GB1321333A - Gas turbine engines having variable pitch guide vanes - Google Patents
Gas turbine engines having variable pitch guide vanesInfo
- Publication number
- GB1321333A GB1321333A GB4050270A GB4050270A GB1321333A GB 1321333 A GB1321333 A GB 1321333A GB 4050270 A GB4050270 A GB 4050270A GB 4050270 A GB4050270 A GB 4050270A GB 1321333 A GB1321333 A GB 1321333A
- Authority
- GB
- United Kingdom
- Prior art keywords
- signal
- compressor
- turbine
- speed
- guide vanes
- 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 7
- 239000007789 gas Substances 0.000 abstract 5
- 238000002485 combustion reaction Methods 0.000 abstract 3
- 239000000567 combustion gas Substances 0.000 abstract 2
- 238000011144 upstream manufacturing Methods 0.000 abstract 2
- 230000001133 acceleration Effects 0.000 abstract 1
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
- F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
- F02C9/48—Control of fuel supply conjointly with another control of the plant
- F02C9/50—Control of fuel supply conjointly with another control of the plant with control of working fluid flow
- F02C9/54—Control of fuel supply conjointly with another control of the plant with control of working fluid flow by throttling the working fluid, by adjusting vanes
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Control Of Turbines (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Engine Equipment That Uses Special Cycles (AREA)
Abstract
1321333 Fuel control in gas turbine engines MOTEREN-UND TURBINEN-UNION MUNCHEN GmbH 21 Aug 1970 [4 Sept 1969] 40502/70 Heading F1G [Also in Division G3] Relates to a control system for an automobile gas turbine power unit. The turbine unit comprises a compressor 17, Fig.1, driven by a compressor turbine 19, compressed air flowing through a heat exchanger 23 to a combustion chamber 22 where it serves for combustion of a fuel B and is expanded in the compressor turbine 19. The combustion gases flow via variable pitch guide vanes 25 to the power turbine 26 and are then exhausted to atmosphere via the heat exchanger. The control system A operates to adjust the guide vanes and hence the amount of through flow opening as a function of deviation of gas temperature difference between compressor delivery air and the combustion gases upstream of the compressor turbine from a desired temp difference, and other variable characteristics as described below. In addition it adjusts a metering device 16 to control the rate of fuel flow to the combustion chamber 22. The fuel is pumped by pump 21 driven by the compressor turbine. The power turbine 26 drives via a gear box 24. In the control system, a signal selector unit 5, Fig.1a, receives a signal E6 significant of deviation in actual speed n 1 of compressor turbine 19 from a desired speed N 1 as demanded by accelerator pedal 1 and controls the fuel B flow rate via the metering device 16 to restore the speed to the desired value. A signal selector unit 8 receives as input signals E 1 to E5. The signal E1 is derived from the sum of first and second signals. The first signal represents the deviation in actual temperature difference between the temperatures (as sensed by thermocouples) at the compressor air intake (t 1 ) and upstream of the compressor turbine (t 4 ) and fed through a unit 10 which compensates for delay in thermocouples response, and a desired temperature difference. The desired temp difference T 4 - T 1 is derived by a function generator 9 which receives as inputs a signal n 1 representing the actual compressor speed and the signal t 1 (compressor intake temp). The said second signal E8 is produced by a function generator 6 from signal inputs received significant of:- actual compressor speed (n 1 ), response time behaviour T w of the heat-exchanger 23, (i.e. a signal which is a function of the temp variation of compressor air flowing out of the heatexchanger over the time, in response to a sudden change in the temp of the power turbine exhaust gas), and fuel flow rate. The other inputs to the signal selector 8 are:- the signal E 2 which is produced when the actual compressor speed n 1 is below a predetermined speed n 1 e. g. half the desired speed, and this signal helps to maintain a predetermined guide vane opening during the starting period, - the signal E3 representing the deviation of the power turbine speed n 2 from a desired value, N2 and protects against overspeed thereof, the signal E4 representing acceleration and derived from the actual pressure change rate of gases downstream of the compressor and prescribed maximum rate of pressure change, whereby the guide vanes will be operated if the said max. rate of change is exceeded. The signal E5 which is a braking signal and operates the guide vanes to effect braking. The signal selector unit 8 comprises a diode logic gate to which signals E1 to E5 are applied Fig.3 (not shown) and the input signal of maximum magnitude and demanding an increase in guide vane through flow area predominates to control the guide vanes position via a hydraulic servomotor 12 and linkage 13. The output of selector unit 8 is also fed via a switch 16' to the selector unit 5 which is also a diode logic gate Fig. 2 (not shown). There again the highest input signal predominates to control the fuel flow rate.
