CN114810228B - Compact high-temperature fuel pyrolysis gas power generation turbine sealing and cooling structure - Google Patents
Compact high-temperature fuel pyrolysis gas power generation turbine sealing and cooling structure Download PDFInfo
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- CN114810228B CN114810228B CN202210268513.5A CN202210268513A CN114810228B CN 114810228 B CN114810228 B CN 114810228B CN 202210268513 A CN202210268513 A CN 202210268513A CN 114810228 B CN114810228 B CN 114810228B
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D15/00—Adaptations of machines or engines for special use; Combinations of engines with devices driven thereby
- F01D15/10—Adaptations for driving, or combinations with, electric generators
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/02—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type
- F01D11/04—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type using sealing fluid, e.g. steam
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
- F01D21/003—Arrangements for testing or measuring
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/08—Cooling; Heating; Heat-insulation
- F01D25/12—Cooling
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/08—Cooling; Heating; Heat-insulation
- F01D25/12—Cooling
- F01D25/125—Cooling of bearings
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/16—Arrangement of bearings; Supporting or mounting bearings in casings
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/18—Lubricating arrangements
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Motor Or Generator Cooling System (AREA)
Abstract
本发明提供了一种紧凑型高温燃料裂解气发电涡轮密封冷却结构，属于发电涡轮技术领域。解决了目前高压高转速涡轮的轴端密封一般使用干气密封，造价高昂结构复杂，需要较大的装配空间以及附属的高压氮气供气装置，但由于材料和技术的限制耐受温度较低；工作于高温工质环境中的涡轮一般使用水循环来带走热量进行冷却，但是对于高超声速飞行器来说冷源有限，而且使用循环水进行冷却会大大增加发电系统体积的问题。它包括电机外壳、涡轮转轴、前端盖、冷却隔热腔、轴向密封、交错迷宫密封和电机冷却系统。本发明满足机载设备对于空间、质量的要求，有较好密封冷却效果；简化涡轮密封隔热系统且能够有效减少涡轮的泄漏量，保证涡轮发电功率。
The present invention provides a compact high-temperature fuel cracking gas power generation turbine seal cooling structure, belonging to the technical field of power generation turbines. It solves the problem that the shaft end seal of the current high-pressure and high-speed turbine generally uses dry gas seals, which are expensive and complex in structure, require a large assembly space and an attached high-pressure nitrogen gas supply device, but have a low tolerance temperature due to material and technical limitations; turbines working in a high-temperature working fluid environment generally use water circulation to remove heat for cooling, but for hypersonic aircraft, the cold source is limited, and the use of circulating water for cooling will greatly increase the volume of the power generation system. It includes a motor housing, a turbine shaft, a front end cover, a cooling and heat insulation cavity, an axial seal, an interlaced labyrinth seal and a motor cooling system. The present invention meets the requirements of airborne equipment for space and quality, and has a good sealing and cooling effect; it simplifies the turbine seal insulation system and can effectively reduce the leakage of the turbine to ensure the turbine power generation.
Description
Technical Field
The invention belongs to the technical field of power generation turbines, and particularly relates to a compact high-temperature fuel pyrolysis gas power generation turbine sealing and cooling structure.
Background
The development of the air suction hypersonic aircraft replaces the traditional aeroengine with a rotating part, but meanwhile, the air suction hypersonic aircraft cannot generate electricity through a rotating shaft for the use of aircraft electronic devices, and huge quality penalty is brought to the aircraft by carrying a battery, so that the current research hot spot is to utilize the energy of the aircraft to generate electricity, and meanwhile, the problems of precooling and compression of hypersonic incoming flow are solved. The hydrocarbon fuel carried by the aircraft absorbs heat and heats up in the cooling channel, meanwhile, the liquid state is changed into a supercritical state, and the hydrocarbon fuel is further cracked to generate an oil-gas mixture composed of micromolecular hydrocarbon, and the high-temperature and high-pressure oil-gas mixture can be used as a working medium to drive the power generation system to generate power.
The oil gas turbine is a core component of an oil gas power generation system, the temperature of oil gas at the inlet of the turbine can reach 500-700 ℃, and the pressure can reach about 3-5 MPa. The turbine is in a high-temperature and high-pressure environment, the maximum working temperature allowed by the motor is 200 ℃, and meanwhile, the sealing and lubrication of the bearing can be disabled by high-temperature and high-pressure oil gas.
At present, the dry gas sealing effect is better in the field of high-pressure gas sealing of a rotating shaft, the technology is mature, the dry gas sealing device is applied at home and abroad, auxiliary gas supply equipment is needed, certain requirements are met on the shaft diameter of the rotating shaft, the dry gas sealing device is not suitable for the requirements of an aircraft on small size and simple structure, and contact sealing is not suitable for sealing high-rotation-speed equipment. The requirement of the airborne equipment on the weight size is high, so that the problems of reducing the weight and the turbine volume on the premise of ensuring the functions are to be solved urgently.
Disclosure of Invention
In view of the above, the present application aims to provide a compact high-temperature fuel pyrolysis gas turbine seal cooling structure, so as to solve the problems that the existing shaft end seal of the high-pressure high-rotation-speed turbine generally uses dry gas seal, the cost is high, the structure is complex, a large assembly space and an attached high-pressure nitrogen gas supply device are required, but the tolerance temperature is low due to the limitation of materials and technology; the turbine working in the high-temperature working medium environment generally uses water circulation to take away heat for cooling, but for hypersonic aircrafts, cold sources are limited, and the cooling by using circulating water can greatly increase the volume of a power generation system; the turbine sealing heat insulation system is simplified, the leakage quantity of the turbine can be effectively reduced, and the turbine power generation is ensured.
