CN113982763B

CN113982763B - Emergency braking device and method for gas turbine

Info

Publication number: CN113982763B
Application number: CN202111199538.6A
Authority: CN
Inventors: 吕新; 章旋
Original assignee: China United Heavy Gas Turbine Technology Co Ltd
Current assignee: China United Heavy Gas Turbine Technology Co Ltd
Priority date: 2021-10-14
Filing date: 2021-10-14
Publication date: 2023-04-28
Anticipated expiration: 2041-10-14
Also published as: CN113982763A

Abstract

The invention provides an emergency braking device and an emergency braking method for a gas turbine, wherein the emergency braking method for the gas turbine comprises the following steps of: a pneumatic brake is arranged on a main shaft of the gas turbine; the pneumatic brake is driven with gas generated by a compressor of the gas turbine to brake the main shaft of the gas turbine. The emergency braking method of the gas turbine has the advantages of high reliability and rapid action.

Description

Emergency braking device and method for gas turbine

Technical Field

The invention relates to the technical field of gas turbines, in particular to an emergency braking device and an emergency braking method for a gas turbine.

Background

Gas turbines are high speed rotating equipment that can cause serious damage to the combustion engine if the rotational speed increases to an unacceptable level. In the related art, overspeed protection of the gas turbine is mainly realized by setting a threshold value, and a manual emergency shutdown button is further used. If the rotational speed is greater than the threshold, a trip signal is generated to the hardware line trip link to interrupt the gas turbine. The manual emergency stop and the automatic trip share a part of trip loops, the two loops are not completely independent, and the mechanism is similar, so that the possibility of common mode faults exists; if the trip link fails, the gas turbine will overspeed. And after the trip link action cuts off fuel, the gas turbine can only wait for the deceleration and can not actively brake.

Disclosure of Invention

The present invention aims to solve at least one of the technical problems in the related art to some extent.

For this reason, embodiments of the present invention provide an emergency braking apparatus for a gas turbine, which has advantages of high reliability and rapid operation.

The embodiment of the invention provides an emergency braking method of a gas turbine, which has the advantages of high reliability and quick action.

The emergency braking device of the gas turbine comprises:

a pneumatic brake adapted to be provided on a main shaft of the gas turbine;

a brake air path adapted to be connected between the pneumatic brake and a compressor of the gas turbine so as to supply air to the pneumatic brake;

the ventilation valve is arranged on the braking air passage and is used for stopping or conducting the braking air passage so as to control the pneumatic brake.

According to the emergency braking device for the gas turbine, disclosed by the embodiment of the invention, the gas generated by the gas compressor of the gas turbine is used for driving the pneumatic brake to brake, and the intrinsic safety type braking of the gas turbine can be realized without depending on external power or energy sources, so that the reliability is good.

The emergency braking device of the gas turbine provided by the embodiment of the invention is rapid in action and can better protect the gas turbine.

Therefore, the emergency braking device of the gas turbine has the advantages of high reliability and rapid action.

In some embodiments, the vent valve includes a vent valve chamber and a diaphragm movably disposed within the vent valve chamber between a closed position and an open position to close or open the brake air path.

In some embodiments, the vent valve further comprises a shear line, the vent valve cavity comprises a first cavity and a second cavity, the brake air path comprises a first section and a second section, one end of the first section is suitable for being connected with a gas compressor of the gas turbine, the other end of the first section is communicated with the first cavity so that the gas compressor of the gas turbine can be used for introducing gas into the first cavity, one end of the second section is communicated with the second cavity, the other end of the second section is connected with the pneumatic brake, the baffle plate is rotatably arranged in the vent valve cavity between a closed position and an open position so as to cut off or conduct the brake air path,

When the baffle is in the closed position, the shear rope is connected between the baffle and the wall surface of the first cavity, the baffle is positioned between the first cavity and the second cavity in the axial direction of the main shaft so as to separate the first cavity and the second cavity,

when the partition plate is in the opening position, the shearing rope is disconnected, and the partition plate is positioned in the second cavity so that the first cavity and the second cavity are communicated.

In some embodiments, the emergency braking apparatus for a gas turbine according to the embodiment of the present invention further includes a shear blade, the vent valve further includes a shear blade and a sealing plug, the shear blade is provided on a wall surface of the first cavity, the shear blade is capable of communicating the first cavity with the outside, the sealing plug is provided in the shear blade to block the shear blade, the shear blade corresponds to the shear blade, and the shear blade is movably provided along an axial direction of the shear blade so as to pass through the sealing plug to thereby cut the shear rope.

In some embodiments, the emergency braking apparatus for a gas turbine according to the embodiments of the present invention further includes a control valve including a control valve chamber, a piston and a piston rod, the piston being movably disposed in the control valve chamber along an axial direction of the cutout, the control valve chamber including a third chamber and a fourth chamber, the piston being located between the third chamber and the fourth chamber in the axial direction of the cutout to block the third chamber and the fourth chamber, one end of the piston rod being located in the fourth chamber, and the one end of the piston rod being connected to the piston, the cutout being disposed on an end face of the other end of the piston rod.

In some embodiments, the emergency braking device for a gas turbine according to the embodiment of the invention further includes an oil injection pipeline, an oil drain pipeline and an oil drain valve, the control valve further includes an oil inlet and an oil outlet, one end of the oil inlet and outlet is communicated with the fourth cavity through the oil inlet and outlet, the other end of the oil inlet and outlet is connected with the oil injection pipeline and the oil drain pipeline, and the oil drain valve is arranged on the oil drain pipeline.

In some embodiments, the emergency braking apparatus for a gas turbine according to the embodiment of the present invention further includes a bursting tube, a first connecting tube, a second connecting tube, and an explosive, wherein the bursting tube and the explosive are disposed in the fourth chamber, and the bursting tube and the explosive are disposed adjacent to each other, so that the explosive bursts the bursting tube, one end of the bursting tube is communicated with the oil inlet and outlet pipe through the first connecting tube, and the other end of the bursting tube is communicated with the oil inlet and outlet pipe through the second connecting tube.

