Device and method of protection of turbomachine calculator in aircraft from speed measurement errors

FIELD: measuring equipment.

SUBSTANCE: protection device of an aircraft turbomachine calculator from speed measurement errors, containing in the adjustment channel a speed sensor for the turbomachine gearbox shaft, the first speed measurement circuit and speed adjustment circuit. In the adjustment channel the device contains a speed sensor for the turbomachine gas generator shaft, the second speed measurement circuit and turbomachine shutdown control circuit. Both speed sensors are two sensors, which are installed opposite two phonic wheels of different processes and having a different number of teeth. The first and second speed adjustment circuits compare a frequency signal with a minimum threshold and deliver the first and second speed issue detection signals, when the measured frequency is lower than the minimum threshold. The device additionally includes a cross-check circuit of the first and second speeds, obtained from the first and second speed measurement circuits, respectively. The cross-check circuit delivers the third speed issue detection signal in case of an abnormal deviation between the first and second speeds. The frequency signals are various frequency signals. According to the method of protection of the turbomachine calculator two pseudo-sinusoidal frequency signal, the frequency signals with a minimum threshold are compared and the speed issue detection signals are delivered, the speeds, delivered from the speed adjustment channel and control channel, are cross-checked, and the third speed issue detection signal is delivered, the machine shutdown is controlled in case of a speed issue.

EFFECT: improvement of the device.

11 cl, 2 dwg

 



 

Same patents:

The invention relates to the turbines and can be used to regulate steam turbines

FIELD: machine building.

SUBSTANCE: invention consists in the method for readjusting a steam turbine (1) with the steam for it being produced by a steam generator. The method allows for the adjustment of a turbine (1) to pass from the first maximum of steam generator heat output to the second maximum of steam generator heat output. The turbine (1) comprises a high-pressure module (2) including at least one set (2A) of stationary blades and at least one set (2B) of moving blades set on a rotor (4). The method implies that in the high-pressure module (2) at least one set (2A) of stationary blades designed to be operated under the conditions of the first heat output maximum is replaced by at least one set (2A) of stationary blades designed to be operated under the conditions of the second heat output maximum. The set or sets (2B) of moving blades are designed to be operated under the conditions of the first or second heat output maximum, the rotor (4) and the set or sets (2B) of moving blades of the high-pressure module (2) remain unchanged at the transition from the first maximum of steam generator heat output to the second maximum of steam generator heat output.

EFFECT: method makes it possible to avoid the rotor replacement at readjustment keeping acceptable efficiency for two maximums of heat output.

8 cl, 5 dwg

FIELD: power industry.

SUBSTANCE: invention relates to the power industry. A method for the asymmetrical supply of a working fluid medium involves the following stages at which: the first portion of the working fluid medium is supplied to the first low pressure turbine and the second portion of the working fluid medium is supplied to the second low pressure turbine; with that, the second portion is larger in terms of quantity than the first portion is; the first portion of the working fluid medium is processed in the first low pressure turbine, thus creating the first outlet fluid medium, and the second portion of the working fluid medium is processed in the second low pressure turbine, thus creating the second outlet fluid medium; the first outlet fluid medium is supplied to the first condenser and the second outlet fluid medium is supplied to the second condenser. Besides, a system for the method implementation is presented.

EFFECT: invention allows improving the operating efficiency of a thermal power plant.

18 cl, 7 dwg

FIELD: power enegeneering.

SUBSTANCE: invention involves a motor-driven headstock for right turbine control valve, which includes casing with fulcrum bracket and bearing datum flange locating a slave cylinder with contralateral windows in front of a bracket, with a frame inside a slave cylinder, carried out in a form of two buckets, combined by two tension strips, arranged in such a manner, that the aperture between the strips has the same form as windows in the slave cylinder; such windows and a frame aperture is pierced by a lever, revolution axis of which goes through one out of two ends of a lever and is located on the bracket and the second end of the lever is resting upon the graded cam, connected to the operating mechanism. A plunger, resting upon the upper ramming piping of the frame, loaded with a recoil spring, the upper part of which is resting upon a tray, located on a stand, is situated in the centre of lever. The lower bucket is connected to the valve shaft, at that the friction surface of the casing is accomplished in a form of plugs, inner surface of which are characterized by the wear proof quality, while the surface of the frame buckets is accomplished in a form of plugs with the tear proof outer surface; bucket group gap width between the frame and the casing is greater, than the gap width between the piston and grand, besides, the slave cylinder, frame with buckets and tension strips are produced out of carbon construction steel, and the bearing datum flange - out of heat-resistant alloyed steel.

