GB619259A - Improvements in or relating to driving gas turbine arrangements having a high efficiency at reduced loads - Google Patents
Improvements in or relating to driving gas turbine arrangements having a high efficiency at reduced loadsInfo
- Publication number
- GB619259A GB619259A GB35337/46A GB3533746A GB619259A GB 619259 A GB619259 A GB 619259A GB 35337/46 A GB35337/46 A GB 35337/46A GB 3533746 A GB3533746 A GB 3533746A GB 619259 A GB619259 A GB 619259A
- Authority
- GB
- United Kingdom
- Prior art keywords
- turbine
- compressor
- stages
- chambers
- pressure
- 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
- F02C3/36—Open cycles
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Supercharger (AREA)
Abstract
619,259. Gas turbine plant. SOC. RATEAU, and ANXIONNAZ, R. Nov. 28, 1946, No. 35337. Convention date, Jan. 25. [Class 110 (iii)] The two stages c<1>, c<2> of the air compressor are driven by two stages a<1>, a<2> of a turbine, the low-pressure stages being on one shaft and the high-pressure on another. The compressor turbine is arranged in gas parallel with a twostage useful power turbine m<1>, m<2>. Reheating chambers are provided between the stages of each turbine. The temperatures of the combustion chambers and reheating chambers are kept substantially equal. The total compression ratio of the air-compressor is eight. The heat-exchanger R for heating the air by the turbine exhaust has an efficiency of not less than 0.6. The compression ratio of the low-pressure compressor and the expansion ratio of the turbine stage which drives it are greater than the corresponding ratios of the high-pressure compressor and its turbine stage. In regulation, the fuel supply to the initial combustion chambers is reduced more rapidly than the fuel supply to the reheating chambers.
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| FR619259X | 1946-01-25 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB619259A true GB619259A (en) | 1949-03-07 |
Family
ID=8983546
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB35337/46A Expired GB619259A (en) | 1946-01-25 | 1946-11-28 | Improvements in or relating to driving gas turbine arrangements having a high efficiency at reduced loads |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB619259A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE956821C (en) * | 1951-12-24 | 1957-01-24 | Schilling Estate Company | Process for operating fire gases through deflagration producing propellant gas generators and device for carrying out the process |
-
1946
- 1946-11-28 GB GB35337/46A patent/GB619259A/en not_active Expired
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE956821C (en) * | 1951-12-24 | 1957-01-24 | Schilling Estate Company | Process for operating fire gases through deflagration producing propellant gas generators and device for carrying out the process |
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