GB765270A - Gas turbine plants - Google Patents
Gas turbine plantsInfo
- Publication number
- GB765270A GB765270A GB5494/55A GB549455A GB765270A GB 765270 A GB765270 A GB 765270A GB 5494/55 A GB5494/55 A GB 5494/55A GB 549455 A GB549455 A GB 549455A GB 765270 A GB765270 A GB 765270A
- Authority
- GB
- United Kingdom
- Prior art keywords
- turbine
- fuel
- air
- compressor
- calorific value
- 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
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
- F02C3/20—Gas-turbine plants characterised by the use of combustion products as the working fluid using a special fuel, oxidant, or dilution fluid to generate the combustion products
- F02C3/22—Gas-turbine plants characterised by the use of combustion products as the working fluid using a special fuel, oxidant, or dilution fluid to generate the combustion products the fuel or oxidant being gaseous at standard temperature and pressure
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
765,270. Gas turbine plant; axial-flow compressors. SULZER FRERES SOC. ANON. Feb. 23, 1955 [March 6, 1954], No. 5494/55. Classes 110 (1) and 110 (3). In a gas turbine plant using a gaseous fuel of low calorific value, a fuel of higher calorific value and additional air are supplied to the combustion chamber when there is a deficiency in the supply of fuel gas of low calorific value. The additional air and fuel supply are adjusted so that the temperature and pressure at the turbine inlet remain constant. In the plant shown, the turbine 5 drives the air compressor 1 and the fuel gas compressor 4. The compressed air passes through a preheater 2, coupled to the turbine exhaust, before entering the combustion chamber 3. Fuel of higher calorific value may be supplied through a pipe 12 and valve 11 and the air compressor, Fig. 2, is provided with variable guide blades 16 operable by a lever 17 so that the volume of air supplied may be varied. A return pipe 8 around the compressor 4 is fitted with a valve 9 and cooler 10. This may be brought into operation to prevent surging when the fuel gas supply is deficient. The compressor 4 may also be fitted with adjustable blades. The plant may consist of several turbine sets, the fuel gas and air compressors for all the sets being driven by a particular turbine. The combustion air compressor may consist of a number of units, only one of which is adjustable.
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CH765270X | 1954-03-06 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB765270A true GB765270A (en) | 1957-01-09 |
Family
ID=4534991
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB5494/55A Expired GB765270A (en) | 1954-03-06 | 1955-02-23 | Gas turbine plants |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB765270A (en) |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5329757A (en) * | 1993-05-12 | 1994-07-19 | Gas Research Institute | Turbocharger-based bleed-air driven fuel gas booster system and method |
| GB2291682A (en) * | 1993-06-23 | 1996-01-31 | Shell Int Research | Gas turbine using low-btu fuel |
| US5488823A (en) * | 1993-05-12 | 1996-02-06 | Gas Research Institute | Turbocharger-based bleed-air driven fuel gas booster system and method |
| FR2783014A1 (en) * | 1998-09-04 | 2000-03-10 | Toshiba Kk | Energy-producing turbine system with reformer and fuel and oxidant compressors |
| WO2001092702A1 (en) * | 2000-05-30 | 2001-12-06 | Turbec Ab | Integrated gas compressor |
| EP1528237A2 (en) * | 2003-10-30 | 2005-05-04 | Hitachi, Ltd. | Gas-turbine power generating installation and method of operating the same |
| CN111878234A (en) * | 2020-08-11 | 2020-11-03 | 新奥能源动力科技（上海）有限公司 | Gas turbine system |
-
1955
- 1955-02-23 GB GB5494/55A patent/GB765270A/en not_active Expired
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5329757A (en) * | 1993-05-12 | 1994-07-19 | Gas Research Institute | Turbocharger-based bleed-air driven fuel gas booster system and method |
| US5488823A (en) * | 1993-05-12 | 1996-02-06 | Gas Research Institute | Turbocharger-based bleed-air driven fuel gas booster system and method |
| GB2291682A (en) * | 1993-06-23 | 1996-01-31 | Shell Int Research | Gas turbine using low-btu fuel |
| FR2783014A1 (en) * | 1998-09-04 | 2000-03-10 | Toshiba Kk | Energy-producing turbine system with reformer and fuel and oxidant compressors |
| WO2001092702A1 (en) * | 2000-05-30 | 2001-12-06 | Turbec Ab | Integrated gas compressor |
| EP1528237A2 (en) * | 2003-10-30 | 2005-05-04 | Hitachi, Ltd. | Gas-turbine power generating installation and method of operating the same |
| EP1528237A3 (en) * | 2003-10-30 | 2012-04-11 | Hitachi, Ltd. | Gas-turbine power generating installation and method of operating the same |
| CN111878234A (en) * | 2020-08-11 | 2020-11-03 | 新奥能源动力科技（上海）有限公司 | Gas turbine system |
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