In some embodiments, the emergency braking device for the gas turbine further comprises a power supply and a detonation device, wherein the oil drain valve is an electromagnetic valve, the oil drain valve is connected with the power supply through an oil drain circuit, a normally closed switch is arranged on the oil drain circuit, the detonation device is used for detonating the explosive, the detonation device is connected with the power supply through a detonation circuit, and a normally open switch is arranged on the detonation circuit.

In some embodiments, the emergency braking apparatus for a gas turbine according to the embodiments of the present invention further includes a power generation apparatus including a permanent magnet adapted to be provided on the main shaft and a coil connected to the power supply through a charging circuit.

In some embodiments, the pneumatic brake includes a brake disc adapted to be disposed on the spindle, a first friction plate and a second friction plate opposite each other in an axial direction of the brake disc, and a portion of the brake disc is located between the first friction plate and the second friction plate in the axial direction of the brake disc.

In some embodiments, the gas turbine emergency brake apparatus of the present embodiments further includes a first cooling branch and a second cooling branch, an air inlet end of each of the first cooling branch and the second cooling branch being in communication with the second section of the brake air path, an air outlet end of the first cooling branch being provided on one of the first friction plate and the second friction plate, and an air outlet end of the second cooling branch being provided on the other of the first friction plate and the second friction plate.

The gas turbine of the embodiment of the invention comprises: the main shaft, the compressor and the emergency braking device according to any of the above embodiments.

The emergency braking method of the gas turbine comprises the following steps:

a pneumatic brake is arranged on a main shaft of the gas turbine;

the pneumatic brake is driven with gas generated by a compressor of the gas turbine to brake the main shaft of the gas turbine.

In some embodiments, the gas turbine emergency braking method of an embodiment of the present invention further comprises the steps of:

a braking air path is arranged between the air compressor and the pneumatic brake;

a ventilation valve is arranged on the braking air path;

the vent valve is opened to actuate the pneumatic brake using gas generated by a compressor of the gas turbine.

In some embodiments, the opening the vent valve comprises: cutting the shear line to rotate the diaphragm to the open position.

In some embodiments, the opening the vent valve further comprises: the shear blade is moved to sever the shear line.

In some embodiments, the method further comprises the steps of:

a control valve is arranged on the ventilation valve;

And starting the control valve, so as to open the ventilation valve.

In some embodiments, the method further comprises the steps of:

starting the control valve by using an oil drain valve or a detonation device;

and power is supplied to the oil drain valve and the detonation device by a power supply.

In some embodiments, the method further comprises the steps of:

a power generation device is arranged on a main shaft of the gas turbine;

and charging the power supply by using a power generation device.

Drawings

FIG. 1 is a schematic braking diagram of a sudden braking device for a gas turbine according to an embodiment of the present invention.

FIG. 2 is a schematic view of a sudden braking apparatus for a gas turbine according to an embodiment of the present invention.

Fig. 3 is an enlarged view at a in fig. 2.

Fig. 4 is an enlarged view at B in fig. 2.

Fig. 5 is an enlarged view at C in fig. 2.

FIG. 6 is a functional block diagram of a gas turbine emergency braking method according to an embodiment of the present invention.

FIG. 7 is a flow chart of a method for sudden braking of a gas turbine according to an embodiment of the invention.

FIG. 8 is a flow chart of a method for sudden braking of a gas turbine according to an embodiment of the invention.

FIG. 9 is a flow chart of a method for sudden braking of a gas turbine according to an embodiment of the invention.

FIG. 10 is a flow chart of a method for sudden braking of a gas turbine according to an embodiment of the invention.

FIG. 11 is a flow chart of a method for sudden braking of a gas turbine according to an embodiment of the invention.

Reference numerals:

a main shaft 1;

a pneumatic brake 2; a brake disc 201; a first friction plate 202; a second friction plate 203;

a brake air path 3; a first section 301; a second section 302;

a vent valve 4; a breather chamber 401; shear cords 402; a partition plate 403; a first cavity 405; a second cavity 406; a shear blade 407; a cutout 408; a sealing plug 409;

a compressor 5;

a first cooling branch 601; a second cooling branch 602;

a control valve 700; a piston 701; a piston rod 702; an in-place shutter 703; oil inlet and outlet pipe 704; an oil inlet/outlet port 705;

a third chamber 712; a fourth chamber 713;

oil injection line 801; oil drain line 802; a drain valve 803;

bursting the tube 901; a first connection pipe 902; a second connection pipe 903; an explosive 904;

a power supply 110; a drain circuit 111; a normally closed switch 112; a normally open switch 113; a detonation circuit 114;

a detonator 12;

a charging circuit 140; a permanent magnet 141; a coil 142; a capacitor 143;

an oil tank 15;

a turbine 16.

Detailed Description

Reference will now be made in detail to embodiments of the present invention, examples of which are illustrated in the accompanying drawings. The embodiments described below by referring to the drawings are illustrative and intended to explain the present invention and should not be construed as limiting the invention.

An emergency braking apparatus for a gas turbine according to an embodiment of the present invention is described below with reference to the accompanying drawings.

As shown in fig. 1, the emergency braking apparatus of a gas turbine according to an embodiment of the present invention includes: a pneumatic brake 2, a brake air path 3 and a ventilation valve 4.

The pneumatic brake 2 is arranged on a main shaft of the gas turbine, the brake air passage 3 is connected between a gas compressor of the gas turbine and the pneumatic brake 2 so as to supply air to the pneumatic brake 2, the ventilation valve 4 is arranged on the brake air passage 3, and the ventilation valve 4 is used for stopping or switching on the brake air passage 3 so as to control the pneumatic brake 2.

It can be understood that after the gas turbine is started, the gas compressor of the gas turbine introduces part of gas into the ventilation valve 4, and when braking is needed, the ventilation valve 4 is started to conduct the braking gas path 3, and at this time, the gas compressor 5 charges the gas generated by the gas compressor into the braking gas path 3 through the ventilation valve 4 to realize the braking function.

That is, the vent valve 4 may be a common valve, and the user can actively open the vent valve 4 to brake, or other control structures may be used to control the opening and closing of the vent valve 4.

