
| FR833521A (en) | 1938-10-24 |
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