CN113982763A

CN113982763A - Gas turbine emergency braking device and method

Info

Publication number: CN113982763A
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: 2022-01-28
Anticipated expiration: 2041-10-14
Also published as: CN113982763B

Abstract

The invention provides an emergency braking device and method for a gas turbine, wherein the emergency braking method for the gas turbine comprises the following steps: arranging a pneumatic brake on a main shaft of the gas turbine; and driving the pneumatic brake by using gas generated by a compressor of the gas turbine so as to brake the main shaft of the gas turbine. The emergency braking method of the gas turbine has the advantages of high reliability and quick action.

Description

Gas turbine emergency braking device and method

Technical Field

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

Background

Gas turbines are high speed rotating equipment that can cause severe damage to the combustion engine if the rotational speed rises to an unacceptable level. In the related art, the overspeed protection of the gas turbine is mainly realized by setting a threshold value and then assisting a manual emergency stop button. If the rotating speed is larger than the threshold value, a trip signal is generated and sent to a hardware line trip link to interrupt the gas turbine. The manual emergency stop and the automatic trip share a part of trip circuits, the manual emergency stop and the automatic trip are not completely independent, the mechanisms are similar, and the possibility of common-mode faults exists; if the trip link fails, the gas turbine will overspeed. And after the trip link acts to cut off fuel, the gas turbine can only wait for the speed reduction, and the active braking cannot be carried out.

Disclosure of Invention

The present invention is directed to solving, at least to some extent, one of the technical problems in the related art.

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

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

The gas turbine emergency braking device of the embodiment of the invention comprises:

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

a brake gas circuit adapted to be connected between the pneumatic brake and a compressor of the gas turbine to supply gas to the pneumatic brake;

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

The gas turbine emergency braking device provided by the embodiment of the invention utilizes the gas generated by the gas compressor of the gas turbine to drive the pneumatic brake to brake, does not depend on external power or energy, can realize the intrinsically safe braking of the gas turbine, and has good reliability.

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

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

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

In some embodiments, the vent valve further comprises a cutting rope, the vent valve cavity comprises a first cavity and a second cavity, the brake gas path comprises a first section and a second section, one end of the first section is suitable for being connected with a compressor of the gas turbine, the other end of the first section is communicated with the first cavity, so that the compressor of the gas turbine can introduce 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 partition plate is rotatably arranged in the vent valve cavity between a closing position and an opening position so as to stop or conduct the brake gas path,

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

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

In some embodiments, the emergency braking device for a gas turbine according to the embodiments of the present invention further includes a shear knife, the vent valve further includes a shear port and a sealing plug, the shear port is disposed on a wall surface of the first cavity, the shear port is capable of communicating the first cavity with the outside, the sealing plug is disposed in the shear port to seal the shear port, the shear knife corresponds to the shear port, and the shear knife is movably disposed along an axial direction of the shear port to penetrate through the sealing plug to cut off the shear string.

In some embodiments, the emergency braking device for a gas turbine according to the embodiments of the present invention further includes a control valve, where the control valve includes a control valve cavity, a piston, and a piston rod, the piston is movably disposed in the control valve cavity along the axial direction of the shear port, the control valve cavity includes a third cavity and a fourth cavity, the piston is located between the third cavity and the fourth cavity in the axial direction of the shear port to block the third cavity and the fourth cavity, one end of the piston rod is located in the fourth cavity, the one end of the piston rod is connected to the piston, and the shear knife is 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 embodiments of the present 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 outlet pipe and an oil inlet and outlet port, one end of the oil inlet and outlet pipe is communicated with the fourth cavity through the oil inlet and outlet port, the other end of the oil inlet and outlet pipe is connected to the oil injection pipeline and the oil drain pipeline, and the oil drain valve is disposed on the oil drain pipeline.

In some embodiments, the gas turbine emergency braking device according to the embodiments of the present invention further includes a bursting tube, a first connecting tube, a second connecting tube, and an explosive, where 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 can burst 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 a gas turbine according to the embodiments of the present invention further includes a power supply and a detonation device, the oil drain valve is a solenoid valve, the oil drain valve is connected to the power supply through an oil drain circuit, the oil drain circuit is provided with a normally closed switch, the detonation device is used for detonating the explosive, the detonation device is connected to the power supply through a detonation circuit, and the detonation circuit is provided with a normally open switch.

