GB800222A - Improvements in and relating to gas turbine engines - Google Patents
Improvements in and relating to gas turbine enginesInfo
- Publication number
- GB800222A GB800222A GB57255A GB57255A GB800222A GB 800222 A GB800222 A GB 800222A GB 57255 A GB57255 A GB 57255A GB 57255 A GB57255 A GB 57255A GB 800222 A GB800222 A GB 800222A
- Authority
- GB
- United Kingdom
- Prior art keywords
- fuel
- gas turbine
- annular
- led
- air
- 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
- 239000000446 fuel Substances 0.000 abstract 4
- 238000002485 combustion reaction Methods 0.000 abstract 2
- 150000001875 compounds Chemical class 0.000 abstract 1
- 239000010409 thin film Substances 0.000 abstract 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K7/00—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof
- F02K7/005—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof the engine comprising a rotor rotating under the actions of jets issuing from this rotor
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Rolling Contact Bearings (AREA)
Abstract
800,222. Vapour burners. WESTLAND AIRCRAFT, Ltd. March 29, 1956 [Jan. 7, 1955], No. 572/55. Class 75(1) [Also in Groups XII and XXVI] Air from the high pressure compressor 13 of a compound gas turbine passes through an axial diffuser 12 to a bifurcated annular passage 14. One part of this air is led to the forward end of the annular combustion chamber 17 in the vicinity of the fuel slinger ring 15. Fuel Supplied through conduits 24, 27 is led through passages 23, 28 and the bearings 25, 29, -which it lubricates, to an annular chamber 34. The fuel then flows along the inner surface 36 of the combustion chamber in a thin film and becomes preheated and partially vaporizes. The fuel then passes through holes 35 on to the slinger ring 15. Specification 795,669 [Group XXXIV] is referred to.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB57255A GB800222A (en) | 1955-01-07 | 1955-01-07 | Improvements in and relating to gas turbine engines |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB57255A GB800222A (en) | 1955-01-07 | 1955-01-07 | Improvements in and relating to gas turbine engines |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB800222A true GB800222A (en) | 1958-08-20 |
Family
ID=9706730
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB57255A Expired GB800222A (en) | 1955-01-07 | 1955-01-07 | Improvements in and relating to gas turbine engines |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB800222A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3299961A (en) * | 1964-06-08 | 1967-01-24 | Rolls Royce | Helicopter rotor |
-
1955
- 1955-01-07 GB GB57255A patent/GB800222A/en not_active Expired
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3299961A (en) * | 1964-06-08 | 1967-01-24 | Rolls Royce | Helicopter rotor |
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