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE19691944868 DE1944868C (en) | 1969-09-04 | Control device for a gas turbine engine for driving a motor vehicle |
Publications (1)
Publication Number | Publication Date |
---|---|
GB1321333A true GB1321333A (en) | 1973-06-27 |
Family
ID=5744599
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB4050270A Expired GB1321333A (en) | 1969-09-04 | 1970-08-21 | Gas turbine engines having variable pitch guide vanes |
Country Status (3)
Country | Link |
---|---|
FR (1) | FR2030930A5 (en) |
GB (1) | GB1321333A (en) |
SE (1) | SE379575B (en) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2021038604A1 (en) * | 2019-08-27 | 2021-03-04 | Nuovo Pignone Tecnologie S.r.l. | Two-shaft gas turbine control system ano method |
Families Citing this family (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE2064340C3 (en) * | 1970-12-29 | 1973-12-06 | Motoren- Und Turbinen-Union Muenchen Gmbh, 8000 Muenchen | Control device for a gas turbine plant |
DE2241363B2 (en) * | 1972-08-23 | 1975-01-09 | Motoren- Und Turbinen-Union Muenchen Gmbh, 8000 Muenchen | Control device for a gas turbine engine, in particular a motor vehicle |
US4274253A (en) * | 1977-12-22 | 1981-06-23 | The Garrett Corporation | Control for turbine and recuperator inlet temperatures |
-
1969
- 1969-12-22 FR FR6944457A patent/FR2030930A5/fr not_active Expired
-
1970
- 1970-08-21 GB GB4050270A patent/GB1321333A/en not_active Expired
- 1970-09-04 SE SE7012062A patent/SE379575B/xx unknown
Cited By (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2021038604A1 (en) * | 2019-08-27 | 2021-03-04 | Nuovo Pignone Tecnologie S.r.l. | Two-shaft gas turbine control system ano method |
US20220195947A1 (en) * | 2019-08-27 | 2022-06-23 | Nuovo Pignone Tecnologie S.r.l. | Two-shaft gas turbine control system and method |
AU2019463160B2 (en) * | 2019-08-27 | 2023-08-24 | Nuovo Pignone Tecnologie S.r.l. | Two-shaft gas turbine control system and method |
US11781492B2 (en) * | 2019-08-27 | 2023-10-10 | Nuovo Pignone Tecnologie S.r.l. | Two-shaft gas turbine control system and method |
Also Published As
Publication number | Publication date |
---|---|
DE1944868B2 (en) | 1972-02-17 |
SE379575B (en) | 1975-10-13 |
FR2030930A5 (en) | 1970-11-13 |
DE1944868A1 (en) | 1971-03-25 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
US2219994A (en) | Gas turbine plant and regulating system therefor | |
US4173121A (en) | Hybrid dual shaft gas turbine with accumulator | |
US2974482A (en) | Coolant injection system for engines | |
GB1498664A (en) | Gas turbine fuel control | |
CA2845182C (en) | System and method for engine transient power response | |
US3777479A (en) | Control system for gas turbine engines | |
GB1473413A (en) | Combined steam turbine and gas turbine power plant | |
US3166902A (en) | Fuel control for a regenerative gas turbine engine | |
US4173119A (en) | Control system for a gas turbine engine, especially a vehicular gas turbine engine | |
JPH0585734B2 (en) | ||
GB1179994A (en) | Electronic Fuel Control System for Gas Turbine Engines. | |
US4102595A (en) | Bleed valve control system | |
US2848869A (en) | Fuel control system for gas turbine engines | |
GB1424138A (en) | Control circuits for gas turbines | |
US3076312A (en) | Fuel supply control for gas turbine engines | |
US3316713A (en) | Closed-loop fuel control for gas turbine engines | |
GB1321333A (en) | Gas turbine engines having variable pitch guide vanes | |
US3888078A (en) | Governing device for a gas turbine system exemplified by a vehicular or aircraft engine | |
US3203177A (en) | Brake and reverse drive for gas turbine engines | |
JPS5941012B2 (en) | Gas turbine engine fuel control method and device | |
US3882672A (en) | System arrangement for governing gas turbine engines, especially gas turbine aero-engines | |
US3747344A (en) | Variable nozzle area control system | |
US4467608A (en) | Control method and apparatus for an internal combustion engine with a turbocharger | |
GB1148578A (en) | Gas turbine power plant | |
US3500637A (en) | Gas turbine engine with aerodynamic torque converter drive |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
PS | Patent sealed [section 19, patents act 1949] | ||
746 | Register noted 'licences of right' (sect. 46/1977) | ||
PCNP | Patent ceased through non-payment of renewal fee |