In some embodiments, the gas turbine emergency braking device of the embodiment of the invention further comprises a power generation device and a charging circuit, wherein the power generation device comprises a permanent magnet and a coil, the permanent magnet is suitable for being arranged on the main shaft, and the coil is connected with the power supply through the charging circuit.

In some embodiments, the pneumatic brake includes a brake disc adapted to be provided on the main shaft, a first friction plate and a second friction plate that are opposed to 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 braking device of the embodiments of the present invention 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 communicated with the second section of the braking 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.

A gas turbine according to an embodiment of the present invention includes: the main shaft, the compressor and the emergency braking device in any one of the embodiments.

The emergency braking method of the gas turbine provided by the embodiment of the invention comprises the following steps of:

arranging a pneumatic brake on a main shaft of the gas turbine;

and driving the pneumatic brake by using gas generated by a compressor of the gas turbine so as to brake the main shaft of the gas turbine.

In some embodiments, the gas turbine emergency braking method of embodiments 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;

and opening the ventilation valve so as to drive the pneumatic brake by using the gas generated by the compressor of the gas turbine.

In some embodiments, said opening said vent valve comprises: the shear line is cut to rotate the diaphragm to an open position.

In some embodiments, said opening said vent valve further comprises: moving a cutting knife to cut the cutting string.

In some embodiments, further comprising the steps of:

a control valve is arranged on the ventilation valve;

activating the control valve to open the vent valve.

In some embodiments, further comprising the steps of:

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

and a power supply is used for supplying power to the oil drain valve and the detonating device.

In some embodiments, 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.

Drawings

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

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

Fig. 3 is an enlarged view of a portion 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 method for emergency braking of a gas turbine in accordance with an embodiment of the present invention.

FIG. 7 is a schematic flow chart illustrating a method for emergency braking of a gas turbine according to an embodiment of the present invention.

FIG. 8 is a schematic flow chart illustrating a method for emergency braking of a gas turbine according to an embodiment of the present invention.

FIG. 9 is a schematic flow chart illustrating a method for emergency braking of a gas turbine according to an embodiment of the present invention.

FIG. 10 is a schematic flow chart illustrating a method for emergency braking of a gas turbine according to an embodiment of the present invention.

FIG. 11 is a schematic flow chart illustrating a method for emergency braking of a gas turbine according to an embodiment of the present 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 gas circuit 3; a first segment 301; a second segment 302;

a vent valve 4; a breather valve cavity 401; a shear line 402; a partition 403; a first cavity 405; a second cavity 406; a shearing knife 407; a shear port 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 baffle 703; an oil inlet pipe 704; an oil inlet and outlet 705;

a third chamber 712; a fourth chamber 713;

an oil injection line 801; an oil drain line 802; an oil relief valve 803;

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

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

an explosive device 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 with reference to the drawings are illustrative and intended to be illustrative of the invention and are not to be construed as limiting the invention.

The gas turbine emergency brake apparatus of the embodiment of the present invention is described below with reference to the accompanying drawings.

As shown in fig. 1, the gas turbine emergency brake apparatus according to the embodiment of the present invention includes: the pneumatic brake 2, the brake gas circuit 3 and the vent valve 4.

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

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

That is to say, the vent valve 4 can be a common valve, and a user can actively open the vent valve 4 for braking, and can also use other control structures to control the start and stop 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 the 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 disc 202 is located on the left side of the brake disc 201, the second friction disc 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 rotate synchronously, and when braking is needed, the pneumatic brake 2 is started to enable the first friction disc 202 and the second friction disc 203 to squeeze the brake disc 201, so that the purpose of braking is achieved.

It can be understood 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 string 402, and a partition 403. The vent valve chamber 401 includes a first chamber 405 and a second chamber 406.