In order to achieve the above purpose, the technical scheme of the invention is realized as follows:
A compact high-temperature fuel pyrolysis gas power generation turbine seal cooling structure comprises a motor shell, a turbine rotating shaft, a front end cover, a cooling heat insulation cavity, an axial seal, a staggered labyrinth seal and a motor cooling system;
The rear end of the cooling heat insulation cavity is fixedly connected with the motor shell, the front end of the cooling heat insulation cavity is fixedly connected with the front end cover, a guide ring is arranged on the outer side of the center of the cooling heat insulation cavity, a working medium air inlet space is formed between the cooling heat insulation cavity and the front end cover as well as between the cooling heat insulation cavity and the guide ring, a stator is arranged in the motor shell, the stator is matched with the rotor, an impeller is arranged in the guide ring, a turbine rotating shaft sequentially penetrates through the rotor and a central hole of the cooling heat insulation cavity to be connected with the impeller, the axial seal is arranged at the central hole of the cooling heat insulation cavity, a first comb tooth seal is arranged at the back of the impeller, a second comb tooth seal is arranged at the position where the front end of the cooling heat insulation cavity is matched with the turbine rotating shaft, and the first comb tooth seal and the second comb tooth seal form a staggered labyrinth seal;
the cooling heat insulation cavity is radially provided with a cooling heat insulation cavity chamber low-temperature fuel inlet and a cooling heat insulation cavity chamber low-temperature fuel outlet which are mutually perpendicular, the radial direction of the cooling heat insulation cavity is also provided with a first eddy current sensor mounting hole and a second eddy current sensor mounting hole which are mutually perpendicular, the two eddy current sensor mounting holes extend to a turbine rotating shaft, the edge of the cooling heat insulation cavity is provided with a radial sealing gas inlet which is communicated with an axial seal, the axial seal is a high-temperature-resistant carbon fiber sealing device, and the high-temperature-resistant carbon fiber sealing device is used for preventing high-temperature cracking gas of fuel from entering a bearing and a motor through a gap between the turbine rotating shaft and the sealing device;
The cooling heat insulation cavity is internally provided with a cooling flow passage which is communicated with a low-temperature fuel inlet of the cooling heat insulation cavity chamber and a low-temperature fuel outlet of the cooling heat insulation cavity chamber; the low-temperature fuel enters the cooling flow passage through the low-temperature fuel inlet of the cooling heat insulation cavity chamber and is discharged from the low-temperature fuel outlet of the cooling heat insulation cavity chamber after being distributed with the cooling flow passage, so that the bearing and the motor are insulated;
The turbine rotating shaft is supported by two bearings, each bearing is installed in a bearing seat, the two bearing seats are located at two ends of the motor shell, the motor cooling system is arranged on the motor shell and the two bearing seats, and the motor cooling system is used for cooling the motor and lubricating and cooling the bearings.
Further, the cooling flow passage comprises four fan-shaped flow passages uniformly distributed on the circumference, each fan-shaped flow passage comprises an inner heat insulation fan-shaped cavity and an outer heat insulation fan-shaped cavity which are correspondingly arranged and mutually communicated, the four outer heat insulation fan-shaped cavities of the four fan-shaped flow passages are arranged on the same plane, the four inner heat insulation fan-shaped cavities are arranged on the same plane, the bottom plane of the four inner heat insulation fan-shaped cavities is lower than the bottom plane of the four outer heat insulation fan-shaped cavities, and the four inner heat insulation fan-shaped cavities are arranged close to the central hole of the cooling heat insulation cavity;
the four outer heat-insulating fan annular cavities are a heat-insulating cavity a, a heat-insulating cavity b, a heat-insulating cavity c and a heat-insulating cavity d respectively, and the four outer heat-insulating fan annular cavities are a heat-insulating cavity e, a heat-insulating cavity f, a heat-insulating cavity g and a heat-insulating cavity h respectively;
the low-temperature fuel oil enters the heat insulation cavity a from radial direction through the low-temperature fuel oil inlet of the cooling heat insulation cavity chamber, enters the heat insulation cavity e after the heat insulation cavity a is filled, flows towards the front end of the turbine in the axial direction at the moment, enters the heat insulation cavity f from the heat insulation cavity e along the circumferential direction through the channel at the front end of the second eddy current sensor mounting hole (22), flows towards the rear end of the turbine in the axial direction after the heat insulation cavity f is filled, enters the heat insulation cavity c from the heat insulation cavity b along the outer side channel, enters the heat insulation cavity g after the heat insulation cavity c is filled, enters the heat insulation cavity h through the channel between the heat insulation cavity g and the heat insulation cavity h, flows into the heat insulation cavity d from the rear end of the turbine in the axial direction after the heat insulation cavity h is filled, and finally is discharged from the low-temperature fuel oil outlet of the cooling heat insulation cavity chamber.
Still further, high temperature resistant carbon fiber sealing device includes seal body and multiunit high temperature resistant carbon fiber sealing ring, the seal body inserts and passes through a plurality of axial fixing bolt connection from the rear end of the centre bore in thermal-insulated chamber of cooling, is equipped with a plurality of groups of graphite seal assembly that contain the spring between the centre bore inner wall in seal body and thermal-insulated chamber of cooling, has seted up the ring channel that holds multiunit high temperature resistant carbon fiber sealing ring in the seal body inside, is equipped with but axial compression spring assembly between two adjacent high temperature resistant carbon fiber sealing rings, is located the outermost of the high temperature resistant carbon fiber sealing ring of rearmost group and passes through jump ring subassembly location.
