GB424836A - Improvements in and relating to explosion turbines - Google Patents
Improvements in and relating to explosion turbinesInfo
- Publication number
- GB424836A GB424836A GB23387/33A GB2338733A GB424836A GB 424836 A GB424836 A GB 424836A GB 23387/33 A GB23387/33 A GB 23387/33A GB 2338733 A GB2338733 A GB 2338733A GB 424836 A GB424836 A GB 424836A
- Authority
- GB
- United Kingdom
- Prior art keywords
- chamber
- turbine
- discharge
- explosion
- supply channel
- 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
- F02C5/00—Gas-turbine plants characterised by the working fluid being generated by intermittent combustion
- F02C5/12—Gas-turbine plants characterised by the working fluid being generated by intermittent combustion the combustion chambers having inlet or outlet valves, e.g. Holzwarth gas-turbine plants
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Fluidized-Bed Combustion And Resonant Combustion (AREA)
Abstract
424,836. Gas turbines. HOLZWARTH, H., 7, Goethestrasse, D³sseldorf, Germany. Aug. 22, 1933, No. 23387. Convention date, Aug. 23, 1932. [Class 110 (iii)] An explosion gas turbine 24 with full peripheral admission has the nozzle ring fed from the discharge-valve end 6 of an explosion chamber 1 by an annular supply channel 21 and the geometrical extension of the cylindrical outer boundary of such supply channel 21 is substantially filled by such dischargevalve end 6 of the explosion chamber. The explosion chamber may be coaxial with the turbine as shown in Fig. 2 or may be arranged transversely, as shown in Figs. 5 and 6, with the chamber axis intersecting the turbine axis at right angles. Where only one transverse combustion chamber is provided, Fig. 5, the discharge valve 6 is coaxial with the turbine and is of such size that its peripheral edge lies near to the inner edge of the supply channel 21 ; if two combustion chambers are provided, Fig. 6, the valves are arranged parallel with the turbine axis and, if the two chambers discharge alternately, auxiliary valves 30 are added to permit scavenging of one chamber when its main valve 6 is closed during the discharge of the other chamber.
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| DE424836X | 1932-08-23 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB424836A true GB424836A (en) | 1935-02-22 |
Family
ID=6476963
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB23387/33A Expired GB424836A (en) | 1932-08-23 | 1933-08-22 | Improvements in and relating to explosion turbines |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB424836A (en) |
-
1933
- 1933-08-22 GB GB23387/33A patent/GB424836A/en not_active Expired
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