EFFECT: increased turbine valve operation management and reduced probability of emergency conditions occurrence within the power plants, alongside with repair costs reduction.

1 cl, 3 dwg

Gas turbine // 2351770

FIELD: engines and pumps.

SUBSTANCE: invention relates to turbojet engine gas turbines. Gas turbine blades are mounted on a cylindrical sleeve to rotate and axially move thereon which is provided for by attaching it to structural circular wall tapered ledge. The said wall central part represents a two-wall cylinder incorporating a spring fitted between the cylinder walls and resting upon the circular ledge of cylindrical barrel rigidly fixed on the shaft. The barrel rear part has a circular wall made integral with a part of vortex turbine blades to allow the second part of aforesaid blades made on the structural circular wall inner surface to enter into the said first part to have both parts aligned in axial travel. Circular webs arranged on the turbojet engine intermediate structural casing confine the vortex turbine blade outer parts. Fuel, in compliance with the fuel lines, actuates the cylindrical sleeve axial travel mechanism to vary the circular gap size controlling the passage of gas flow onto the gas turbine blades.

EFFECT: power take-off adjustment.

2 cl, 5 dwg

The invention relates to the fields of manufacturing and maintenance powerful steam turbines and applies the control and measuring equipment

The invention relates to the field of oil supply of steam turbines for nuclear submarines

Gas turbine // 2351770

FIELD: engines and pumps.

SUBSTANCE: invention relates to turbojet engine gas turbines. Gas turbine blades are mounted on a cylindrical sleeve to rotate and axially move thereon which is provided for by attaching it to structural circular wall tapered ledge. The said wall central part represents a two-wall cylinder incorporating a spring fitted between the cylinder walls and resting upon the circular ledge of cylindrical barrel rigidly fixed on the shaft. The barrel rear part has a circular wall made integral with a part of vortex turbine blades to allow the second part of aforesaid blades made on the structural circular wall inner surface to enter into the said first part to have both parts aligned in axial travel. Circular webs arranged on the turbojet engine intermediate structural casing confine the vortex turbine blade outer parts. Fuel, in compliance with the fuel lines, actuates the cylindrical sleeve axial travel mechanism to vary the circular gap size controlling the passage of gas flow onto the gas turbine blades.

EFFECT: power take-off adjustment.

2 cl, 5 dwg

FIELD: power enegeneering.

SUBSTANCE: invention involves a motor-driven headstock for right turbine control valve, which includes casing with fulcrum bracket and bearing datum flange locating a slave cylinder with contralateral windows in front of a bracket, with a frame inside a slave cylinder, carried out in a form of two buckets, combined by two tension strips, arranged in such a manner, that the aperture between the strips has the same form as windows in the slave cylinder; such windows and a frame aperture is pierced by a lever, revolution axis of which goes through one out of two ends of a lever and is located on the bracket and the second end of the lever is resting upon the graded cam, connected to the operating mechanism. A plunger, resting upon the upper ramming piping of the frame, loaded with a recoil spring, the upper part of which is resting upon a tray, located on a stand, is situated in the centre of lever. The lower bucket is connected to the valve shaft, at that the friction surface of the casing is accomplished in a form of plugs, inner surface of which are characterized by the wear proof quality, while the surface of the frame buckets is accomplished in a form of plugs with the tear proof outer surface; bucket group gap width between the frame and the casing is greater, than the gap width between the piston and grand, besides, the slave cylinder, frame with buckets and tension strips are produced out of carbon construction steel, and the bearing datum flange - out of heat-resistant alloyed steel.