The brake gas circuit 3 comprises a first section 301 and a second section 302, one end of the first section 301 is suitable for being connected with a gas 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 plate 403 is rotatably arranged in the ventilation valve cavity 401 between a closed position and an open position, and the extension direction of the main axis of the partition plate 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 be connected to the compressor 5, the left end of the first section 301 is in communication with the first chamber 405, the right end of the second section 302 is in communication 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 main shaft 1 to block the first chamber 405 and the second chamber 406.

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

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

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

It can be appreciated that, as shown in fig. 2 and 5, when the partition 403 is in the closed position, the partition 403 separates the first chamber 405 and the second chamber 406 under the pulling force of the shear rope 402, and when braking is required, the shear rope 402 is disconnected, the partition 403 is rotated counterclockwise by the pressure of the gas in the first chamber 405 to connect the first chamber 405 and the second chamber 406, and then the gas source enters the pneumatic brake 2 through the first section 301, the first chamber 405, the second chamber 406 and the second section 302 to move the first friction plate 202 and the second friction plate 203 toward the brake disc 201 and press the brake disc 201 to perform braking, so as to achieve the active braking function, thereby increasing the safety of the present invention.

After the gas turbine is started, the gas compressor of the gas turbine works, the gas compressor of the gas turbine continuously fills gas into the first cavity 405 through the first section 301 until the gas turbine operates stably, namely, the rotating speed of the main shaft of the combustion area turbine keeps unchanged, the gas compressor of the gas turbine fills gas into the first cavity 405 and maintains certain pressure, and the gas pressure in the first cavity 405 is not enough to break the shearing rope 402.

That is, under the same condition, the higher the rotation speed of the main shaft of the gas turbine is, the more gas the compressor of the gas turbine charges into the first cavity 405, so that the gas pressure in the first cavity 405 is higher, and thus the higher the gas pressure provided to the pneumatic brake 2 is, the higher the braking power generated by the pneumatic brake 2 is. That is, the braking power generated by the pneumatic brake 2 is changed according to the change of the rotation speed of the gas turbine main shaft.

Specifically, when the shear line 402 is disconnected, the separator 403 is rapidly rotated counterclockwise by the gas pressure of the first chamber 405, and the gas in the first chamber 405 is introduced into the pneumatic brake 2 through the first chamber 405, the second chamber 406 and the second segment inlet 302, so that the first friction plate 202 and the second friction plate 203 press the brake disc 201, thereby rapidly braking the gas turbine.

In some embodiments, as shown in fig. 2 and 3, the gas turbine emergency braking apparatus of the embodiments of the present invention further includes a first cooling branch 601 and a second cooling branch 602. An 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, an air outlet end of the first cooling branch 601 is provided on one of the first friction plate 202 and the second friction plate 203, and an air outlet end of the second cooling branch 602 is provided on the other of the first friction plate 202 and the second friction plate 203.

That is, the air intake end of the first cooling branch 601 communicates with the second section 302 of the brake air path 3, and the air intake 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 discharged from the gas outlet end of the first cooling branch 601 can cool the left end surface of the brake disc 201, and the gas discharged from the gas outlet end of the second cooling branch 602 can cool the right end surface of the brake disc 201.

In some embodiments, as shown in fig. 2, 4 and 5, the gas turbine emergency braking device of embodiments of the present invention further comprises a shear knife 407. The vent valve 4 further comprises a cutting opening 408, a sealing plug 409 is arranged on the cutting opening, the cutting opening 408 is communicated with the first cavity 405 and the outside, the cutting knife 407 corresponds to the cutting opening 408, and the cutting knife 407 is movably arranged along the axial direction of the cutting opening 408 so as to cut off the cutting rope 402, and the axial direction of the cutting opening 408 is perpendicular to the extension direction of the main axis of the partition 403.

Specifically, the shearing knife 407 is located above the shearing opening 408, when braking is needed, the shearing knife 407 moves downward, the lower end of the shearing knife 407 penetrates through the shearing opening 408 into the first cavity 405, the shearing rope 402 is cut off, the partition 403 rotates counterclockwise, 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 for braking.

It will be appreciated that when the gas turbine is rotating, the compressor of the gas turbine discharges the air source into the first cavity 405 through the first section 301 to maintain a certain pressure in the first cavity 405, and after the shear line 402 is cut off, the diaphragm 403 rotates counterclockwise under the pressure in the first cavity 405 to connect the first cavity 405 and the second cavity 406, so as to charge the air into the pneumatic brake 2, thereby generating a braking effect. Therefore, when braking is needed, braking can be rapidly performed.