Furthermore, the high temperature resistant carbon fiber sealing ring is formed by overlapping three annular sheets, the central angle of each annular sheet is 126 degrees, each annular sheet is provided with a radial groove matched with the radial bulge on the inner wall of the annular groove of the sealing body, the outer edge of each annular sheet is provided with a radial compression spring, each group of high temperature resistant carbon fiber sealing rings is axially provided with an annular baffle plate, and the annular baffle plate is connected with a corresponding axial compression spring assembly.
Still further, motor cooling system is including seting up spiral runner and the two nozzles around the motor on the motor housing wall, has radial oil gas entry in motor housing portion, radial oil gas entry is linked together with spiral runner, has seted up the passageway of the corresponding tip of a intercommunication spiral runner in every bearing frame, is equipped with a nozzle in every passageway, and every nozzle is arranged towards the bearing of corresponding side, is equipped with an oil gas outlet in the below of every bearing frame, and low temperature oil gas gets into the spiral runner from radial oil gas entry and cools off the motor in, and the low temperature oil gas after the cooling motor gets into the bearing of corresponding side through the nozzle, and the lubrication of bearing is followed two oil gas outlets and is discharged and gets into high temperature fuel preheating passageway.
Furthermore, the outside of the sealed cooling cavity is provided with a gas distributor communicated with the working medium inlet space, the gas distributor comprises an annular bin, a turbine air inlet is communicated with the annular bin, the annular bin is communicated with the working medium inlet space through a plurality of pipelines, high-temperature working medium entering from a turbine air inlet pipe orifice enters the working medium inlet space through a plurality of pipelines, and the turbine works and is discharged from a turbine air outlet.
Still further, first electric vortex sensor mounting hole and second electric vortex sensor mounting hole are the screw hole, and electric vortex sensor passes through threaded connection mode and installs at the screw hole.
Furthermore, a sealing cooling gas inlet on the sealing heat insulation cavity is provided with threads, a pressure gauge sensor is installed by connecting a three-way pipe, the pressure gauge sensor monitors the pressure of high-temperature oil gas leaked from a sealing part of the rotating shaft in real time, and the pressure of the sealing cooling gas is regulated through feedback, so that the high-temperature working medium is prevented from leaking along the axial direction.
Further, the impeller and the turbine shaft are axially positioned by a nut.
Further, the first comb tooth seal and the turbine are integrally molded and cast, and the second comb tooth seal and the seal heat insulation cavity are integrally molded and cast.
Compared with the prior art, the compact high-temperature fuel pyrolysis gas power generation turbine sealing and cooling structure has the beneficial effects that:
1. The low-temperature oil gas is taken as sealing gas to enter the volute sealing structure to form pneumatic sealing together with the volute sealing structure, so that high-temperature cracking gas of fuel is prevented from entering a bearing and a motor through a gap between a rotating shaft and the sealing, and a failure coil of the bearing is prevented from being damaged; the low-temperature oil gas enters the spiral through hole to cool the motor, heat brought by heat conduction is reduced, the oil gas after cooling the motor enters the bearing through the nozzle to lubricate the bearing, and meanwhile, heat generated by high-speed movement of the bearing is taken away by the flow of the oil gas.
2. The double bond is adopted between the impeller and the rotating shaft to transfer torque, when the turbine works, because the high-temperature fuel oil cracking gas pressure entering from the turbine inlet is higher, if the motor torque turbine is not controlled in real time through the motor feedback system, the motor can exceed the design range to damage the turbine under the drive of high-pressure gas, so that the impeller receives opposite torque from the high-temperature gas and the motor at any time when working, and the double bond is used to transfer torque to avoid loosening of the impeller caused by using threads.
3. The pressure gauge sensor is arranged at the oil gas inlet of the sealed cooling cavity, and the air inlet pressure of the cooling gas is automatically adjusted according to the pressure of leaked high-temperature oil gas, so that the air inlet pressure of the cooling gas is slightly larger than the pressure of the high-temperature oil gas, a sealing gap is filled with low-temperature oil gas, the low-temperature oil gas cannot excessively enter the turbine, the turbine is guaranteed to be functional, meanwhile, the same working medium is used, and the working medium cannot be mixed when the sealing gas enters the turbine. And monitoring pressure change in real time in the running process, if the leakage pressure value is larger than the set sealing limit pressure value, reducing the pressure of low-temperature oil gas, releasing a small amount of leakage high-temperature oil gas to reduce the pressure, and preventing a large amount of high-temperature oil gas from entering a bearing and a motor due to the fact that the leakage pressure value exceeds the sealing capacity too high to break the sealing.
4. The low-temperature working medium is used for cooling the motor, the cooling channel is positioned on the motor shell, cooling gas does not enter the motor, and the motor is not damaged due to the combined action of the change of sealing gas pressure and electromagnetic pulsation between the motor rotor and the stator.
5. The low-temperature fuel oil enters the flow channel and the cavity between the cooling heat insulation cavity and the seal through the pipeline, the whole cavity is fully distributed to play a heat insulation role, the bearing and the motor at the rear are protected, and meanwhile, the cooling cavity surrounds the periphery of the eddy current sensor, so that the eddy current sensor has lower working temperature, and the fuel oil flowing in the cavity is heated and then enters the heater to be cracked.
