GB765915A - Turbo-propeller jet propulsion motors - Google Patents
Turbo-propeller jet propulsion motorsInfo
- Publication number
- GB765915A GB765915A GB17830/56A GB1783056A GB765915A GB 765915 A GB765915 A GB 765915A GB 17830/56 A GB17830/56 A GB 17830/56A GB 1783056 A GB1783056 A GB 1783056A GB 765915 A GB765915 A GB 765915A
- Authority
- GB
- United Kingdom
- Prior art keywords
- shaft
- vanes
- disc
- discs
- cover
- 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
- F02C3/06—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising only axial stages
- F02C3/067—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising only axial stages having counter-rotating rotors
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
765,915. Gas turbine engines; axial-flow compressors. BUCHI, A. May 6, 1953 [May 6, 1952], No. 17830/56. Divided out of 765,913. Classes 110 (1) and 110 (3). A gas turbine propeller engine comprises two contra-rotating turbine rotors 1, 30 each of which drives a set of vanes of a contra-rotating compressor. The low-pressure turbine rotor 30 is mounted on a shaft 32 and has two blade stages 311, 31 with a set of fixed blades 312 therebetween. Compressor rotor discs 175, 174, 173, 172, 171 and 17 are mounted on the shaft 32 and sets of vanes 155, 154, 153, 152, 151 and 15 are carried by the discs. The shaft 32 is mounted in bearings 6, 36. The high-pressure turbine rotor disc 1 is mounted on a hollow shaft 8 and has two blade stages 2<SP>1</SP>, 2 with a set of fixed blades 222 therebetween. A compressor rotor disc 9 is secured to the shaft 8 and carries vanes 14 and a screwed cover ring 16. The ring 16 is connected to a screwed cover ring 161 which in turn is connected to further cover rings 162, 163, 164, 165, 166, the cover rings carrying vanes 141, 142, 143, 144, 145, 146 and discs 91 to 96, the hubs of which are disposed close to the hubs of the discs mounted on the inner shaft 32. The screwed cover rings 16, 161, 162, 163, 164, 165, 166 together form a drum, the vane rows 141, 142, 143, 144, 145 being located midway of the respective cover rings and each cover ring is of such a width that the ends thereof surround the tips of the contrarotating vanes on either side of the vanes carried by the cover ring. The adjacent cover rings overlap each other axially and the overlapping parts are in screwed engagement. The hollow shaft 8 is mounted in bearings 5, 5<SP>1</SP> and the disc 96 at the inlet end of the drum is mounted in a bearing 21 located in the fixed disc 18 which carries inlet guide vanes 19. The bearing 36 is formed within the hub of the disc 96. The combustion equipment is indicated at C and the jet propulsion nozzle at D. A propeller 24 is driven from the shaft 32 by means of gearing 22, 23. A second embodiment is described having fewer compressor, stages, and having two contra-rotating propellers one driven through gearing from the inner shaft 32 and the other through gearing from the outer shaft 8.
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CH765915X | 1952-05-06 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB765915A true GB765915A (en) | 1957-01-16 |
Family
ID=4535031
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB17830/56A Expired GB765915A (en) | 1952-05-06 | 1953-05-06 | Turbo-propeller jet propulsion motors |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB765915A (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2129502A (en) * | 1982-11-01 | 1984-05-16 | Gen Electric | Counter rotation power turbine |
| US4790133A (en) * | 1986-08-29 | 1988-12-13 | General Electric Company | High bypass ratio counterrotating turbofan engine |
| US4860537A (en) * | 1986-08-29 | 1989-08-29 | Brandt, Inc. | High bypass ratio counterrotating gearless front fan engine |
| US5079916A (en) * | 1982-11-01 | 1992-01-14 | General Electric Company | Counter rotation power turbine |
| US7451592B2 (en) | 2004-03-19 | 2008-11-18 | Rolls-Royce Plc | Counter-rotating turbine engine including a gearbox |
| CN105134380A (en) * | 2015-10-16 | 2015-12-09 | 常胜 | Forward and reverse rotating centrifugal turbine engine |
-
1953
- 1953-05-06 GB GB17830/56A patent/GB765915A/en not_active Expired
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2129502A (en) * | 1982-11-01 | 1984-05-16 | Gen Electric | Counter rotation power turbine |
| GB2129502B (en) * | 1982-11-01 | 1989-10-18 | Gen Electric | Aircraft engine having a counter rotation power turbine |
| US5079916A (en) * | 1982-11-01 | 1992-01-14 | General Electric Company | Counter rotation power turbine |
| US4790133A (en) * | 1986-08-29 | 1988-12-13 | General Electric Company | High bypass ratio counterrotating turbofan engine |
| US4860537A (en) * | 1986-08-29 | 1989-08-29 | Brandt, Inc. | High bypass ratio counterrotating gearless front fan engine |
| US7451592B2 (en) | 2004-03-19 | 2008-11-18 | Rolls-Royce Plc | Counter-rotating turbine engine including a gearbox |
| CN105134380A (en) * | 2015-10-16 | 2015-12-09 | 常胜 | Forward and reverse rotating centrifugal turbine engine |
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