In some embodiments, as shown in fig. 1-5, the pneumatic brake 2 includes a brake disc 201, a first friction plate 202, and a second friction plate 203. The brake disc 201 is adapted to be provided on a main shaft of a gas turbine, the first friction plate 202 and the second friction plate 203 are opposed in an axial direction of the brake disc 201, and a portion of the brake disc 201 is located between the first friction plate 202 and the second friction plate 203 in the axial direction of the brake disc 201.

Specifically, the brake disc 201 is sleeved on a main shaft of the gas turbine, the first friction plate 202 is located on the left side of the brake disc 201, the second friction plate 203 is located on the right side of the brake disc 201, when the gas turbine operates, the main shaft of the gas turbine rotates to drive the brake disc 201 to synchronously rotate, and when braking is needed, the pneumatic brake 2 is started to enable the first friction plate 202 and the second friction plate 203 to squeeze the brake disc 201, so that the purpose of braking is achieved.

It can be appreciated that compared with the common valve, when a user finds that braking is needed, the valve is actively opened, so that a delayed braking effect is generated, and the labor intensity of the user is increased.

Further, the vent valve 4 of the present invention includes a vent valve chamber 401, a shear line 402, and a diaphragm 403. The breather chamber 401 includes a first chamber 405 and a second chamber 406.

The brake air path 3 comprises a first section 301 and a second section 302, one end of the first section 301 is suitable for being connected with an air source, the other end of the first section 301 is communicated with a first cavity 405, one end of the second section 302 is communicated with a second cavity 406, the other end of the second section 302 is connected with the pneumatic brake 2 so as to control the pneumatic brake 2, a partition 403 is rotatably arranged in the ventilation valve cavity 401 between a closed position and an open position, and the extending direction of the main axis of the partition 403 is perpendicular to the axial direction of the main shaft of the gas turbine.

Specifically, the right end of the first section 301 is adapted to connect to the compressor 5, the left end of the first section 301 communicates with the first chamber 405, the right end of the second section 302 communicates with the second chamber 406, and the left end of the second section 302 is connected to the pneumatic brake 2.

When the diaphragm 403 is in the closed position, the shear line 402 is connected between the diaphragm 403 and the wall surface of the first chamber 405, and the diaphragm 403 is located between the first chamber 405 and the second chamber 406 in the axial direction of the spindle 1 to block the first chamber 405 and the second chamber 406.

Specifically, diaphragm 403 separates first cavity 405 from second cavity 406 under the pulling force of shear line 402, and ensures that gas within first cavity 405 cannot enter second cavity 406 when diaphragm 403 is in the closed position.

When diaphragm 403 is in the open position, shear line 402 is disconnected and diaphragm 403 is positioned within second chamber 406 such that first chamber 405 and second chamber 406 are in communication.

That is, when shear line 402 is disconnected, diaphragm 403 rotates counterclockwise, allowing first chamber 405 and second chamber 406 to communicate, i.e., diaphragm 403 is in the open position.

It will be appreciated that when the diaphragm 403 is in the closed position as shown in fig. 2 and 5, the diaphragm 403 separates the first and

second chambers

405 and 406 under the tension of the shear line 402, when braking is required, the shear line 402 is disconnected, the diaphragm 403 is rotated counterclockwise by the pressure of the gas in the first chamber 405, so that the first and

second chambers

405 and 406 are communicated, and then the gas source enters the pneumatic brake 2 via the first and

second sections

301 and 405 and 302, so that the first and

second friction plates

202 and 203 move toward the brake disc 201, and the brake disc 201 is pressed to perform braking, thereby achieving the function of active braking, and increasing the safety of the present invention.

After the gas turbine is started, the gas compressor of the gas turbine continuously charges gas into the first cavity 405 through the first section 301 until the operation of the gas turbine is stable, namely, the main shaft rotation speed of the gas turbine in the combustion area is kept unchanged, the gas compressor of the gas turbine charges gas into the first cavity 405 and maintains a certain pressure, and the gas pressure in the first cavity 405 is insufficient to break the shear ropes 402, it is understood that a braking gas source required by the pneumatic brake 2 of the gas turbine comes from the gas compressor of the gas turbine, and a power source of the gas compressor of the gas turbine is a main shaft of the gas turbine.

That is, under the same conditions, the higher the main shaft rotation speed of the gas turbine, the more gas is filled into the first chamber 405 by the gas compressor of the gas turbine, and the higher the gas pressure in the first chamber 405 is, the higher the air pressure supplied to the pneumatic brake 2 is, and the higher the braking power generated by the pneumatic brake 2 is. I.e. the braking power generated by the pneumatic brake 2 is changed in response to the change in the rotational speed of the main shaft of the gas turbine.

Specifically, after shear line 402 is disconnected, diaphragm 403 is rapidly rotated counterclockwise by the gas pressure of first chamber 405, and gas from first chamber 405 enters pneumatic brake 2 via first chamber 405, second chamber 406, and second section 302, causing first friction plate 202 and second friction plate 203 to compress brake disc 201, thereby rapidly braking the gas turbine.

In some embodiments, as shown in fig. 2 and 3, the gas turbine emergency brake apparatus of an embodiment of the present invention further includes a first cooling branch 601 and a second cooling branch 602. The air inlet end of each of the first cooling branch 601 and the second cooling branch 602 is communicated with the second section 302 of the brake air path 3, the air outlet end of the first cooling branch 601 is arranged on one of the first friction plate 202 and the second friction plate 203, and the air outlet end of the second cooling branch 602 is arranged on the other one of the first friction plate 202 and the second friction plate 203.

That is, the air inlet end of the first cooling branch 601 communicates with the second section 302 of the brake air path 3, and the air inlet end of the second cooling branch 602 communicates with the second section 302 of the brake air path 3.

The air outlet end of the first cooling branch 601 is arranged on the first friction plate 202, and the air outlet end of the second cooling branch 602 is arranged on the second friction plate 203; alternatively, the air outlet end of the first cooling branch 601 is disposed on the second friction plate 203, and the air outlet end of the second cooling branch 602 is disposed on the first friction plate 202.