6. Because only one centralized mass is arranged on the turbine rotating shaft, and two rigid supports are arranged on two sides of the motor rotor, the maximum vibration displacement position of the motor shaft is positioned near the impeller, and the high-temperature oil gas with leakage at the front end of the seal is not installed. The electric vortex sensor is installed at the sealed rear end and has the protection of sealing and volute cooling, and is nearer to the impeller, and the measured data is basically consistent with the vibration of the rotating shaft, so that the electric vortex sensor can be used as a vibration monitoring point of the rotating shaft, and meanwhile, the space is saved, and an additional device is not needed.
Drawings
The accompanying drawings, which are included to provide a further understanding of the invention and are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and together with the description serve to explain the invention. In the drawings:
FIG. 1 is a schematic structural diagram of a compact high temperature fuel pyrolysis gas power generation turbine seal cooling structure according to an embodiment of the present invention;
FIG. 2 is a schematic diagram of a motor cooling and bearing lubrication cooling structure according to an embodiment of the present invention;
FIG. 3 is a schematic view of a scroll cooling and insulating structure;
FIG. 4 is a schematic view of a high temperature resistant carbon fiber seal structure;
FIG. 5 is a schematic view of the structure of a single annulus flap;
FIG. 6 is a schematic view of the structure of the two annuloplasty ring superimposed;
Fig. 7 is a top view of fig. 6.
Reference numerals illustrate:
1. A turbine inlet; 2. a turbine exhaust port; 3. a bearing; 4. a turbine shaft; 5. a motor housing; 6. cooling the heat insulation cavity; 7. an impeller; 8. a first eddy current sensor mounting hole; 9. the first comb teeth are sealed; 10. a high temperature resistant carbon fiber sealing device; 11. a stator; 12. a rotor; 13. an oil gas inlet; 14. a first oil and gas outlet; 15. a second oil gas outlet; 16. a nozzle; 17. a spiral flow passage; 18. the second comb teeth are sealed; 19. an impeller fixing nut; 20. a low-temperature fuel inlet for cooling the heat insulation cavity chamber; 21. a low-temperature fuel outlet for cooling the heat insulation cavity chamber; 22. a second eddy current sensor mounting hole; 23. sealing the gas inlet; 24. an axial fixing bolt; 25. a graphite seal assembly containing a spring; 26. high temperature resistant carbon fiber sealing ring; 27. a sealing body; 28. an axially compressible spring assembly; 29. a clamp spring assembly; 30. a radial compression spring; 31. a positioning groove; 32. a front end cover; 33. a guide ring; 34. a gas distributor; 35. and a bearing seat.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention. It should be noted that, in the case of no conflict, embodiments of the present invention and features of the embodiments may be combined with each other, and the described embodiments are only some embodiments of the present invention, not all embodiments.
As shown in fig. 1-7, the "high-temperature fuel pyrolysis gas" refers to a fuel pyrolysis gas at 500-600 ℃, and a compact high-temperature fuel pyrolysis gas power generation turbine seal cooling structure comprises a motor shell 5, a turbine rotating shaft 4, a front end cover 32, a cooling heat insulation cavity 6, an axial seal, a staggered labyrinth seal and a motor cooling system;
The rear end of the cooling heat insulation cavity 6 is fixedly connected with the motor shell 5, the front end is fixedly connected with the front end cover 32, a guide ring 33 is arranged on the outer side of the center of the cooling heat insulation cavity 6, a working medium inlet space is formed between the cooling heat insulation cavity 6 and the front end cover 32 and between the cooling heat insulation cavity and the guide ring 33, a stator 11 is installed in the motor shell 5, the stator 11 is matched with a rotor 12, an impeller 7 is installed in the guide ring 33, a turbine rotating shaft 4 sequentially penetrates through the rotor 12 and a central hole of the cooling heat insulation cavity 6 to be connected with the impeller 7, the axial seal is arranged at the central hole of the cooling heat insulation cavity 6, a first comb tooth seal 9 is arranged at the back of the impeller 7, a second comb tooth seal 18 is arranged at the position where the front end of the cooling heat insulation cavity 6 is matched with the turbine rotating shaft 4, and the first comb tooth seal 9 and the second comb tooth seal 18 form a staggered labyrinth seal; the second comb seal 18 is used for reducing the temperature and the pressure of working media to play a role in protecting graphite rings;
the cooling heat insulation cavity 6 is radially provided with a cooling heat insulation cavity chamber low-temperature fuel inlet 20 and a cooling heat insulation cavity chamber low-temperature fuel outlet 21 which are mutually perpendicular, the radial direction of the cooling heat insulation cavity 6 is also provided with a first electric vortex sensor mounting hole 8 and a second electric vortex sensor mounting hole 22 which are mutually perpendicular, the two electric vortex sensor mounting holes extend to the turbine rotating shaft 4, the edge of the cooling heat insulation cavity 6 is provided with a radial sealing gas inlet 23, the sealing gas inlet 23 is communicated with an axial seal, the axial seal is a high-temperature-resistant carbon fiber sealing device 10, and the high-temperature-resistant carbon fiber sealing device 10 is used for preventing high-temperature cracking gas of fuel from entering the bearing 3 and the motor through a gap between the turbine rotating shaft 4 and the sealing device;
A cooling flow passage is formed in the cooling heat insulation cavity 6, and is communicated with a cooling heat insulation cavity chamber low-temperature fuel inlet 20 and a cooling heat insulation cavity chamber low-temperature fuel outlet 21; the low-temperature fuel enters the cooling flow passage through the low-temperature fuel inlet 20 of the cooling heat insulation cavity chamber and is discharged from the low-temperature fuel outlet 21 of the cooling heat insulation cavity chamber after being distributed with the cooling flow passage, so that the bearing 3 and the motor are insulated;
The turbine rotating shaft 4 is supported by two bearings 3, each bearing 3 is installed in a bearing seat 35, the two bearing seats 35 are located at two ends of the motor shell 5, the motor cooling system is arranged on the motor shell and the two bearing seats 35, and the motor cooling system is used for cooling the motor and lubricating and cooling the bearings 3.