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, and the control valve 700 includes a control valve cavity, a piston 701 and a piston rod 702.

The piston 701 is movably disposed in the control valve chamber including a third chamber 712 and a fourth chamber 713 in the axial direction of the shear port 408. The piston 701 is located between the third cavity 712 and the fourth cavity 713 in the axial direction of the shearing opening 408 to block the third cavity 712 and the fourth cavity 713, one end of the piston rod 702 is located in the fourth cavity 713, one end of the piston rod 702 is connected with the piston 701, and the shearing knife 407 is arranged on the end face of the other end of the piston rod 702.

The piston rod 702 is provided with an in-position baffle 703, and the in-position 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, the piston 701 keeps the third chamber 712 and the fourth chamber 713 in a sealed state during moving, the upper end of the piston rod 702 is connected with the piston 701, and the lower end of the piston rod 702 is connected with the shearing knife 407. Therefore, when braking is needed, the piston moves downwards under the action of external force and accelerates downwards under the action of self gravity, so that the time required for the piston 701 to descend is shortened, and the efficiency is improved.

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

It is understood that the oil used in the gas turbine emergency brake device of the embodiment of the present invention may be hydraulic oil.

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

Specifically, hydraulic oil in the oil filling pipeline 801 flows through the oil inlet/outlet pipe 704 and the oil inlet/outlet port 705, the hydraulic oil is filled into the fourth cavity 713, the liquid level of the hydraulic oil in the fourth cavity 713 rises, the in-place baffle 703 moves upwards, the piston 701 is driven 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 discharge the hydraulic oil in the fourth cavity 713 into the oil tank 15 through the oil inlet/outlet 705, the oil inlet/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 knife 407 to move downwards, the lower end of the shearing knife 407 penetrates through the shearing hole and cuts off the shearing rope 402, the partition plate 403 is in the opening 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 braking apparatus according to the embodiment of the present invention further includes a bursting tube 901, a first connecting tube 902, a second connecting tube 903 and an explosive 904, the bursting tube 901 and the explosive 904 are disposed in the fourth cavity 713, and the bursting tube 901 and the explosive 904 are disposed adjacent to each other so that the explosive 904 bursts the bursting tube 901, one end of the bursting tube 901 is communicated with the oil inlet/outlet pipe 704 through the first connecting tube 902, and the other end of the bursting tube 901 is communicated with the oil inlet/outlet pipe 704 through the second connecting tube 903.

As shown in fig. 2 and 4, explosive 904 is disposed above the bursting tube 901, the bursting tube 901 is disposed above the piston 701, the bursting tube 901 is made of a fragile material, such as glass, the explosive 904 is an explosive, when the explosive 904 is detonated, the explosive is detonated in the third chamber 712, the explosive energy shatters the burst tube 901, and after the burst tube 901 is broken, hydraulic oil enters the third cavity 712 through the oil inlet/outlet pipe 704 and the first connecting pipe 902, the explosive 904 is detonated to drive the piston 701 and drive the piston rod 702 and the shearing knife 407 to move downwards, the positioning baffle 703 discharges the hydraulic oil in the fourth chamber 713 to the third chamber 712 through the oil inlet/outlet 705, the oil inlet/outlet pipe 704 and the second connecting pipe 903, so that the third chamber 712 is quickly filled with the hydraulic oil, the pressure is applied to the piston 701 quickly, so that the piston 701 moves downward quickly, and thus the braking effect is achieved more quickly, and the process is a burst braking mode.

It can be understood that the energy released by the explosive explosion can 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 to 4, the gas turbine emergency braking device according to the embodiments of the present invention further includes a power supply 110 and a detonating device 12, 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, the oil drain circuit 111 is provided with a normally closed switch 113, the detonating device 12 is used for detonating an explosive 904, the detonating device 12 is connected to the power supply 110 through a detonating circuit 114, and the detonating circuit 114 is provided with a normally open switch 112.

