GB590634A - Improvements in or relating to gas turbines - Google Patents
Improvements in or relating to gas turbinesInfo
- Publication number
- GB590634A GB590634A GB174347A GB174347A GB590634A GB 590634 A GB590634 A GB 590634A GB 174347 A GB174347 A GB 174347A GB 174347 A GB174347 A GB 174347A GB 590634 A GB590634 A GB 590634A
- Authority
- GB
- United Kingdom
- Prior art keywords
- rotor
- compressor
- blades
- combustion chamber
- gas
- 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
- F02C3/14—Gas-turbine plants characterised by the use of combustion products as the working fluid characterised by the arrangement of the combustion chamber in the plant
- F02C3/16—Gas-turbine plants characterised by the use of combustion products as the working fluid characterised by the arrangement of the combustion chamber in the plant the combustion chambers being formed at least partly in the turbine rotor or in an other rotating part of the plant
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
590,634. Gas turbines. LOMAX, F. Jan. 29, 1945, No. 1743/47. Divided out of Complete Specification of 590,591. [Class 110 (iii)] In a gas turbine plant comprising a compressor 3, a combustion chamber 6 and a turbine rotor 5 which drives the compressor rotor, the exhaust products being used for jet propulsion, the rotor 5 is hollow with the central space forming part of the combustion chamber. The compressor may be of the axial-flow or another type. The rotor 5 has a number of radial outlets 11 which are spirally curved to give driving torque to the rotor and the gases pass through blades on a rotor 4, and intermediate fixed guide blades, before being exhausted through a jet 12. Fuel is supplied through nozzles 7. The rotor 4 may be omitted and blades may be affixed to the periphery of the rotor 5 and coact with stationary guide blades attached to the casing wall. The gas flow through the rotor 5 may be reversed.
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB590634A true GB590634A (en) | 1947-07-23 |
Family
ID=1626958
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB174347A Expired GB590634A (en) | 1945-01-29 | Improvements in or relating to gas turbines |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB590634A (en) |
-
1945
- 1945-01-29 GB GB174347A patent/GB590634A/en not_active Expired
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