The low-temperature oil gas working medium introduced by the sealing gas inlet 23 is used as cooling sealing gas of the high-temperature-resistant carbon fiber ring sealing device, the low-temperature oil gas working medium introduced by the oil gas inlet is used as cooling gas of a cooling motor, and is used as a lubricating medium of the ceramic ball bearing to simultaneously take away heat generated by high-speed rotation of the bearing, and the heated low-temperature oil gas is recovered to the front end of the turbine inlet to enter the turbine for working.
The cooling flow passage comprises four fan-shaped flow passages uniformly distributed in the circumference, each fan-shaped flow passage comprises an inner heat insulation fan-shaped cavity and an outer heat insulation fan-shaped cavity which are correspondingly arranged and mutually communicated, the four outer heat insulation fan-shaped cavities of the four fan-shaped flow passages are arranged on the same plane, the four inner heat insulation fan-shaped cavities are arranged on the same plane, the bottom plane of the four inner heat insulation fan-shaped cavities is lower than the bottom plane of the four outer heat insulation fan-shaped cavities, and the four inner heat insulation fan-shaped cavities are arranged close to the central hole of the cooling heat insulation cavity 6;
the four outer heat-insulating fan annular cavities are a heat-insulating cavity a, a heat-insulating cavity b, a heat-insulating cavity c and a heat-insulating cavity d respectively, and the four outer heat-insulating fan annular cavities are a heat-insulating cavity e, a heat-insulating cavity f, a heat-insulating cavity g and a heat-insulating cavity h respectively;
the low-temperature fuel oil enters the heat insulation cavity a from radial through the low-temperature fuel oil inlet 20 of the cooling heat insulation cavity chamber, enters the heat insulation cavity e after the heat insulation cavity a is filled, flows towards the front end of the turbine in the axial direction at the moment, enters the heat insulation cavity f from the heat insulation cavity e along the circumferential direction through a channel at the front end of the second electric vortex sensor mounting hole 22, flows towards the rear end of the turbine in the axial direction after the heat insulation cavity f is filled, enters the heat insulation cavity c from the heat insulation cavity b along an outer channel, enters the heat insulation cavity g after the heat insulation cavity c is filled, enters the heat insulation cavity h through a channel between the heat insulation cavity g and the heat insulation cavity h, flows towards the rear end of the turbine in the axial direction after the heat insulation cavity h is filled, and finally is discharged from the low-temperature fuel oil outlet 21 of the cooling heat insulation cavity chamber;
The arrangement above the sealed heat-insulating cooling cavity ensures that each cavity can be filled with cooling gas to achieve the purpose of cooling heat insulation, and meanwhile, the arrangement ensures that the cavity distribution can avoid the sealed gas inlet 23 and two eddy current sensor mounting holes, and the eddy current sensors are under the protection of low-temperature sealed gas.
The inside of the through hole of the rotating shaft at the front end of the cooling heat insulation cavity 6 is sequentially provided with a second comb tooth seal 18 and a high-temperature-resistant carbon fiber sealing device 10 for sealing, and high-temperature fuel pyrolysis gas leaked from the back of the impeller is throttled and depressurized through labyrinth sealing, so that a certain protection effect is achieved on the carbon fiber ring.
The high-temperature-resistant carbon fiber sealing device 10 comprises a sealing body 27 and three groups of high-temperature-resistant carbon fiber sealing rings 26, wherein the sealing body 27 is inserted from the rear end of a central hole of the cooling heat insulation cavity 6 and is connected through a plurality of axial fixing bolts, and the front end of the sealing body 27 is chamfered by 30 degrees for convenient installation; three groups of graphite sealing assemblies 25 containing springs are arranged between the sealing body 27 and the inner wall of the central hole of the cooling heat insulation cavity 6, so that the sealing between the two gaps is ensured, the introduced sealing gas can maintain stable pressure, and the high-temperature fuel cracking gas leaked from the rotating shaft is sealed in front of the bearing; radial through holes are formed between every two of the three groups of graphite rings and are communicated with the surface of the rotating shaft, annular grooves are formed in the intersections of the through holes and the rotating shaft, a pressure gauge sensor is arranged at the inlet of the through holes, annular grooves for accommodating multiple groups of high-temperature-resistant carbon fiber sealing rings 26 are formed in the sealing body 27, an axially compressible spring assembly 28 is arranged between every two adjacent groups of high-temperature-resistant carbon fiber sealing rings 26, and the outermost side of the high-temperature-resistant carbon fiber sealing ring 26 located at the rearmost end group is positioned through a clamp spring assembly 29. The high temperature resistant carbon fiber sealing ring 26 is formed by overlapping three annular sheets, the central angle of each annular sheet is 126 degrees, each annular sheet is provided with a radial groove matched with a radial bulge on the inner wall of the annular groove of the sealing body 27, and the sealing ring is fixed when the rotating shaft rotates to prevent the sealing ring from rotating along with the rotating shaft; the outer edge of each annular flap is provided with a radial compression spring 30, and each group of high-temperature-resistant carbon fiber sealing rings 26 is axially provided with an annular baffle which is connected with a corresponding axially compressible spring assembly 28; under the condition that the radial runout of the rotating shaft is severe in axial movement, the sealing ring and the rotating shaft simultaneously perform axial movement, friction between the sealing ring and the rotating shaft is reduced, and meanwhile the sealing ring is convenient to install and position.