Specifically, as shown in fig. 2, the air outlet end of the first cooling branch 601 is disposed on the first friction plate 202, and the air outlet end of the second cooling branch 602 is disposed on the second friction plate 203. Therefore, the gas exhausted from the gas outlet end of the first cooling branch 601 can cool the left end face of the brake disc 201, and the gas exhausted from the gas outlet end of the second cooling branch 602 can cool the right end face of the brake disc 201.

In some embodiments, as shown in fig. 2, 4 and 5, the gas turbine emergency brake apparatus of an embodiment of the present invention further includes a shear blade 407. The vent valve 4 further comprises a shear notch 408, and a sealing plug 409 is provided on the shear notch, the shear notch 408 communicates the first chamber 405 with the outside, the shear blade 407 corresponds to the shear notch 408, and the shear blade 407 is movably provided along the axial direction of the shear notch 408 so as to cut the shear line 402, the axial direction of the shear notch 408 being perpendicular to the extension direction of the main axis of the partition 403.

Specifically, when the shearing blade 407 is located above the shearing opening 408, and braking is required, the shearing blade 407 moves downward, the lower end of the shearing blade 407 penetrates through the shearing opening 408 to the first cavity 405, the shearing rope 402 is cut off, the partition plate 403 rotates anticlockwise, the first cavity 405 and the second cavity 406 are communicated, and the air source enters the pneumatic brake 2 through the first section 301, the first cavity 405, the second cavity 406 and the second section 302 to perform braking.

It will be appreciated that when the gas turbine rotates, the compressor of the gas turbine discharges the gas source through the first section 301 into the first chamber 405, so that a certain pressure is maintained in the first chamber 405, and then after the shear line 402 is cut off, the diaphragm 403 rotates anticlockwise under the action of the pressure in the first chamber 405, so that the first chamber 405 and the second chamber 406 are communicated, and thus gas is filled into the pneumatic brake 2, and a braking effect is generated. Therefore, braking can be quickly performed when braking is required.

In some embodiments, as shown in fig. 2 and 4, the gas turbine emergency brake apparatus of the embodiment of the present invention further includes a control valve 700, the control valve 700 including a control valve chamber, a piston 701, and a piston rod 702.

The piston 701 is movably provided in the control valve chamber in the axial direction of the cutout 408, the control valve chamber including a third chamber 712 and a fourth chamber 713. The piston 701 is located between the third chamber 712 and the fourth chamber 713 in the axial direction of the cutout 408 to block the third chamber 712 and the fourth chamber 713, one end of the piston rod 702 is located in the fourth chamber 713, and one end of the piston rod 702 is connected to the piston 701, and the cutout 407 is provided on the end face of the other end of the piston rod 702.

The piston rod 702 is provided with an in-place baffle 703, and the in-place baffle 703 is located in the fourth chamber 713.

Specifically, the third chamber 712 is located above the fourth chamber 713, the upper end of the piston 701 is located in the third chamber 712, the lower end of the piston 701 is located in the fourth chamber 713, the piston 701 can move up and down in the control valve chamber, and the piston 701 maintains a sealed state between the third chamber 712 and the fourth chamber 713 during the movement, the upper end of the piston rod 702 is connected to the piston 701, and the lower end of the piston rod 702 is connected to the shear blade 407. Therefore, when braking is needed, the piston moves downwards under the action of external force and simultaneously accelerates downwards under the action of self gravity, so that the time required for descending the piston 701 is shortened, and the efficiency is improved.

In some embodiments, as shown in fig. 2-5, the gas turbine emergency brake apparatus of the present embodiment further includes a fuel injection line 801, a fuel drain line 802, and a fuel drain valve 803. The control valve 700 further comprises an oil inlet and outlet pipe 704 and an oil inlet and outlet port 705, one end of the oil inlet and outlet pipe 704 is communicated with the fourth cavity 713 through the oil inlet and outlet port 705, the other end of the oil inlet and outlet pipe 704 is connected with the oil injection pipeline 801 and the oil drain pipeline 802, and the oil drain valve 803 is arranged on the oil drain pipeline 802.

It will be appreciated that the oil used in the emergency braking apparatus of a gas turbine according to an embodiment of the present invention may be hydraulic oil.

That is, the oil filling line 801 fills the fourth chamber 713 with hydraulic oil through the oil inlet and outlet pipe 704, and the hydraulic oil in the fourth chamber 713 is also discharged into the oil drain line 802 through the oil inlet and outlet pipe 704, and the oil drain valve 803 can control the oil drain line 802 to discharge the hydraulic oil in the fourth chamber 713 into the oil tank 15.

Specifically, the hydraulic oil in the oil filling pipeline 801 is filled into the fourth cavity 713 through the oil inlet and outlet pipe 704 and the oil inlet and outlet port 705, the liquid level of the hydraulic oil in the fourth cavity 713 rises, so that the in-place baffle 703 moves upwards, thereby driving the piston 701 to move upwards, and the piston drives the piston rod 702 and the shearing knife 407 to move upwards until the upper top surface of the in-place baffle 703 contacts with the upper top surface of the fourth cavity 713.

When braking is needed, the oil drain valve 803 is controlled to drain hydraulic oil in the fourth cavity 713 into the oil tank 15 through the oil inlet and outlet port 705, the oil inlet and outlet pipe 704, the oil drain pipeline 802 and the oil drain valve 803, the liquid level of the hydraulic oil in the fourth cavity 713 is lowered, so that the piston 701 moves downwards, the piston 701 drives the piston rod 702 and the shearing blade 407 to move downwards, the lower end of the shearing blade 407 penetrates through the shearing hole and cuts off the shearing rope 402, the partition plate 403 is in an open position, and then an air source is introduced into the pneumatic brake 2 to implement braking, and the process is an oil drain braking mode.

In some embodiments, as shown in fig. 2, the gas turbine emergency brake apparatus of the embodiment of the present invention further includes a burst tube 901, a first connection tube 902, a second connection tube 903, and an explosive 904, the burst tube 901 and the explosive 904 being disposed in the fourth chamber 713, and the burst tube 901 and the explosive 904 being disposed adjacent to each other such that the explosive 904 bursts the burst tube 901, one end of the burst tube 901 being in communication with the in-out oil pipe 704 through the first connection tube 902, and the other end of the burst tube 901 being in communication with the in-out oil pipe 704 through the second connection tube 903.

