GB1079264A - - Google Patents
Info
- Publication number
- GB1079264A GB1079264A GB1079264DA GB1079264A GB 1079264 A GB1079264 A GB 1079264A GB 1079264D A GB1079264D A GB 1079264DA GB 1079264 A GB1079264 A GB 1079264A
- Authority
- GB
- United Kingdom
- Prior art keywords
- turbine
- rotor
- rotors
- gearing
- ducted fan
- 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.)
- Active
Links
Landscapes
- Control Of Turbines (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
1,079,264. Gas turbine ducted fan engines. BRISTOL SIDDELEY ENGINES Ltd. June 27, 1966 [June 28, 1965], No. 27327/65. Headings F1J and F1T. The invention relates to gas turbine ducted fan jet engines which comprise in series flow compressor, combustion equipment, a first turbine connected to drive the compressor, a second turbine and a third turbine, the second and third turbines being interconnected by gearing so as to determine the relative speeds thereof, a ducted fan being connected to the second or third turbine rotor. In the embodiment shown in Fig. 1 the turbine 1 drives the compressor (not shown) and the gases from the turbine 1 pass through duct 2 to drive the second turbine 5 and the third turbine 7, the gases then discharging through nozzle 8. The turbine 7 is connected to drive the ducted fan blade assembly by means of a frustoconical ring 7A. The turbine rotors 5 and 7 are interconnected by gearing disposed within casing 14 located forwardly of the turbine rotors 5 and 7, the gearing interconnecting the rotors for contrarotation and so that the rotational speed.of the rotor 5 is greater than that of the rotor 7. The shaft 12 of the rotor 5 carries a gear 15 with which engage a plurality of intermediate pinions 16 which in turn engage with an internal ring gear 17 carried by the shaft 13 of the turbine rotor 7. In Fig. 2 (not shown) the gearing 39, 41, 40 interconnecting the turbine rotors 22, 23 is disposed within a casing 31 located downstream of the turbine rotors and within the inner wall of the propulsion nozzle 25.
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB1079264A true GB1079264A (en) |
Family
ID=1758718
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB1079264D Active GB1079264A (en) |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB1079264A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2129502A (en) * | 1982-11-01 | 1984-05-16 | Gen Electric | Counter rotation power turbine |
| US4815273A (en) * | 1985-12-31 | 1989-03-28 | Peter Rudolph | Single propeller turboprop propulsion apparatus |
| GB2230821A (en) * | 1989-04-11 | 1990-10-31 | Gen Electric | Aircraft propulsion system |
| US5079916A (en) * | 1982-11-01 | 1992-01-14 | General Electric Company | Counter rotation power turbine |
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0
- GB GB1079264D patent/GB1079264A/en active Active
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 |
| 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 |
| US4815273A (en) * | 1985-12-31 | 1989-03-28 | Peter Rudolph | Single propeller turboprop propulsion apparatus |
| GB2230821A (en) * | 1989-04-11 | 1990-10-31 | Gen Electric | Aircraft propulsion system |
| US5112191A (en) * | 1989-04-11 | 1992-05-12 | General Electric Company | Rotating cowling |
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