The size of the annular groove is larger than that of the carbon fiber sealing ring in the radial direction and the axial direction, the radial compression spring at the outer edge of the sealing ring enables the sealing ring to keep a gap of h6 with the rotating shaft, the sealing ring keeps concentric with the rotating shaft when the rotating shaft is static, the rotating shaft vibrates greatly when the turbine is started and stopped, certain radial runout is generated, under the action of air film force between the rotating shaft and the sealing ring, the spring at the outer edge of the sealing ring is compressed, one valve in the sealing ring moves radially along with the vibration of the rotating shaft, the other two valves move along with the action of the compression spring, the sealing ring still basically keeps concentric with the rotating shaft with the same section, but forms a certain angle with the shaft axis of the rotating shaft, no bump grinding occurs under the condition that the rotating shaft keeps a small gap with the sealing ring, and when the rotating shaft is stable under the action of the compression spring, the sealing ring resumes concentricity with the shaft axis of the rotating shaft.
The motor cooling system comprises a spiral runner 17 and two nozzles 16 which are arranged on the wall of a motor shell 5 and surround the motor, a radial oil gas inlet 13 is formed in the whole part of the motor shell 5, the radial oil gas inlet 13 is communicated with the spiral runner 17, a channel which is communicated with the corresponding end part of the spiral runner 17 is formed in each bearing seat 35, one nozzle 16 is arranged in each channel, each nozzle 16 faces to a bearing 3 on the corresponding side, an oil gas outlet is formed below each bearing seat, low-temperature oil gas enters the spiral runner 17 from the radial oil gas inlet 13 to cool the motor, the low-temperature oil gas after cooling the motor enters the bearing 3 on the corresponding side through the nozzles 16, and the low-temperature oil gas is lubricated and cooled by the bearing 3 and then discharged into a high-temperature oil gas preheating channel through the two oil gas outlets. The low-temperature oil gas enters the spiral through hole to cool the motor, heat brought by heat conduction is reduced, the oil gas after cooling the motor enters the bearing through the nozzle to lubricate the bearing, and meanwhile, heat generated by high-speed movement of the bearing is taken away by the flow of the oil gas.
The outside of sealed cooling chamber is equipped with the gas distributor with working medium air intake space intercommunication, gas distributor includes annular storehouse, and the intercommunication has turbine air inlet 1 on annular storehouse, annular storehouse is through a plurality of pipelines and working medium air intake space intercommunication, and the high temperature working medium that gets into from turbine air intake mouth of pipe gets into working medium air intake space through a plurality of pipelines, and turbine is discharged from turbine gas vent 2 after doing work.
The first eddy current sensor mounting hole 8 and the second eddy current sensor mounting hole 22 are threaded holes, and the eddy current sensor is mounted in the threaded holes in a threaded connection mode. The electric vortex sensor is installed at the sealed rear end and has the protection of sealing and volute cooling, and is nearer to the impeller, and the measured data is basically consistent with the vibration of the rotating shaft, so that the electric vortex sensor can be used as a vibration monitoring point of the rotating shaft, and meanwhile, the space is saved, and an additional device is not needed.
The sealing cooling gas inlet 23 on the sealing heat insulation cavity is provided with threads, a pressure gauge sensor is installed by connecting a three-way pipe, the pressure gauge sensor monitors the pressure of high-temperature oil gas leaked from the sealing part of the rotating shaft in real time, and the pressure of the sealing cooling gas is regulated through feedback, so that the high-temperature working medium is prevented from leaking along the axial direction.
The impeller and the rotating shaft are connected through a key to transmit torque, the impeller is pushed in axially in an interference fit mode, the front end is compressed by using a nut 19, the axial positioning is easier than that of a thread by using the key connection, the phenomenon that the staggered sealing gap is too greatly reduced in sealing effect due to axial installation deviation of the impeller is prevented, and the gap is too small to generate friction is prevented; the impeller 7 is axially arranged at the front end of the turbine rotating shaft 4, the impeller 7 and the turbine rotating shaft 4 are axially positioned through a screw cap, the first comb tooth seal 9 and the turbine are integrally molded and cast, and the second comb tooth seal 18 and the sealed heat insulation cavity are integrally molded and cast. Because the impeller is separated from the rotating shaft, the comb tooth seal at the back of the impeller can be corresponding to the comb tooth seal on the volute, and a small gap is kept after the impeller and the volute are combined, so that a staggered labyrinth seal is formed, and the sealing performance is improved greatly compared with a flat tooth labyrinth seal.