As shown in fig. 2-5, the power source 110, the oil drain valve 803, the normally closed switch 113 and the oil drain circuit 111 form a normally closed circuit, that is, when the normally closed circuit is powered on, the oil filling pipe 801 fills hydraulic oil into the fourth cavity 713 through the oil inlet/outlet pipe 704 and the oil inlet/outlet port 705, and the normally closed switch 113 is turned off, the oil drain valve 803 controls the oil drain circuit 802, so that the hydraulic oil in the fourth cavity 713 is drained into the oil tank 15 through the oil inlet/outlet port 705, the oil inlet/outlet pipe 704 and the oil drain pipe 802, the hydraulic oil level in the fourth cavity 713 is lowered, the piston 701 drives the piston rod 702 and the shearing knife 407 to move downward, the shearing knife 407 penetrates through the shearing port 408 and the 409, the shearing rope 402 is sheared, and the gas in the first cavity 405 is led into the pneumatic brake 2 through the second cavity 406 and the second section 302, so as to perform braking. The power source 110, the detonation circuit 114, the normally open switch 112 and the detonation device 12 form a normally open loop, that is, when the normally open switch 112 is closed, the normally open loop is energized to control the detonation device 12 to detonate the explosive 904, so that the detonation tube 901 is ruptured, hydraulic oil in the oil inlet/outlet pipe 704 is discharged into the third cavity 713 through the first connecting pipe 902, the 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 greater than the pressure of the hydraulic oil in the fourth cavity 713 acting on the in-place baffle 703, the piston 701 moves downward, the hydraulic oil in the fourth cavity 713 is discharged into the third cavity 912 through the second connecting pipe 903, the hydraulic oil level in the fourth cavity 713 is rapidly lowered, the piston 701 drives the piston rod 702 and the shear knife 407 to move downward, the shear knife 407 penetrates through the sealing plug 409 through the shear port 408 to shear 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, thereby performing braking.

Therefore, the gas turbine emergency braking device provided by the embodiment of the invention provides two emergency braking modes, thereby improving the reliability of the invention.

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

As shown in fig. 2, the charging circuit 140 includes a capacitor 143, 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 the line.

It is understood that when the normally closed switch 113 is turned off, the capacitor 143 provides power to the pressure relief valve to discharge the hydraulic oil in the fourth chamber 713, so that the passive operation is realized without an external power supply.

When the emergency braking device for the gas turbine according to the embodiment of the present invention is in use, the hydraulic oil in the normally closed circuit control oil tank 15 is discharged into the bursting tube 901 and the third chamber 712 through the oil relief valve 803 and the oil inlet/outlet pipe 704, and the bursting tube 901 and the third chamber 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 gas compressor 5 and the turbine 16 work and discharge a gas source into the first cavity 405 through the first section 301, so that a certain pressure is kept in the first cavity 405.

When braking is needed, an oil drainage braking mode is preferentially adopted, namely, the normally closed switch 113 is turned off, the oil drainage valve 803 controls hydraulic oil in the fourth cavity 713 to be discharged into the oil tank 15 through the oil inlet/outlet port 705, the oil inlet/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 knife 407 penetrates through the shearing port 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 compressor 5 is discharged 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 brake disc 201 and are contacted to brake, meanwhile, the air source is discharged from the first cooling branch 601 and the second cooling branch 602 to cool the first friction plate 202, the second friction plate 203 and the brake disc 201, so as to achieve better braking effect.

When the oil drainage braking mode fails and emergency braking cannot be performed, a blasting braking mode is adopted, namely the normally open switch 112 is closed, the normally open loop is electrified, the explosion device is triggered to detonate the explosive 904, the explosion tube 901 is shattered after the explosive 904 is detonated and drives the piston 701 to move downwards, meanwhile, after the explosion tube 901 is shattered, 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 and drives the piston rod 702 and the shearing knife 407 to move downwards after the explosive 904 is detonated, the in-place baffle 703 discharges the hydraulic oil in the fourth cavity 713 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, so that the hydraulic oil is rapidly filled into the third cavity 712 to rapidly apply pressure to the piston 701, the piston 701 rapidly moves downwards until the shearing knife 407 penetrates through the shearing port 408 and cuts off the shearing rope 402, and the partition 403 rotates anticlockwise under the pressure in the first cavity 405, therefore, air supply provided by the compressor 5 is discharged 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 brake disc 201 and are contacted with each other for braking, and the air supply is discharged from the first cooling branch 601 and the second cooling branch 602 to cool the first friction plate 202, the second friction plate 203 and the brake disc 201.