EFFECT: increased turbine valve operation management and reduced probability of emergency conditions occurrence within the power plants, alongside with repair costs reduction.

1 cl, 3 dwg

FIELD: power industry.

SUBSTANCE: invention relates to the power industry. A method for the asymmetrical supply of a working fluid medium involves the following stages at which: the first portion of the working fluid medium is supplied to the first low pressure turbine and the second portion of the working fluid medium is supplied to the second low pressure turbine; with that, the second portion is larger in terms of quantity than the first portion is; the first portion of the working fluid medium is processed in the first low pressure turbine, thus creating the first outlet fluid medium, and the second portion of the working fluid medium is processed in the second low pressure turbine, thus creating the second outlet fluid medium; the first outlet fluid medium is supplied to the first condenser and the second outlet fluid medium is supplied to the second condenser. Besides, a system for the method implementation is presented.

EFFECT: invention allows improving the operating efficiency of a thermal power plant.

18 cl, 7 dwg

FIELD: machine building.

SUBSTANCE: invention consists in the method for readjusting a steam turbine (1) with the steam for it being produced by a steam generator. The method allows for the adjustment of a turbine (1) to pass from the first maximum of steam generator heat output to the second maximum of steam generator heat output. The turbine (1) comprises a high-pressure module (2) including at least one set (2A) of stationary blades and at least one set (2B) of moving blades set on a rotor (4). The method implies that in the high-pressure module (2) at least one set (2A) of stationary blades designed to be operated under the conditions of the first heat output maximum is replaced by at least one set (2A) of stationary blades designed to be operated under the conditions of the second heat output maximum. The set or sets (2B) of moving blades are designed to be operated under the conditions of the first or second heat output maximum, the rotor (4) and the set or sets (2B) of moving blades of the high-pressure module (2) remain unchanged at the transition from the first maximum of steam generator heat output to the second maximum of steam generator heat output.

EFFECT: method makes it possible to avoid the rotor replacement at readjustment keeping acceptable efficiency for two maximums of heat output.

8 cl, 5 dwg

FIELD: transport.

SUBSTANCE: aircraft turbojet compressor (1) comprises grating (2) of fixed blades and air intake system at the level of passages (5) between two blades (3) via slits (6 made said wall (4). Blades (3) are fitted on wall (4) to make air passages (5) there between. Slits are arranged in a discrete manner to make multiple holes (O1, O2, O3, O4) located in airflow direction (E). Upstream hole (O1) of every slit (6) features cross-section area larger than that of the other, downstream, holes (O2, O3, O4) of slit (6). Quantity and cross-section of downstream holes (O2, O3, O4) can vary depending upon preset suction flow rate. This invention consists in the air intake at the level of passages between two blades effected by means of multiple holes arranged one after the other in airflow direction to substitute the sole hole. Suction distribution among several openings allows ruling out of recycling possible in sole hole.

EFFECT: decreased secondary losses in impeller and ruled out flow separation.

8 cl, 4 dwg

FIELD: power industry.

SUBSTANCE: invention relates to power industry. A control system of a steam turbine for maintenance of synchronisation between power grid (10) and electric generator (20) brought into action by steam turbine (30), after short circuit occurs in the power grid, containing the following: control (40) that can control valve mechanism (50) to control the steam flow in the steam turbine; measuring device (60) of voltage drop at the electric generator outlet; measuring device (70) of electric power drop at the electric generator outlet; with that, the control is made so that it can bring into action the valve mechanism of the steam turbine in response to voltage drop exceeding the specified value and to electric power drop exceeding the specified value.

EFFECT: invention allows reducing initiation delay of speed control of the steam turbine after short circuit occurs in the power grid.

4 cl, 5 dwg

FIELD: measuring equipment.