The invention provides a compact high-temperature fuel pyrolysis gas turbine sealing and cooling system which is compact in overall design structure, can be used for better sealing a turbine high-temperature working medium, and can be used for protecting components such as a turbine bearing, a motor and the like in a normal working temperature range. The compact high temperature fuel pyrolysis gas turbine seal cooling system includes: the impeller is radially sealed, and staggered seals are arranged on the back surface of the impeller; the rotary shaft is axially sealed, a combined seal consisting of labyrinth seal and an inflatable carbon fiber ring is arranged in front of the bearing, and a cooling seal gas inlet is arranged between the high-temperature-resistant carbon fiber rings. And the turbine shell at the outer side of the motor is provided with a radial spiral through hole. The low-temperature fuel oil respectively enters the cooling channels and circulates in the channels to take away heat so as to achieve the purpose of reducing the temperature.
The embodiments of the invention disclosed above are intended only to help illustrate the invention. The examples are not intended to be exhaustive or to limit the invention to the precise forms disclosed. Many modifications and variations are possible in light of the above teaching. The embodiments were chosen and described in order to best explain the principles of the invention and the practical application, to thereby enable others skilled in the art to best understand and utilize the invention.
Claims (10)
1. A compact high-temperature fuel pyrolysis gas power generation turbine seal cooling structure is characterized in that: the device comprises a motor shell (5), a turbine rotating shaft (4), a front end cover (32), a cooling heat insulation cavity (6), axial seals, staggered labyrinth seals and a motor cooling system;
The rear end of the cooling heat insulation cavity (6) is fixedly connected with the motor shell (5), the front end of the cooling heat insulation cavity is fixedly connected with the front end cover (32), a guide ring (33) is arranged on the outer side of the center of the cooling heat insulation cavity (6), a working medium air inlet space is formed between the cooling heat insulation cavity (6) and the front end cover (32) and between the cooling heat insulation cavity and the guide ring (33), a stator (11) is arranged in the motor shell (5), the stator (11) is matched with the rotor (12), an impeller (7) is arranged in the guide ring (33), a turbine rotating shaft (4) sequentially penetrates through the rotor (12) and the central hole of the cooling heat insulation cavity (6) to be connected with the impeller (7), a first comb tooth seal (9) is arranged on the back of the impeller (7), a second comb tooth seal (18) is arranged at the matching position of the front end of the cooling heat insulation cavity (6) and the turbine rotating shaft (4), and the first comb tooth seal (9) and the second comb tooth seal (18) form a labyrinth seal;
the cooling heat insulation cavity (6) is radially provided with a cooling heat insulation cavity chamber low-temperature fuel inlet (20) and a cooling heat insulation cavity chamber low-temperature fuel outlet (21) which are perpendicular to each other, the cooling heat insulation cavity (6) is radially provided with a first eddy current sensor mounting hole (8) and a second eddy current sensor mounting hole (22) which are perpendicular to each other, the two eddy current sensor mounting holes extend to the turbine rotating shaft (4), the edge of the cooling heat insulation cavity (6) is provided with a radial sealing gas inlet (23), the sealing gas inlet (23) is communicated with an axial seal, the axial seal is a high-temperature-resistant carbon fiber sealing device (10), and the high-temperature-resistant carbon fiber sealing device (10) is used for preventing high-temperature cracking gas of fuel from entering a bearing (3) and a motor through a gap between the turbine rotating shaft (4) and the high-temperature-resistant carbon fiber sealing device (10);
A cooling flow passage is formed in the cooling heat insulation cavity (6), and the cooling flow passage is communicated with a cooling heat insulation cavity chamber low-temperature fuel inlet (20) and a cooling heat insulation cavity chamber low-temperature fuel outlet (21); the low-temperature fuel enters the cooling flow passage through the low-temperature fuel inlet (20) of the cooling heat insulation cavity chamber and is discharged from the low-temperature fuel outlet (21) of the cooling heat insulation cavity chamber after being distributed with the cooling flow passage, so that the bearing (3) and the motor are insulated;
The turbine rotating shaft (4) is supported by two bearings (3), each bearing (3) is installed in a bearing seat (35), the two bearing seats (35) are located at two ends of the motor shell (5), the motor cooling system is arranged on the motor shell and the two bearing seats, and the motor cooling system is used for cooling the motor and lubricating and cooling the bearings (3).
2. The compact, high temperature fuel pyrolysis gas power generation turbine seal cooling structure of claim 1, wherein: the cooling flow passage comprises four fan-shaped flow passages uniformly distributed in the circumference, each fan-shaped flow passage comprises an inner heat insulation fan-shaped cavity and an outer heat insulation fan-shaped cavity which are correspondingly arranged and mutually communicated, the four outer heat insulation fan-shaped cavities of the four fan-shaped flow passages are arranged on the same plane, the four inner heat insulation fan-shaped cavities are arranged on the same plane, the bottom plane of the four inner heat insulation fan-shaped cavities is lower than the bottom plane of the four outer heat insulation fan-shaped cavities, and the four inner heat insulation fan-shaped cavities are arranged close to the central hole of the cooling heat insulation cavity (6);
The four outer heat-insulating fan annular cavities are a heat-insulating cavity a, a heat-insulating cavity b, a heat-insulating cavity c and a heat-insulating cavity d respectively, and the four inner heat-insulating fan annular cavities are a heat-insulating cavity e, a heat-insulating cavity f, a heat-insulating cavity g and a heat-insulating cavity h respectively;
The low-temperature fuel oil enters the heat insulation cavity a from radial direction through the low-temperature fuel oil inlet (20) of the cooling heat insulation cavity chamber, enters the heat insulation cavity e after the heat insulation cavity a is full, flows towards the front end of the turbine in the axial direction at the moment, enters the heat insulation cavity f from the heat insulation cavity e along the circumferential direction through the channel at the front end of the second electric vortex sensor mounting hole (22), flows towards the rear end of the turbine in the axial direction after the heat insulation cavity f is full, enters the heat insulation cavity c from the heat insulation cavity b along the outer side flow channel, enters the heat insulation cavity g after the heat insulation cavity c is full, enters the heat insulation cavity h through the channel between the heat insulation cavity g and the heat insulation cavity h, flows into the heat insulation cavity d from the rear end of the turbine in the axial direction after the heat insulation cavity h is full, and finally is discharged from the low-temperature fuel oil outlet (21) of the cooling heat insulation cavity chamber.