As shown in fig. 2 and fig. 4, the explosive 904 is located above the bursting tube 901, the bursting tube 901 is located above the piston 701, the bursting tube 901 is made of brittle material, such as glass, the explosive 904 is explosive, when the explosive 904 is detonated, the explosive is detonated in the third cavity 712, the bursting tube 901 is broken by the explosion energy, after the bursting tube 901 is broken, hydraulic oil enters the third cavity 712 through the oil inlet and outlet pipe 704 and the first connecting pipe 902, the piston 701 is driven by the detonation of the explosive 904 and drives the piston rod 702 and the shearing knife 407 to move downwards, the hydraulic oil in the fourth cavity 713 is discharged into the third cavity 712 through the oil inlet and outlet port 705, the oil inlet and outlet pipe 704 and the second connecting pipe 903 by the in-place baffle 703, so that the hydraulic oil is rapidly filled in the third cavity 712 to rapidly press the piston 701, and the piston 701 is rapidly moved downwards, thus the braking effect is achieved rapidly, and the process is a blasting braking mode.

It can be understood that the energy released by the explosion of the explosive does not reach the ignition point of the hydraulic oil used in the invention, so as to ensure the safety of the invention

In some embodiments, as shown in fig. 2-4, the emergency braking device for a gas turbine according to the embodiment of the present invention further includes a power supply 110 and a detonation device 12, where the oil drain valve 803 is a solenoid valve, the oil drain valve 803 is connected to the power supply 110 through an oil drain circuit 111, a normally closed switch 113 is disposed on the oil drain circuit 111, the detonation device 12 is used for detonating an explosive 904, the detonation device 12 is connected to the power supply 110 through a detonation circuit 114, and a normally open switch 112 is disposed on the detonation circuit 114.

As shown in fig. 2-5, the power supply 110, the oil drain valve 803, the normally closed switch 113 and the oil drain circuit 111 form a normally closed loop, that is, when the normally closed loop is electrified, hydraulic oil is injected into the fourth cavity 713 through the oil inlet and outlet pipe 704 and the oil inlet and outlet port 705 by the oil injection pipeline 801, and when the normally closed switch 113 is disconnected, the oil drain valve 803 controls the oil drain circuit 802, so that hydraulic oil in the fourth cavity 713 is discharged into the oil tank 15 through the oil inlet and outlet port 705, the oil inlet and outlet pipe 704 and the oil drain pipeline 802, the hydraulic oil level in the fourth cavity 713 is lowered, the piston 701 drives the piston rod 702 and the shear blade 407 to move downwards, the shear blade 407 penetrates the sealing plug 409 through the shear notch 408, and the shear rope 402 is sheared, so that gas in the first cavity 405 is introduced into the pneumatic brake 2 through the second cavity 406 and the second segment 302 to perform braking. The power supply 110, the detonation circuit 114, the normally open switch 112 and the detonation device 12 form a normally open loop, namely when the normally open switch 112 is closed, the normally open loop is electrified to control the detonation device 12 to detonate the explosive 904 so as to break the detonation tube 901, hydraulic oil in the oil inlet and outlet tube 704 is discharged into the third cavity 713 through the first connecting tube 902, hydraulic oil in the third cavity 713 is gradually increased, when the pressure of the hydraulic oil in the third cavity 712 acting on the piston 701 is larger than the pressure of the hydraulic oil in the fourth cavity 713 acting on the in-place baffle 703, the piston 701 moves downwards, the hydraulic oil in the fourth cavity 713 is discharged into the third cavity 912 through the second connecting tube 903, the hydraulic oil level in the fourth cavity 713 is quickly reduced, the piston 701 drives the piston rod 702 and the cutter 407 to move downwards, the cutter 407 penetrates the sealing plug 409 through the cutting opening 408, and cuts off the shearing rope 402, so that the gas in the first cavity 405 is introduced into the pneumatic brake 2 through the second cavity 406 and the second section 302, and braking is performed.

Therefore, the emergency braking device of the gas turbine provided by the embodiment of the invention provides two emergency braking modes, so that the reliability of the emergency braking device is improved.

In some embodiments, the emergency braking apparatus for a gas turbine according to an embodiment of the present invention further includes a power generation apparatus and a charging circuit 140, the power generation apparatus includes a permanent magnet 141 and a coil 142, the permanent magnet 141 is adapted to be disposed on a main shaft of the gas turbine, and the coil 142 is connected to the power supply 110 through the charging circuit 140.

As shown in fig. 2, the charging circuit 140 includes a capacitor 143, and the rotation of the main shaft of the gas turbine drives the permanent magnet 141 to rotate, and the permanent magnet 141 rotates to charge the capacitor 143 through a wire.

It will be appreciated that when the normally closed switch 113 is turned off, the capacitor 143 provides power to the pressure relief valve for draining hydraulic oil from the fourth chamber 713, thereby achieving non-actuation without the need for an external power source.

When the emergency braking device of the gas turbine is used, hydraulic oil in the normally closed loop control oil tank 15 is discharged into the burst pipe 901 and the third cavity 712 through the oil drain valve 803 and the oil inlet and outlet pipe 704, and the burst pipe 901 and the third cavity 712 are filled with the hydraulic oil.

When the gas turbine works, the main shaft 1 rotates to drive the permanent magnet 141 and the brake disc 201 to rotate, the capacitor 143 is charged, and meanwhile, the compressor 5 and the turbine 16 work and are discharged into the first cavity 405 through the first section 301 to form a gas source, so that a certain pressure is kept in the first cavity 405.

When braking is needed, a mode of oil drainage braking is preferably adopted, namely a normally closed switch 113 is turned off, the oil drainage valve 803 controls hydraulic oil in the fourth cavity 713 to be drained into the oil tank 15 through the oil inlet and outlet port 705, the oil inlet and outlet pipe 704 and the oil drainage valve 803, meanwhile, the piston rod 702 moves downwards along with the reduction of the hydraulic oil in the fourth cavity 713 until the shearing blade 407 penetrates through the shearing opening 408 and cuts off the shearing rope 402, the partition plate 403 rotates anticlockwise under the pressure in the first cavity 405, so that an air source provided by the air compressor 5 is drained into the pneumatic brake 2 through the first section 301, the first cavity 405, the second cavity 406 and the second section 302, the pneumatic brake 2 is started, the first friction plate 202 and the second friction plate 203 move towards the direction of the brake disc 201 and are contacted, braking is carried out, and meanwhile, the air source is drained from the first cooling branch 601 and the second cooling branch 602, and the first friction plate 202, the second friction plate 203 and the brake disc 201 are cooled, so that a better braking effect is achieved.

