GB838323A - Improvements in automatic control systems - Google Patents
Improvements in automatic control systemsInfo
- Publication number
- GB838323A GB838323A GB3344957A GB3344957A GB838323A GB 838323 A GB838323 A GB 838323A GB 3344957 A GB3344957 A GB 3344957A GB 3344957 A GB3344957 A GB 3344957A GB 838323 A GB838323 A GB 838323A
- Authority
- GB
- United Kingdom
- Prior art keywords
- signal
- turbine
- comparator
- demanded
- fed
- 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
-
- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05B—CONTROL OR REGULATING SYSTEMS IN GENERAL; FUNCTIONAL ELEMENTS OF SUCH SYSTEMS; MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS OR ELEMENTS
- G05B5/00—Anti-hunting arrangements
- G05B5/01—Anti-hunting arrangements electric
Landscapes
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Engineering & Computer Science (AREA)
- Automation & Control Theory (AREA)
- Electrical Control Of Air Or Fuel Supplied To Internal-Combustion Engine (AREA)
Abstract
838,323. Automatic control systems for jet engines. SMITH & SONS (ENGLAND) Ltd., S. Oct. 27, 1958 [Oct. 25, 1957], No. 33449/57. Class 38 (4). An automatic control system for controlling the operation of a jet tur. bine is so arranged that it is stable for small or large discrepancies between actual and demanded operational conditions of the turbine. A jet turbine 1 is normally controlled by a throttle 2 attached to a fuel supply system 3, the fuel system 3 having an over-riding control in the form of a solenoid controlled valve in accordance with an electric signal in a line 4. Thermocouples in the jet pipe of the turbine 1 develop a signal representing the actual operating value of the turbine exhaust temperature which signal is fed into a comparator 7 by way of an amplifier 5. A further signal is generated in a function generator 8 from signals 9, 10, 11 representing turbine speed and intake temperature and pressure respectively, the generated signal representing the demanded exhaust temperature, which signal is fed into the comparator 7 in opposition to the " actual value " signal such that any signal appearing at the output of the comparator 7 represents a discrepancy between the actual and demanded operation conditions of the turbine 1. The discrepancy signal is fed to a second comparator 14 by way of two parallel circuits the first of which is a T-network comprising components 16-19 which transmits the discrepancy signal whatever its value but with a phase lag, the second of which circuits comprises components 21-23 and a by-pass diode 28 which circuit transmits the discrepancy signal only when it exceeds a predetermined value but which is then transmitted with a phase advance. The output of the comparator 14 is fed to a phase shift circuit 33, the output of which constitutes the signal 4 controlling the solenoid in the fuel supply system 3 whereby the turbine is controlled according to the demanded conditions.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB3344957A GB838323A (en) | 1957-10-25 | 1957-10-25 | Improvements in automatic control systems |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB3344957A GB838323A (en) | 1957-10-25 | 1957-10-25 | Improvements in automatic control systems |
Publications (1)
Publication Number | Publication Date |
---|---|
GB838323A true GB838323A (en) | 1960-06-22 |
Family
ID=10353098
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB3344957A Expired GB838323A (en) | 1957-10-25 | 1957-10-25 | Improvements in automatic control systems |
Country Status (1)
Country | Link |
---|---|
GB (1) | GB838323A (en) |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3153322A (en) * | 1959-07-17 | 1964-10-20 | Dehavilland Aircraft | Magnetic amplifier circuits |
US3774395A (en) * | 1970-12-29 | 1973-11-27 | Mtu Muenchen Gmbh | Control system for gas turbine engines |
-
1957
- 1957-10-25 GB GB3344957A patent/GB838323A/en not_active Expired
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3153322A (en) * | 1959-07-17 | 1964-10-20 | Dehavilland Aircraft | Magnetic amplifier circuits |
US3774395A (en) * | 1970-12-29 | 1973-11-27 | Mtu Muenchen Gmbh | Control system for gas turbine engines |
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