3. The compact, high temperature fuel pyrolysis gas power generation turbine seal cooling structure of claim 1, wherein: the high temperature resistant carbon fiber sealing device (10) comprises a sealing body (27) and a plurality of groups of high temperature resistant carbon fiber sealing rings (26), wherein the sealing body (27) is inserted from the rear end of a central hole of a cooling heat insulation cavity (6) and is connected through a plurality of axial fixing bolts, a plurality of groups of graphite sealing assemblies (25) containing springs are arranged between the sealing body (27) and the inner wall of the central hole of the cooling heat insulation cavity (6), annular grooves for accommodating the plurality of groups of high temperature resistant carbon fiber sealing rings (26) are formed in the sealing body (27), an axial compression spring assembly (28) is arranged between two adjacent groups of high temperature resistant carbon fiber sealing rings (26), and the outermost side of the high temperature resistant carbon fiber sealing ring (26) positioned at the rearmost end group is positioned through a clamp spring assembly (29).
4. A compact, high temperature fuel pyrolysis gas power generation turbine seal cooling structure according to claim 3, wherein: the high temperature resistant carbon fiber sealing ring (26) is formed by overlapping three annular sheets, the central angle of each annular sheet is 126 degrees, each annular sheet is provided with a radial groove matched with the radial bulge on the inner wall of the annular groove of the sealing body (27), the outer edge of each annular sheet is provided with a radial compression spring (30), each group of high temperature resistant carbon fiber sealing rings (26) is axially provided with an annular baffle, and the annular baffle is connected with a corresponding axial compression spring assembly (28).
5. The compact, high temperature fuel pyrolysis gas power generation turbine seal cooling structure of claim 1, wherein: the motor cooling system comprises a spiral runner (17) and two nozzles (16) which are arranged on the wall of a motor shell (5) and encircle the motor, a radial oil gas inlet (13) is formed in the motor shell (5), the radial oil gas inlet (13) is communicated with the spiral runner (17), a channel which is communicated with the corresponding end part of the spiral runner (17) is formed in each bearing seat (35), one nozzle (16) is arranged in each channel, each nozzle (16) faces towards a bearing (3) on the corresponding side, an oil gas outlet is formed below each bearing seat (35), low-temperature oil gas enters the spiral runner (17) from the radial oil gas inlet (13) to cool the motor, the low-temperature oil gas after cooling the motor enters a bearing (3) on the corresponding side through the nozzles (16), and the low-temperature oil gas is discharged into a high-temperature fuel preheating channel through the two oil gas outlets after lubrication and cooling of the bearing (3).
6. The compact, high temperature fuel pyrolysis gas power generation turbine seal cooling structure of claim 1, wherein: the cooling heat-insulating cavity is externally provided with a gas distributor communicated with a working medium inlet space, the gas distributor comprises an annular bin, a turbine air inlet (1) is communicated with the annular bin, the annular bin is communicated with the working medium inlet space through a plurality of pipelines, high-temperature working medium entering from the turbine air inlet enters the working medium inlet space through a plurality of pipelines, and the working medium is discharged from a turbine air outlet (2) after the turbine does work.
7. The compact, high temperature fuel pyrolysis gas power generation turbine seal cooling structure of claim 1, wherein: the first eddy current sensor mounting holes (8) and the second eddy current sensor mounting holes (22) are threaded holes, and the eddy current sensors are mounted in the threaded holes in a threaded connection mode.
8. The compact, high temperature fuel pyrolysis gas power generation turbine seal cooling structure of claim 1, wherein: the sealing gas inlet (23) on the cooling heat insulation cavity is provided with threads, a three-way pipe is connected with a pressure gauge sensor, the pressure gauge sensor monitors the pressure of high-temperature fuel pyrolysis gas leaked from an axial sealing position in real time, and the pressure of the sealing gas is regulated through feedback, so that the high-temperature working medium is prevented from leaking along the axial direction.
9. The compact, high temperature fuel pyrolysis gas power generation turbine seal cooling structure of claim 1, wherein: the impeller (7) and the turbine rotating shaft (4) are axially positioned through nuts.
10. A compact high temperature fuel cracking gas power generating turbine seal cooling structure according to any one of claims 1-9, characterized in that: the first comb tooth seal (9) and the turbine are integrally molded and cast, and the second comb tooth seal (18) and the cooling heat insulation cavity are integrally molded and cast.
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| CN118079785B (en) * | 2024-02-28 | 2025-09-23 | 宜春万申智能装备股份有限公司 | An air-sealed water-cooled rotary granulator |
| CN119957541B (en) * | 2025-01-03 | 2025-11-18 | 上海交通大学 | Supercritical carbon dioxide compressor low-leakage sealing system and control method |
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