GB518767A - Regulation of constant pressure gas turbine installations particularly for the propulsion of ships - Google Patents
Regulation of constant pressure gas turbine installations particularly for the propulsion of shipsInfo
- Publication number
- GB518767A GB518767A GB25092/38A GB2509238A GB518767A GB 518767 A GB518767 A GB 518767A GB 25092/38 A GB25092/38 A GB 25092/38A GB 2509238 A GB2509238 A GB 2509238A GB 518767 A GB518767 A GB 518767A
- Authority
- GB
- United Kingdom
- Prior art keywords
- turbine
- compressor
- increase
- gas temperature
- 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
Landscapes
- Control Of Positive-Displacement Air Blowers (AREA)
Abstract
518,767. Gas turbines; servo-motors. AKT.-GES. BROWN, BOVERI, & CIE. Aug. 26, 1938, No. 25092. Convention date, Sept. 24, 1937. [Class 110 (iii)] [Also in Group XXIX] In a gas turbine plant, the power distribution between the compressor turbine 4 and the useful power turbine 5 is regulated by means of angularly adjustable guide blades 11 provided in at least the initial'stages of the compressor turbine. Similar blades may be used in the effective power turbine also, or a simple throttle valve 13 may be provided. A regulator, 8, 9, 12 maintains the gas temperature leaving the combustion chamber 2 constant and at such a level that the output of the turbine 4 equals the input to the compressor irrespective of the air inlet temperature. If the gas temperature increases or decreases, the thermostat 8 will, by 'acting on the guide blades 11 by means of the leak-off 9 and servomotor 10, adjust the air supply to restore the balance. If the compressor air inlet temperature falls, the air delivered by the compressor will be in excess and the gas temperature will fall. The thermostat responds and closes the guide blades of the. compressor turbine and so reduces the power developed for compression. An adjustable regulator 16 acting on the piston 17a can temporarily increase the ratio of fuel to air and thereby increase the gas temperature leaving the combustion chamber. The increase in gas temperature is followed by an increase-in the speed of the compressor turbine, a lowering of the temperature in the combustion chamber, and an increase in the pressure, therein. This increase in pressure increases the output of the effective power turbine. A motor 24 is used for starting purposes. A bye-pass valve 18 is controlled by an emergency governor 19.
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| DE518767X | 1937-09-24 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB518767A true GB518767A (en) | 1940-03-07 |
Family
ID=6550203
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB25092/38A Expired GB518767A (en) | 1937-09-24 | 1938-08-26 | Regulation of constant pressure gas turbine installations particularly for the propulsion of ships |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB518767A (en) |
-
1938
- 1938-08-26 GB GB25092/38A patent/GB518767A/en not_active Expired
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