GB461887A - Improvements relating to internal combustion turbines - Google Patents
Improvements relating to internal combustion turbinesInfo
- Publication number
- GB461887A GB461887A GB2110735A GB2110735A GB461887A GB 461887 A GB461887 A GB 461887A GB 2110735 A GB2110735 A GB 2110735A GB 2110735 A GB2110735 A GB 2110735A GB 461887 A GB461887 A GB 461887A
- Authority
- GB
- United Kingdom
- Prior art keywords
- turbine
- compresser
- turbines
- stage
- fitted
- 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
- F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
- F02C3/08—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising at least one radial stage
Abstract
461,887. Gas turbines; centrifugal pumps. WHITTLE, F. July 25, 1935, No. 21107. [Classes 110 (i) and 110 (iii)] In an internal-combustion turbine working on a constant pressure cycle, compression is effected by a two-stage compresser of the kind described in Specification 456,976 and made up of two first stage units 10 and 11 fitted with double inlet impellers, each supplying one intake of a second stage, double inlet centrifugal compresser 20. The units 10 and 11 are placed on either side of the unit 20 and are driven through a single shaft by the turbines 29 at each end. Compressed air from the volute 25 is taken to a helical combustion chamber 26 fitted with a fuel burner and then passes to the volute chamber 27 through turbine 29, exhausting into conduit 30. Water jackets 31 and 32 are used to cool the bearings and faces of the turbine rotor. The excess output of compresser unit 20 is delivered into another combustion chamber 35 of an independent turbine. The working fluid may pass through two or more turbines in succession or through a turbine having two oppositely rotating wheels, one delivering useful power and the other driving the compresser.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB2110735A GB461887A (en) | 1935-07-25 | 1935-07-25 | Improvements relating to internal combustion turbines |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB2110735A GB461887A (en) | 1935-07-25 | 1935-07-25 | Improvements relating to internal combustion turbines |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB461887A true GB461887A (en) | 1937-02-25 |
Family
ID=10157341
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB2110735A Expired GB461887A (en) | 1935-07-25 | 1935-07-25 | Improvements relating to internal combustion turbines |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB461887A (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2445114A (en) * | 1948-07-13 | Arrangement of jet propulsion | ||
| DE873632C (en) * | 1942-04-05 | 1953-04-16 | Ernst Heinkel A G Zweigniederl | Multi-flow compressor system for gas turbines of all kinds |
| US2715814A (en) * | 1949-03-25 | 1955-08-23 | Centrax Power Units Ltd | Fuel-flow for plural radial inwardflow gas turbines |
| US2937496A (en) * | 1955-01-25 | 1960-05-24 | Caillette Georges | Jet propelling unit |
| FR2413551A1 (en) * | 1978-01-03 | 1979-07-27 | Thomassen Holland Bv | GAS TURBINE INSTALLATION |
| CN103673371A (en) * | 2013-12-13 | 2014-03-26 | 中国航空工业集团公司金城南京机电液压工程研究中心 | Four-wheel-coaxial two-level expansion turbine cooler |
-
1935
- 1935-07-25 GB GB2110735A patent/GB461887A/en not_active Expired
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2445114A (en) * | 1948-07-13 | Arrangement of jet propulsion | ||
| DE873632C (en) * | 1942-04-05 | 1953-04-16 | Ernst Heinkel A G Zweigniederl | Multi-flow compressor system for gas turbines of all kinds |
| US2715814A (en) * | 1949-03-25 | 1955-08-23 | Centrax Power Units Ltd | Fuel-flow for plural radial inwardflow gas turbines |
| US2937496A (en) * | 1955-01-25 | 1960-05-24 | Caillette Georges | Jet propelling unit |
| FR2413551A1 (en) * | 1978-01-03 | 1979-07-27 | Thomassen Holland Bv | GAS TURBINE INSTALLATION |
| CN103673371A (en) * | 2013-12-13 | 2014-03-26 | 中国航空工业集团公司金城南京机电液压工程研究中心 | Four-wheel-coaxial two-level expansion turbine cooler |
| CN103673371B (en) * | 2013-12-13 | 2016-07-06 | 中国航空工业集团公司金城南京机电液压工程研究中心 | A kind of cooling turbine unit of the coaxial double expansion of four-wheel |
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