GB900744A - Gas turbine power units - Google Patents
Gas turbine power unitsInfo
- Publication number
- GB900744A GB900744A GB808659A GB808659A GB900744A GB 900744 A GB900744 A GB 900744A GB 808659 A GB808659 A GB 808659A GB 808659 A GB808659 A GB 808659A GB 900744 A GB900744 A GB 900744A
- Authority
- GB
- United Kingdom
- Prior art keywords
- lever
- pressure
- datum
- turbine
- pipe
- 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
- F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
- F02C9/26—Control of fuel supply
- F02C9/28—Regulating systems responsive to plant or ambient parameters, e.g. temperature, pressure, rotor speed
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Electrical Discharge Machining, Electrochemical Machining, And Combined Machining (AREA)
Abstract
900,744. Fluid-pressure servomotor-control systems. NAPIER & SON Ltd., D. March 4, 1960 [March 9, 1959; Aug. 26, 1959], Nos. 8086/59 and 29244/59. Class 135. [Also in Group XXVI] A gas turbine power unit having a free power turbine and equipped with a fuel metering unit which is actuated in response to pressure and temperature at the compressor air inlet, is provided with a governor which is coupled to the free power turbine and compares the actual speed of this turbine with a datum and further modifies the fuel supply to maintain the datum speed which is set by a manual speed selector. The gas turbine engine 10 has a free power turbine 22 driving a helicopter rotor 11. Fuel is supplied to the burners 19 through a metering unit 17 which is responsive to ambient air pressure and temperature at the compressor inlet through sensing devices 95, 96, respectively, the metering unit being fed by a variable-stroke pump 16. Geared to the turbine output shaft 26 is a hydro-mechanical speed signal generator 28, e.g. as disclosed in Specification 832,195, which produces a differential hydraulic pressure between two pipes 29, 30 connected to a comparator unit 31 in which the datum is set by a manual speed selector lever 34 through a lever 32. A control pressure set up by the comparator through a pipe 35 acts on a servoadjuster 47 to adjust the stroke of the pump 16. The selector lever 34 is also connected to the metering unit 17. Pipes 29, 30 lead to opposite sides of a diaphragm 36, Fig. 2, in the comparator 31, this diaphragm actuating through a lever 42 a half ball leak-off valve 45 controlling the pipe 35, in opposition to a datum loading spring 40. The compression of this spring is set through a movable abutment 50 carried by a double-acting servo piston 51 which is arranged to follow up the movement of a control-valve 54 connected through lever 32 to the manual setting lever 34. Operating pressure to this servo piston is supplied through a pipe 59 and exhausted along with the leak-off from valve 45 through a pipe 48. In a modification, an indication of the governor authority is obtained electrically through a variable induction device, Fig. 4, having'a movable armature 66 actuated by a pressure-balanced plunger 64 which contacts the half ball valve lever 42 to indicate, e.g. on a dial, the effective movement of this lever. Several forms of the inductive device are described.
Priority Applications (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB808659A GB900744A (en) | 1959-03-09 | 1959-03-09 | Gas turbine power units |
BE588441A BE588441A (en) | 1959-03-09 | 1960-03-09 | Tuning of gas turbine engines |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB808659A GB900744A (en) | 1959-03-09 | 1959-03-09 | Gas turbine power units |
Publications (1)
Publication Number | Publication Date |
---|---|
GB900744A true GB900744A (en) | 1962-07-11 |
Family
ID=9845483
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB808659A Expired GB900744A (en) | 1959-03-09 | 1959-03-09 | Gas turbine power units |
Country Status (1)
Country | Link |
---|---|
GB (1) | GB900744A (en) |
-
1959
- 1959-03-09 GB GB808659A patent/GB900744A/en not_active Expired
Similar Documents
Publication | Publication Date | Title |
---|---|---|
GB909511A (en) | Improvements relating to gas turbine engines having a compressor bleed valve | |
GB1018729A (en) | Improvements in two shaft gas turbine control system | |
GB561932A (en) | A means for controlling the speed of rotation of a gas compressor used in connection with or forming part of an internal combustion engine | |
GB585032A (en) | Improvements in governors for internal combustion turbines | |
GB1147076A (en) | Improvements relating to gas turbine installations | |
GB900744A (en) | Gas turbine power units | |
GB845269A (en) | Improvements in fuel flow control apparatus for gas turbine engines | |
US3095702A (en) | Afterburner fuel control | |
GB861601A (en) | Control mechanism for aircraft power plants comprising a gas turbine engine driving a propeller | |
GB614106A (en) | Improvements in or relating to gas turbine plants | |
GB1247570A (en) | A gas turbine engine having a free-power turbine | |
GB694083A (en) | Improved regulating device for gas turbines and like machines or engines | |
GB727201A (en) | Improvements in fuel supply systems for gas turbine engines | |
US2585200A (en) | Governing of free piston gas generator power plant | |
GB930924A (en) | Improvements in or relating to hydraulic governors | |
GB551516A (en) | Improvements in the governing of a prime mover such as a turbine supplied by gas generators | |
GB949031A (en) | Improvements in the pitch control of variable pitch vanes in axial flow compressors | |
GB636115A (en) | Improvements in or relating to pressure controls for turbines | |
GB769103A (en) | Improvements relating to fuel systems of gas-turbine engines | |
GB588005A (en) | Improvements relating to hydraulic governors | |
GB732459A (en) | Improvements in and relating to regulators for variable nozzle gas turbine powerplants | |
GB944720A (en) | Control means for groups comprising one or more electric motors supplied with current by a generator driven by a internal combustion engine | |
GB806207A (en) | Improvements in or relating to governors, more particularly for gas turbine engines | |
GB837903A (en) | Internal combustion engine installations with supercharging and indirect power transmission | |
GB831038A (en) | Improvements in fuel control systems for turbo propeller engines |