When the oil discharge braking mode fails and emergency braking cannot be performed, a bursting braking mode is adopted, namely, a normally open switch 112 is closed, a normally open loop is electrified, an explosion device is triggered and explosive 904 is detonated, after the explosive 904 is detonated, a burst pipe 901 is broken and the piston 701 is driven to move downwards, meanwhile, after the burst pipe 901 is broken, hydraulic oil enters a third cavity 712 through an oil inlet and outlet pipe 704 and a first connecting pipe 902, after the explosive 904 is detonated, the piston 701 is driven and drives a piston rod 702 and a shear blade 407 to move downwards, hydraulic oil in a fourth cavity 713 is discharged into the third cavity 712 through an oil inlet and outlet port 705, the oil inlet and outlet pipe 704 and a second connecting pipe 903 by an in-place baffle 703, hydraulic oil is rapidly filled into the third cavity 712 for rapidly pressurizing the piston 701, the piston 701 moves downwards until the shear blade 407 penetrates through the shear cut 408 and cuts off a shear rope 402, the baffle 403 rotates anticlockwise under the pressure in the first cavity 405, so that an air source provided by a compressor 5 is discharged into a pneumatic brake 2 through the first cavity 405, the second cavity 406 and the second cavity 302, the first friction plate 202 and the second friction plate 201 are cooled by the first and the second friction plate 203, and the friction plate 201 is cooled, and the friction plate is cooled and cooled by the second friction plate 201 and the friction plate is cooled.

The two emergency braking modes of the emergency braking device of the gas turbine in the embodiment of the invention are described above, and it can be understood that the oil release braking mode is preferentially selected when emergency braking is needed, and when the oil release braking mode fails and emergency braking cannot be performed, the explosion braking mode is adopted, that is, when the explosion braking mode is adopted, the oil release braking mode fails.

The gas turbine of the embodiment of the invention comprises a main shaft 1, a compressor 5 and the gas turbine emergency braking device of any embodiment.

The gas turbine provided by the embodiment of the invention has the advantages of high reliability and rapid braking.

An emergency braking method of a gas turbine according to an embodiment of the present invention is described below with reference to the accompanying drawings.

The emergency braking method of the gas turbine is implemented by using the emergency braking device of the gas turbine.

The emergency braking method of the gas turbine comprises the following steps:

a pneumatic brake 2 is arranged on a main shaft 1 of the gas turbine;

the pneumatic brake 2 is driven by gas generated by the compressor 5 of the gas turbine to brake the main shaft 1 of the gas turbine.

As shown in fig. 6, in the emergency braking method for a gas turbine according to the embodiment of the present invention, the pneumatic brake is disposed on the spindle 1, and the pneumatic brake 2 is driven by the gas generated by the gas compressor 5 of the gas turbine, so that the gas generated during the start of the gas turbine is used for braking the gas turbine, thereby realizing the non-actuation, and no additional gas source is required, that is, when the gas turbine needs to be braked, the gas in the gas compressor 5 is introduced into the pneumatic brake 2, so as to realize the braking of the gas turbine.

The emergency braking method of the gas turbine has the advantages of high reliability and rapid action.

As shown in fig. 7, the specific steps of the emergency braking method of the gas turbine of the above embodiment are as follows:

s101, a pneumatic brake 2 is arranged on a main shaft 1 of the gas turbine.

S102, driving the pneumatic brake 2 by using gas generated by the compressor 5 of the gas turbine.

S103, braking the main shaft 1 of the gas turbine by using the pneumatic brake 2.

a braking air path 3 is arranged between the air compressor 5 and the pneumatic brake 2;

a ventilation valve 4 is arranged on the brake air path 3;

the vent valve 4 is opened to actuate the pneumatic brake 2 using the gas generated by the compressor 5 of the gas turbine.

It will be appreciated that when the gas turbine is started, the compressor 5 charges a portion of the gas into the vent valve 4 and opens the vent valve 4, the compressor 5 charges gas into the pneumatic brake 2 to achieve a braking effect.

As shown in fig. 8, the specific steps of the emergency braking method of the gas turbine of the above embodiment are as follows:

s201, a pneumatic brake 2 is provided on the main shaft 1 of the gas turbine.

S202, a braking air path 3 is arranged between the compressor 5 and the pneumatic brake 2 of the gas turbine.

And S203, arranging a ventilation valve 4 on the brake air path 3.

S204, opening the ventilation valve 4.

S205, the gas turbine compressor 5 generates gas to drive the pneumatic brake 2.

S206, braking the main shaft 1 of the gas turbine by using the pneumatic brake 2.

a control valve 700 is arranged on the ventilation valve 4;

the control valve 700 is actuated to open the vent valve 4.

The emergency braking method of the gas turbine according to the embodiment of the invention opens the vent valve 4 by using the control valve 700, thereby facilitating the control of the vent valve 4. That is, after the control valve 700 is started, the vent valve 4 can be opened, and the vent valve 4 does not need a control component, so that the control component can not adversely affect the brake air path 3.

Further, the control valve 700 may be at least one of a hydraulic valve, a solenoid valve, or other control valve capable of opening the vent valve 4.

As shown in fig. 9, the specific steps of the emergency braking method of the gas turbine of the above embodiment are as follows:

s301, a pneumatic brake 2 is arranged on a main shaft 1 of the gas turbine.

S302, a braking air path 3 is arranged between the compressor 5 and the pneumatic brake 2 of the gas turbine.

S303, a ventilation valve 4 is arranged on the pneumatic controller 2.

And S304, setting a control valve 700 on the ventilation valve 4.

S305, opening the control valve 700.