The two emergency braking modes of the emergency braking device for the gas turbine in the embodiment of the invention are described above, and it can be understood that the oil drainage braking mode is preferentially selected when emergency braking is required, and when the oil drainage 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 drainage 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 one of the embodiments.

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

A gas turbine emergency braking method of an embodiment of the present invention is described below with reference to the drawings.

The emergency braking method of the gas turbine of the embodiment of the invention 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 gas generated by the compressor 5 of the gas turbine is used to drive the pneumatic brake 2 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 main shaft 1, and the pneumatic brake 2 is driven by using the gas generated by the compressor 5 of the gas turbine, so that the gas generated when the gas turbine is started can be used for braking the gas turbine itself, thereby realizing non-activity, and no additional gas source is needed, that is, when the gas turbine needs to be braked, the gas in the compressor 5 is introduced into the pneumatic brake 2, thereby realizing braking of the gas turbine.

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

As shown in fig. 7, the method for emergency braking of a gas turbine according to the above embodiment includes the following specific steps:

and S101, arranging an air brake 2 on a main shaft 1 of the gas turbine.

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

S103, the main shaft 1 of the gas turbine is braked by 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 gas circuit 3;

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

It can be understood that when the gas turbine is started, the compressor 5 charges part of the gas into the vent valve 4, and when the vent valve 4 is opened, the compressor 5 charges the gas into the pneumatic brake 2 to realize the braking effect.

As shown in fig. 8, the method for emergency braking of a gas turbine according to the above embodiment includes the following specific steps:

s201, arranging an air brake 2 on a main shaft 1 of the gas turbine.

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

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

And S204, opening the ventilation valve 4.

And S205, driving the pneumatic brake 2 by using gas generated by the compressor 5 of the gas turbine.

S206, the main shaft 1 of the gas turbine is braked by 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 present invention opens the vent valve 4 using the control valve 700, thereby facilitating the control of the vent valve 4. That is to say, after the control valve 700 is started, the vent valve 4 can be opened along with the control valve, and the vent valve 4 does not need a control component, so that the control component is prevented from generating adverse effects on the braking air circuit 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 method for emergency braking of a gas turbine according to the above embodiment includes the following specific steps:

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

And S302, arranging a braking air circuit 3 between a compressor 5 and a pneumatic brake 2 of the gas turbine.

And S303, arranging a ventilation valve 4 on the pneumatic controller 2.

S304, the control valve 700 is provided to the vent valve 4.

S305, opening the control valve 700.

S306, opening the ventilation valve 4.

And S307, driving the pneumatic brake 2 by using the gas generated by the compressor 5 of the gas turbine.

S308, the main shaft 1 of the gas turbine is braked by the pneumatic brake 2.

the control valve 700 is actuated by either the bleeder valve 803 or the detonator 12;

the oil release valve 803 and the detonator 12 are powered by the power source 110.

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

and S401, arranging an air brake 2 on a main shaft 1 of the gas turbine.

And S402, arranging a braking air circuit 3 between a compressor 5 and a pneumatic brake 2 of the gas turbine.

And S403, arranging a ventilation valve 4 on the pneumatic controller 2.

And S404, arranging a control valve 700 on the ventilation valve 4.

S405, the power supply 110 supplies power to the oil relief valve 803.

S406, the control valve 700 is actuated by the relief valve 803.

And S409, starting the control valve 700.

And S410, opening the ventilation valve 4.

And S411, driving the pneumatic brake 2 by using gas generated by the compressor 5 of the gas turbine.

S412, the main shaft 1 of the gas turbine is braked by the pneumatic brake 2.

It can be understood that the steps are the oil drainage braking mode of the emergency braking method of the gas turbine, the reuse of the control valve 4 is ensured, and the use efficiency is improved.

