GB368317A - Improvements in or relating to turbines - Google Patents
Improvements in or relating to turbinesInfo
- Publication number
- GB368317A GB368317A GB33154/30A GB3315430A GB368317A GB 368317 A GB368317 A GB 368317A GB 33154/30 A GB33154/30 A GB 33154/30A GB 3315430 A GB3315430 A GB 3315430A GB 368317 A GB368317 A GB 368317A
- Authority
- GB
- United Kingdom
- Prior art keywords
- turbine
- driving
- turbines
- compressors
- driven
- 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)
- Engine Equipment That Uses Special Cycles (AREA)
Abstract
368,317. Gas turbine plant. AKTIEBOLAGET MILO, 17, Võstra Tradgardsgatan, Stockholm. Nov. 4, 1930, No. 33154. Convention date, March 24. [Class 110 (iii).] Relates to gas turbine plant in which the power-producing turbines are not mechanically connected with the turbines which drive the compressors for the combustion air, and consists in arranging that the low-pressure compressor is driven by a gas turbine working against the lowest pressure. In Fig. 1 air taken in at 6 passes in series through compressors 4, 5 driven by a double-rotary turbine 1. The air, which may be cooled by fins 7, is passed to a combustion chamber 13, and the gases therein produced are divided between the turbine 1 driving the compressors, and the turbine 16 driving the generators 21, by pipes 31, 32. In Fig. 2 the turbine 6 driving the low-pressure compressors 4, 5 is driven by the exhaust from the turbine 16 driving the generators 21, 22. A high-pressure compressor 24 driven by a high-pressure turbine 25 is provided. The exhaust from this turbine drives the turbine 16. A number of modifications are described in which the turbines driving the compressors and those producing power are coupled in series or in parallel, or some in series and some in parallel. In Fig. 8 the air passes in series through compressors 108, 110, 91, driven by turbines 125, 116, 90, to a preheater 128 through which the final exhaust passes. A pipe 130 leads it to a combustion chamber 93. The path of the gases therein produced is by turbine 90 and reheater 112 to the turbines 95, 104 driving the generator 96. A reheater is provided at 114. The gases then pass through a reheater 117, turbine 116, and reheater 120 to one of the turbines 119 driving a generator 120a. The exhaust from this turbine is divided between the turbine 125 and the turbine 124 which is coupled to the generator 120a. Water may be injected into the primary combustion chamber. Specifications 368,318 and 368,319 are referred to.
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| DE368317X | 1930-03-24 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB368317A true GB368317A (en) | 1932-03-04 |
Family
ID=6318063
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB33154/30A Expired GB368317A (en) | 1930-03-24 | 1930-11-04 | Improvements in or relating to turbines |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB368317A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2457594A (en) * | 1942-05-14 | 1948-12-28 | Nettel Frederick | Turbine compressor plant |
| US2473356A (en) * | 1942-04-18 | 1949-06-14 | Turbo Engineering Corp | Combustion gas turbine arrangement |
| US2540991A (en) * | 1942-03-06 | 1951-02-06 | Lockheed Aircraft Corp | Gas reaction aircraft power plant |
| US2646663A (en) * | 1949-08-31 | 1953-07-28 | Rateau Soc | Semiopen circuit gas-turbine engine |
-
1930
- 1930-11-04 GB GB33154/30A patent/GB368317A/en not_active Expired
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2540991A (en) * | 1942-03-06 | 1951-02-06 | Lockheed Aircraft Corp | Gas reaction aircraft power plant |
| US2473356A (en) * | 1942-04-18 | 1949-06-14 | Turbo Engineering Corp | Combustion gas turbine arrangement |
| US2457594A (en) * | 1942-05-14 | 1948-12-28 | Nettel Frederick | Turbine compressor plant |
| US2646663A (en) * | 1949-08-31 | 1953-07-28 | Rateau Soc | Semiopen circuit gas-turbine engine |
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