S306, opening the ventilation valve 4.

S307, the pneumatic brake 2 is driven by the gas generated by the compressor 5 of the gas turbine.

And S308, braking the main shaft 1 of the gas turbine by using the pneumatic brake 2.

actuating the control valve 700 with the oil drain valve 803 or the detonator 12;

the power supply 110 is used to power the spill valve 803 and the detonator 12.

As shown in FIG. 10, in some embodiments, the gas turbine emergency braking method includes the following specific steps:

s401, a pneumatic brake 2 is provided on the main shaft 1 of the gas turbine.

S402, a braking air path 3 is arranged between a compressor 5 and a pneumatic brake 2 of the gas turbine.

S403, the ventilation valve 4 is arranged on the pneumatic controller 2.

S404, a control valve 700 is arranged on the ventilation valve 4.

S405, power is supplied to the oil drain valve 803 by the power supply 110.

S406, the control valve 700 is started by the drain valve 803.

S409, the control valve 700 is started.

S410, opening the ventilation valve 4.

S411, the pneumatic brake 2 is driven by the gas generated by the compressor 5 of the gas turbine.

S412, braking the main shaft 1 of the gas turbine by using the pneumatic brake 2.

It can be understood that the above steps are the oil-release braking mode of the emergency braking method of the gas turbine in the embodiment of the invention, thereby ensuring the repeated use of the control valve 4 and improving the use efficiency.

As shown in FIG. 10, in other embodiments, the gas turbine emergency braking method includes the following specific steps:

s401, a pneumatic brake 2 is provided on the main shaft 1 of the gas turbine.

S403, the ventilation valve 4 is arranged on the pneumatic controller 2.

S404, a control valve 700 is arranged on the ventilation valve 4.

S407, power is supplied to the detonator 12 by the power supply 110.

S408, the control valve 700 is actuated by the detonator 12.

S409, the control valve 700 is started.

S410, opening the ventilation valve 4.

It can be understood that the above steps are burst braking modes of the emergency braking method of the gas turbine according to the embodiment of the present invention, that is, the emergency braking method of the gas turbine according to the embodiment of the present invention has two emergency braking methods, and the oil release braking mode is preferentially selected when emergency braking is required, and when the oil release braking mode fails, the burst braking mode is adopted, that is, when the emergency braking cannot be performed, the oil release braking mode fails.

charging the power supply 110 with a power generation device;

the power generation device is driven by the main shaft 1 of the gas turbine.

As shown in FIG. 11, in some embodiments, the gas turbine emergency braking method includes the following specific steps:

s501, a pneumatic brake 2 is provided on the main shaft 1 of the gas turbine.

S502, a braking air path 3 is arranged between the compressor 5 and the pneumatic brake 2 of the gas turbine.

S503, arranging a ventilation valve 4 on the pneumatic controller 2.

S504, a control valve 700 is provided to the vent valve 4.

S505, a power generation device is arranged on the main shaft 1 of the gas turbine.

S506, the power supply 110 is charged by the power generation device.

S507, power is supplied to the drain valve 803 by the power supply 110.

S508, the control valve 700 is started by the drain valve 803.

S511, the control valve 700 is started.

S512, opening the ventilation valve 4.

S513, the pneumatic brake 2 is driven by the gas generated by the compressor 5 of the gas turbine.

S514, braking the main shaft 1 of the gas turbine by using the pneumatic brake 2.

As shown in FIG. 11, in other embodiments, the gas turbine emergency braking method includes the following specific steps:

s501, a pneumatic brake 2 is provided on the main shaft 1 of the gas turbine.

S503, arranging a ventilation valve 4 on the pneumatic controller 2.

S504, a control valve 700 is provided to the vent valve 4.

S506, the power supply 110 is charged by the power generation device.

S509, power is supplied to the detonator 12 by the power supply 110.

S510, the control valve 700 is actuated by the detonator 12.

S511, the control valve 700 is started.

S512, opening the ventilation valve 4.

S514, braking the main shaft 1 of the gas turbine by using the pneumatic brake 2. That is, the gas turbine is started, the main shaft 1 rotates and charges the power supply 110 through the power generation device to ensure that the power supply 110 supplies power to the oil drain valve 803 and the detonation device 12, thereby achieving braking of the gas turbine.

Therefore, the emergency braking method of the gas turbine can realize braking under the condition that no external energy source is provided.

In the description of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", "axial", "radial", "circumferential", etc. indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings are merely for convenience in describing the present invention and simplifying the description, and do not indicate or imply that the device or element being referred to must have a specific orientation, be configured and operated in a specific orientation, and therefore should not be construed as limiting the present invention.

Furthermore, the terms "first," "second," and the like, are used for descriptive purposes only and are not to be construed as indicating or implying a relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defining "a first" or "a second" may explicitly or implicitly include at least one such feature. In the description of the present invention, the meaning of "plurality" means at least two, for example, two, three, etc., unless specifically defined otherwise.

In the present invention, unless explicitly specified and limited otherwise, the terms "mounted," "connected," "secured," and the like are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally formed; may be mechanically connected, may be electrically connected or may be in communication with each other; either directly or indirectly, through intermediaries, or both, may be in communication with each other or in interaction with each other, unless expressly defined otherwise. The specific meaning of the above terms in the present invention can be understood by those of ordinary skill in the art according to the specific circumstances.

In the present invention, unless expressly stated or limited otherwise, a first feature "up" or "down" a second feature may be the first and second features in direct contact, or the first and second features in indirect contact via an intervening medium. Moreover, a first feature being "above," "over" and "on" a second feature may be a first feature being directly above or obliquely above the second feature, or simply indicating that the first feature is level higher than the second feature. The first feature being "under", "below" and "beneath" the second feature may be the first feature being directly under or obliquely below the second feature, or simply indicating that the first feature is less level than the second feature.

For purposes of this disclosure, the terms "one embodiment," "some embodiments," "example," "a particular example," or "some examples," etc., mean that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the invention. In this specification, schematic representations of the above terms are not necessarily directed to the same embodiment or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples. Furthermore, the different embodiments or examples described in this specification and the features of the different embodiments or examples may be combined and combined by those skilled in the art without contradiction.

