GB817931A - Improvements in the control of gas turbine plants - Google Patents
Improvements in the control of gas turbine plantsInfo
- Publication number
- GB817931A GB817931A GB33711/55A GB3371155A GB817931A GB 817931 A GB817931 A GB 817931A GB 33711/55 A GB33711/55 A GB 33711/55A GB 3371155 A GB3371155 A GB 3371155A GB 817931 A GB817931 A GB 817931A
- Authority
- GB
- United Kingdom
- Prior art keywords
- valve
- valves
- gas turbine
- combustion
- fuel
- 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
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
- F23R3/26—Controlling the air flow
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
- F05B2250/00—Geometry
- F05B2250/40—Movement of component
- F05B2250/41—Movement of component with one degree of freedom
Abstract
817,931. Gas turbine plant. BROWN. BOVERI & CO. A.G. Nov. 24, 1955 [Dec. 18, 1.954], No. 33711/55. Class 110 (3). [Also in Group XII] An automatic control system for the combustion chamber of a gas turbine plant comprising a first, a second and a third valve which control the flow of air to the combustion zone, cooling zone and mixing zone respectively has each of the valves actuated by a regulating impulse which also controls the fuel supply to the combustion. chamber. A gas turbine combustion chamber 1 has a flame tube 2 which encloses a combustion space 2<SP>1</SP> and a mixing space 2<SP>11</SP>. Air enters the combustion chamber at 3 and 4 is the gas outlet. Fuel is supplied to the chamber by a nozzle 5 regulated by a power piston 6 which actuates a fuel valve 6<SP>1</SP>. A thr6ttle 7 which regulates the primary air supply and a valve 8 which controls the amount of cooling air passed to the mixing space 2<SP>11</SP>, are regulated by a power piston 9. A valve 10 controls the secondary air supply to the mixing space 2<SP>11</SP> and is controlled by a power piston 11. A retarding or accelerating control is formed by the accumulator 12, throttle 12<SP>1</SP> and compensating power piston 12<SP>11</SP>. When the power demand increases the pressure in the pipe 13 rises and this causes the fuel nozzle 5 and valves 7 and 8 to move in the opening direction and the valve 10 to be moved in the closing direction. The valves 7 and 8 are opened to a greater extent than is desirable for stable running condition. This assists the acceleration of the engine. After a period of time under steady running determined by the setting of the throttle 12<SP>1</SP> the pressure acting on the piston 12<SP>11</SP> becomes equal to that in the pipe 13 and then the valves 7 and 8 are closed a little.
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CH817931X | 1954-12-18 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB817931A true GB817931A (en) | 1959-08-06 |
Family
ID=4539127
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB33711/55A Expired GB817931A (en) | 1954-12-18 | 1955-11-24 | Improvements in the control of gas turbine plants |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB817931A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2133832A1 (en) * | 1971-04-15 | 1972-12-01 | United Aircraft Canada | |
| US3975900A (en) * | 1972-02-18 | 1976-08-24 | Engelhard Minerals & Chemicals Corporation | Method and apparatus for turbine system combustor temperature |
| GB2136553A (en) * | 1983-03-11 | 1984-09-19 | British Gas Corp | Burner |
| CN111363910A (en) * | 2020-03-03 | 2020-07-03 | 首钢京唐钢铁联合有限责任公司 | Pulse type burner heating output control method and system |
-
1955
- 1955-11-24 GB GB33711/55A patent/GB817931A/en not_active Expired
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2133832A1 (en) * | 1971-04-15 | 1972-12-01 | United Aircraft Canada | |
| US3975900A (en) * | 1972-02-18 | 1976-08-24 | Engelhard Minerals & Chemicals Corporation | Method and apparatus for turbine system combustor temperature |
| GB2136553A (en) * | 1983-03-11 | 1984-09-19 | British Gas Corp | Burner |
| CN111363910A (en) * | 2020-03-03 | 2020-07-03 | 首钢京唐钢铁联合有限责任公司 | Pulse type burner heating output control method and system |
| CN111363910B (en) * | 2020-03-03 | 2021-11-19 | 首钢京唐钢铁联合有限责任公司 | Pulse type burner heating output control method and system |
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