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

and S401, arranging an air brake 2 on a main shaft 1 of the gas turbine.

And S403, arranging a ventilation valve 4 on the pneumatic controller 2.

And S404, arranging a control valve 700 on the ventilation valve 4.

S407, the power supply 110 supplies power to the ignition device 12.

S408, the control valve 700 is activated by the igniter 12.

And S409, starting the control valve 700.

And S410, opening the ventilation valve 4.

S412, the main shaft 1 of the gas turbine is braked by the pneumatic brake 2.

It can be understood that the above steps are the explosion braking mode of the gas turbine emergency braking method in the embodiment of the present invention, that is, the gas turbine emergency braking method in the embodiment of the present invention has two emergency braking methods, the oil drainage braking mode is preferentially selected when emergency braking is required, and when the oil drainage braking mode fails and emergency braking cannot be performed, the explosion braking mode is adopted again, that is, when the explosion braking mode is adopted, the oil drainage braking mode fails.

charging the power source 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 steps:

and S501, arranging an air brake 2 on the main shaft 1 of the gas turbine.

And S502, arranging a braking air circuit 3 between a compressor 5 and a pneumatic brake 2 of the gas turbine.

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

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

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

And S506, charging the power supply 110 by using the power generation device.

And S507, supplying power to the oil relief valve 803 by using the power supply 110.

S508, the control valve 700 is actuated by the relief valve 803.

And S511, starting the control valve 700.

S512, opening the ventilation valve 4.

And S513, driving the pneumatic brake 2 by using the gas generated by the compressor 5 of the gas turbine.

And 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 comprises the following specific steps:

and S501, arranging an air brake 2 on the main shaft 1 of the gas turbine.

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

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

And S506, charging the power supply 110 by using the power generation device.

S509, the power supply 110 supplies power to the ignition device 12.

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

And S511, starting the control valve 700.

S512, opening the ventilation valve 4.

And 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 source 110 through the power generation device to ensure that the power source 110 supplies power to the oil drain valve 803 and the igniter 12, thereby achieving braking of the gas turbine.

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

In the description of the present invention, it is to be understood that the terms "central," "longitudinal," "lateral," "length," "width," "thickness," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," "clockwise," "counterclockwise," "axial," "radial," "circumferential," and the like are used in the orientations and positional relationships indicated in the drawings for convenience in describing the invention and to simplify the description, and are not intended to indicate or imply that the referenced devices or elements must have a particular orientation, be constructed and operated in a particular orientation, and are therefore not to be considered limiting of the invention.

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

In the present invention, unless otherwise expressly stated or limited, the terms "mounted," "connected," "secured," and the like are to be construed broadly and can, for example, be fixedly connected, detachably connected, or integrally formed; may be mechanically coupled, may be electrically coupled or may be in communication with each other; they may be directly connected or indirectly connected through intervening media, or they may be connected internally or in any other suitable relationship, unless expressly stated otherwise. The specific meanings of the above terms in the present invention can be understood by those skilled in the art according to specific situations.

In the present invention, unless otherwise expressly stated or limited, the first feature "on" or "under" the second feature may be directly contacting the first and second features or indirectly contacting the first and second features through an intermediate. Also, a first feature "on," "over," and "above" a second feature may be directly or diagonally above the second feature, or may simply indicate that the first feature is at a higher level than the second feature. A first feature being "under," "below," and "beneath" a second feature may be directly under or obliquely under the first feature, or may simply mean that the first feature is at a lesser elevation than the second feature.

In the present disclosure, the terms "one embodiment," "some embodiments," "an example," "a specific example," or "some examples" and the like mean that a specific feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the present disclosure. In this specification, the schematic representations of the terms used above are not necessarily intended to refer 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, various embodiments or examples and features of different embodiments or examples described in this specification can be combined and combined by one skilled in the art without contradiction.

Although embodiments of the present invention have been shown and described above, it is understood that the above embodiments are exemplary and should not be construed as limiting the present invention, and that variations, modifications, substitutions and alterations can be made to the above embodiments by those of ordinary skill in the art within the scope of the present invention.