SUBSTANCE: protection device of an aircraft turbomachine calculator from speed measurement errors, containing in the adjustment channel a speed sensor for the turbomachine gearbox shaft, the first speed measurement circuit and speed adjustment circuit. In the adjustment channel the device contains a speed sensor for the turbomachine gas generator shaft, the second speed measurement circuit and turbomachine shutdown control circuit. Both speed sensors are two sensors, which are installed opposite two phonic wheels of different processes and having a different number of teeth. The first and second speed adjustment circuits compare a frequency signal with a minimum threshold and deliver the first and second speed issue detection signals, when the measured frequency is lower than the minimum threshold. The device additionally includes a cross-check circuit of the first and second speeds, obtained from the first and second speed measurement circuits, respectively. The cross-check circuit delivers the third speed issue detection signal in case of an abnormal deviation between the first and second speeds. The frequency signals are various frequency signals. According to the method of protection of the turbomachine calculator two pseudo-sinusoidal frequency signal, the frequency signals with a minimum threshold are compared and the speed issue detection signals are delivered, the speeds, delivered from the speed adjustment channel and control channel, are cross-checked, and the third speed issue detection signal is delivered, the machine shutdown is controlled in case of a speed issue.

EFFECT: improvement of the device.

11 cl, 2 dwg

FIELD: engines and pumps.

SUBSTANCE: invention relates to installations comprising turboexpanders and drive turbomachines, as well as to methods for such installations’ controlling. Installation with the turboexpander and the drive turbomachine comprises a turboexpander designed to expand the first fluid and comprising an expansion stage with one impeller, first row of moving input guide vanes located at the input to said expansion stage, drive turbomachine configured with possibility to process a second fluid and comprising an impeller, second row of movable input guide vanes located at the input of the impeller of the turbomachine, mechanical transmission located between the turboexpander and the drive turbomachine and a controller coupled to a second row of movable guide vanes and configured with possibility to control a second row of movable blades for controlling the rotation speed of said drive turbomachine and said turboexpander. Controller is configured with possibility to receive data on the specified rotation speed and controlling the second row of moving blades to control the rotational speed to the desired value. Plant control method comprises a turboexpander, a mechanically driven turbomachine driven by a turboexpander. Also comprises first row of moving input guide vanes located at the turboexpander input, and a second row of movable input guide vanes located at the drive turbomachine. Method comprises the following steps: expanding the first fluid in a turboexpander and generating mechanical energy therefrom; provision of the drive turbomachine rotation with the help of mechanical energy, produced by turboexpander; processing of the second fluid; control of the second row of movable input guide vanes for control over the rotation speed of the drive turbomachine and a turboexpander and controlling a second row of moving blades to maintain a rotational speed within a near constant value range.

EFFECT: technical result consists in enabling of plant’s efficiency.

17 cl, 5 dwg

FIELD: measuring equipment.

SUBSTANCE: protection device of an aircraft turbomachine calculator from speed measurement errors, containing in the adjustment channel a speed sensor for the turbomachine gearbox shaft, the first speed measurement circuit and speed adjustment circuit. In the adjustment channel the device contains a speed sensor for the turbomachine gas generator shaft, the second speed measurement circuit and turbomachine shutdown control circuit. Both speed sensors are two sensors, which are installed opposite two phonic wheels of different processes and having a different number of teeth. The first and second speed adjustment circuits compare a frequency signal with a minimum threshold and deliver the first and second speed issue detection signals, when the measured frequency is lower than the minimum threshold. The device additionally includes a cross-check circuit of the first and second speeds, obtained from the first and second speed measurement circuits, respectively. The cross-check circuit delivers the third speed issue detection signal in case of an abnormal deviation between the first and second speeds. The frequency signals are various frequency signals. According to the method of protection of the turbomachine calculator two pseudo-sinusoidal frequency signal, the frequency signals with a minimum threshold are compared and the speed issue detection signals are delivered, the speeds, delivered from the speed adjustment channel and control channel, are cross-checked, and the third speed issue detection signal is delivered, the machine shutdown is controlled in case of a speed issue.

EFFECT: improvement of the device.

11 cl, 2 dwg

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