While embodiments of the present invention have been shown and described above, it will be understood that the above embodiments are illustrative and not to be construed as limiting the invention, and that variations, modifications, alternatives and variations may be made to the above embodiments by one of ordinary skill in the art within the scope of the invention.

Claims

1. An emergency braking apparatus for a gas turbine, comprising:

A pneumatic brake adapted to be provided on a main shaft of the gas turbine;

the ventilation valve is arranged on the brake air passage and is used for stopping or conducting the brake air passage so as to control the pneumatic brake;

the ventilation valve comprises a ventilation valve cavity and a baffle plate, and the baffle plate is movably arranged in the ventilation valve cavity between a closed position and an open position so as to stop or conduct the brake gas path;

the air vent valve cavity comprises a first cavity and a second cavity, the brake air passage comprises a first section and a second section, one end of the first section is suitable for being connected with a gas compressor of the gas turbine, the other end of the first section is communicated with the first cavity, so that the gas compressor of the gas turbine is used for introducing gas into the first cavity, one end of the second section is communicated with the second cavity, the other end of the second section is connected with the pneumatic brake, and the partition board is rotatably arranged in the air vent valve cavity between a closing position and an opening position so as to cut off or conduct the brake air passage.

2. The gas turbine emergency brake apparatus of claim 1, wherein the vent valve further comprises a shear line,

when the baffle plate is in the closed position, the shear rope is connected between the baffle plate and the wall surface of the first cavity, the baffle plate is positioned between the first cavity and the second cavity in the axial direction of the main shaft of the gas turbine so as to block the first cavity and the second cavity,

3. The emergency braking apparatus of a gas turbine according to claim 2, further comprising a shear blade, the vent valve further comprising a shear blade provided on a wall surface of the first chamber, the shear blade being capable of communicating the first chamber with the outside, and a sealing plug provided in the shear blade to block the shear blade, the shear blade corresponding to the shear blade, and the shear blade being movably provided in an axial direction of the shear blade so as to pass through the sealing plug to thereby cut the shear rope.

4. The gas turbine emergency brake apparatus of claim 3, further comprising a control valve including a control valve chamber, a piston and a piston rod, the piston being movably disposed in the control valve chamber in an axial direction of the cutout, the control valve chamber including a third chamber and a fourth chamber, the piston being located between the third chamber and the fourth chamber in the axial direction of the cutout to block the third chamber and the fourth chamber, one end of the piston rod being located in the fourth chamber, and the one end of the piston rod being connected to the piston, the cutout being disposed on an end face of the other end of the piston rod.

5. The emergency braking apparatus of a gas turbine of claim 4, further comprising an oil injection pipeline, an oil drain pipeline and an oil drain valve, wherein the control valve further comprises an oil inlet and an oil outlet, one end of the oil inlet and outlet is communicated with the fourth cavity through the oil inlet and outlet, the other end of the oil inlet and outlet is connected with the oil injection pipeline and the oil drain pipeline, and the oil drain valve is arranged on the oil drain pipeline.

6. The gas turbine emergency brake apparatus of claim 5, further comprising a bursting tube, a first connecting tube, a second connecting tube, and an explosive, said bursting tube and said explosive being disposed in said fourth chamber, and said bursting tube and said explosive being disposed adjacent such that said explosive bursts said bursting tube, one end of said bursting tube being in communication with said oil inlet and outlet tube through said first connecting tube, and the other end of said bursting tube being in communication with said oil inlet and outlet tube through said second connecting tube.

7. The emergency braking apparatus of a gas turbine of claim 6, further comprising a power source and a detonation device, wherein the oil drain valve is an electromagnetic valve, the oil drain valve is connected with the power source through an oil drain circuit, a normally closed switch is arranged on the oil drain circuit, the detonation device is used for detonating the explosive, the detonation device is connected with the power source through a detonation circuit, and a normally open switch is arranged on the detonation circuit.

8. The gas turbine emergency brake apparatus of claim 7, further comprising a power generation device and a charging circuit, the power generation device comprising a permanent magnet adapted to be disposed on a main shaft of the gas turbine and a coil connected to the power source through the charging circuit.

9. The gas turbine emergency brake apparatus of any of claims 1-8, wherein the pneumatic brake includes a brake disk, a first friction plate, and a second friction plate, the brake disk adapted to be disposed on a main shaft of the gas turbine, the first friction plate and the second friction plate being opposite in an axial direction of the brake disk, and a portion of the brake disk being located between the first friction plate and the second friction plate in the axial direction of the brake disk.

10. The gas turbine emergency brake apparatus of claim 9, further comprising a first cooling branch and a second cooling branch, an air inlet end of each of the first cooling branch and the second cooling branch being in communication with the second section of the brake air path, an air outlet end of the first cooling branch being provided on one of the first friction plate and the second friction plate, and an air outlet end of the second cooling branch being provided on the other of the first friction plate and the second friction plate.

11. A gas turbine, comprising: a main shaft, a compressor and an emergency braking apparatus as claimed in any one of claims 1 to 10.

12. A gas turbine emergency braking method, characterized in that a gas turbine emergency braking device as defined in any one of claims 1 to 10 is used, comprising the steps of:

a pneumatic brake is arranged on a main shaft of the gas turbine;

13. The gas turbine emergency braking method of claim 12, further comprising the steps of:

a ventilation valve is arranged on the braking air path;

14. The gas turbine emergency braking method of claim 13, wherein the opening the vent valve comprises: cutting the shear line to rotate the diaphragm to the open position.

15. The gas turbine emergency braking method of claim 14, wherein the opening the vent valve further comprises: the shear blade is moved to sever the shear line.

16. The gas turbine emergency braking method of any of claims 13 to 15, further comprising the steps of:

a control valve is arranged on the ventilation valve;

and starting the control valve, so as to open the ventilation valve.

17. The gas turbine emergency braking method of claim 16, further comprising the steps of:

starting the control valve by using an oil drain valve or a detonation device;

18. The gas turbine emergency braking method of claim 17, further comprising the steps of:

a power generation device is arranged on a main shaft of the gas turbine;

and charging the power supply by using a power generation device.