Claims

1. A gas turbine emergency brake assembly, comprising:

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

2. The gas turbine emergency brake assembly of claim 1, wherein said vent valve includes a vent valve cavity and a diaphragm movably disposed within said vent valve cavity between a closed position and an open position for blocking or unblocking said brake air path.

3. The gas turbine emergency brake apparatus of claim 2, wherein the vent valve further comprises a shear cord, the vent valve cavity comprises a first cavity and a second cavity, the brake path comprises a first section and a second section, one end of the first section is adapted to be connected to a compressor of the gas turbine, the other end of the first section is in communication with the first cavity so that the compressor of the gas turbine can supply gas into the first cavity, one end of the second section is in communication with the second cavity, the other end of the second section is connected to the pneumatic brake, and the partition is rotatably disposed in the vent valve cavity between a closed position and an open position so as to close or open the brake path,

the partition plate is positioned between the first chamber and the second chamber in the axial direction of the gas turbine main shaft so as to block the first chamber and the second chamber,

4. The gas turbine emergency braking device of claim 3, further comprising a shear knife, wherein the vent valve further comprises a shear port and a sealing plug, the shear port is disposed on the wall surface of the first cavity, the shear port is capable of communicating the first cavity with the outside, the sealing plug is disposed in the shear port to seal the shear port, the shear knife corresponds to the shear port, and the shear knife is movably disposed along the axial direction of the shear port to pass through the sealing plug, so as to cut off the shear string.

5. The gas turbine emergency braking device according to claim 4, further comprising a control valve, wherein the control valve includes a control valve cavity, a piston, and a piston rod, the piston is movably disposed in the control valve cavity along the axial direction of the shear port, the control valve cavity includes a third cavity and a fourth cavity, the piston is disposed between the third cavity and the fourth cavity in the axial direction of the shear port to block the third cavity and the fourth cavity, one end of the piston rod is disposed in the fourth cavity, the one end of the piston rod is connected to the piston, and the shear knife is disposed on an end face of the other end of the piston rod.

6. The gas turbine emergency braking device according to claim 5, 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 outlet pipe and an oil inlet and outlet, one end of the oil inlet and outlet pipe is communicated with the fourth cavity through the oil inlet and outlet, the other end of the oil inlet and outlet pipe is connected with the oil injection pipeline and the oil drain pipeline, and the oil drain valve is arranged on the oil drain pipeline.

7. The gas turbine emergency braking device of claim 6, further comprising a detonation tube, a first connecting tube, a second connecting tube, and an explosive, wherein the detonation tube and the explosive are disposed in the fourth chamber, and the detonation tube and the explosive are disposed adjacent to each other so that the explosive ruptures the detonation tube, one end of the detonation tube is communicated with the oil inlet and outlet pipe through the first connecting tube, and the other end of the detonation tube is communicated with the oil inlet and outlet pipe through the second connecting tube.

8. The gas turbine emergency braking device according to claim 7, further comprising a power supply and a detonation device, wherein the oil drain valve is a solenoid 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.

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

10. The gas turbine emergency brake device according to any one of claims 1 to 9, wherein the air brake includes a brake disc, a first friction plate, and a second friction plate, the brake disc being adapted to be provided on the main shaft of the gas turbine, the first friction plate and the second friction plate being opposed to each other in the axial direction of the brake disc, and a portion of the brake disc being located between the first friction plate and the second friction plate in the axial direction of the brake disc.

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

12. A gas turbine engine, comprising: a spindle, a compressor and an emergency brake device as claimed in any one of claims 1 to 11.

13. A method of emergency braking a gas turbine engine, comprising the steps of:

arranging a pneumatic brake on a main shaft of the gas turbine;

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

a ventilation valve is arranged on the braking air path;

15. The gas turbine emergency braking method of claim 14, wherein said opening said vent valve comprises: the shear line is cut to rotate the diaphragm to an open position.

16. The gas turbine emergency braking method of claim 15, wherein said opening said vent valve further comprises: moving a cutting knife to cut the cutting string.

17. A gas turbine emergency braking method according to any one of claims 14 to 16, further comprising the steps of:

a control valve is arranged on the ventilation valve;

activating the control valve to open the vent valve.

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

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

19. The gas turbine emergency braking method of claim 18, 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.