CN117569923A - Turbine fulcrum structure of gas turbine - Google Patents

Turbine fulcrum structure of gas turbine Download PDF

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Publication number
CN117569923A
CN117569923A CN202410044382.1A CN202410044382A CN117569923A CN 117569923 A CN117569923 A CN 117569923A CN 202410044382 A CN202410044382 A CN 202410044382A CN 117569923 A CN117569923 A CN 117569923A
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CN
China
Prior art keywords
turbine
bearing
casing
assembly
ring
Prior art date
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Granted
Application number
CN202410044382.1A
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Chinese (zh)
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CN117569923B (en
Inventor
王鸣
方圆
齐振彪
杜治能
蔡鹏�
徐世辉
陶思佚
赵芳亮
王梁丞
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Chengdu Zhongke Yineng Technology Co Ltd
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Chengdu Zhongke Yineng Technology Co Ltd
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Priority to CN202410044382.1A priority Critical patent/CN117569923B/en
Publication of CN117569923A publication Critical patent/CN117569923A/en
Application granted granted Critical
Publication of CN117569923B publication Critical patent/CN117569923B/en
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/20—Mounting or supporting of plant; Accommodating heat expansion or creep
    • 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
    • F01D1/00—Non-positive-displacement machines or engines, e.g. steam turbines
    • F01D1/02—Non-positive-displacement machines or engines, e.g. steam turbines with stationary working-fluid guiding means and bladed or like rotor, e.g. multi-bladed impulse steam turbines
    • F01D1/04—Non-positive-displacement machines or engines, e.g. steam turbines with stationary working-fluid guiding means and bladed or like rotor, e.g. multi-bladed impulse steam turbines traversed by the working-fluid substantially axially
    • 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
    • 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
    • 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
    • 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
    • F01D25/162—Bearing supports
    • 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
    • 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
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • 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
    • F01D25/28—Supporting or mounting arrangements, e.g. for turbine casing
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/06—Arrangements of bearings; Lubricating
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/12—Cooling of plants
    • F02C7/14—Cooling of plants of fluids in the plant, e.g. lubricant or fuel
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/12—Cooling of plants
    • F02C7/16—Cooling of plants characterised by cooling medium
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/12—Cooling of plants
    • F02C7/16—Cooling of plants characterised by cooling medium
    • F02C7/18—Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

The invention discloses a turbine fulcrum structure of a gas turbine, which comprises a turbine casing, a turbine blade assembly and a bearing casing, wherein two ends of the turbine blade assembly are respectively connected with the turbine casing and the bearing casing; the turbine engine comprises a turbine blade assembly, a turbine casing, a bearing casing, a guide pipe assembly, an oil pipe assembly, an air cooling cavity, an oil pipe assembly, an oil circuit circulation flow channel, an air cooling cavity, an oil pipe assembly and an air circulation flow channel. According to the invention, the air circulation flow passage is established between the air pipe group and the air cooling cavity, and the bearing oil cavity can exchange heat with the air cooling cavity, so that the air pipe group can cool the bearing oil cavity and form a blowing system of the bearing oil cavity, thereby effectively cooling the bearing casing and lubricating oil.

Description

Turbine fulcrum structure of gas turbine
Technical Field
The invention belongs to the technical field of gas turbines, and particularly relates to a turbine fulcrum structure of a gas turbine.
Background
A gas turbine is an internal combustion type power machine that converts energy of gas into useful work, and is widely used in aerospace vehicles. The working process of the gas turbine is as follows: the compressor continuously sucks air from the atmosphere and compresses the air; the compressed air enters the combustion chamber, is mixed with the gas sprayed into the combustion chamber and then is combusted, so that high-temperature gas is formed, then flows into the gas turbine to expand and do work, and the high-temperature gas pushes the turbine to rotate together with the gas compressor. The gas turbine is a device with good cleanliness and high efficiency, has the advantages of small volume, low weight and the like, and is widely applied to the fields of power generation, independent energy systems, mechanical driving and the like. Since the advent of gas turbines, the gas turbines have the advantages of large power, small volume, quick start, stable operation, capability of using various fuels and the like, have gained wide acceptance at home and abroad, and meanwhile, a great deal of research work has been carried out on the gas turbines by a plurality of scientific and technological workers at home and abroad, and the gas turbines have developed across in a short time, so that the gas turbines are widely applied to the fields of power machinery such as aviation, ships and the like and the industrial fields such as electric power, chemical industry and the like.
In a gas turbine of a dual-rotor gas turbine, a supporting structure adopted by the turbine is often a structural scheme for transferring force on a rear support plate of the turbine or a structural scheme for transferring force on a pull rod body between a high-pressure turbine and a low-pressure turbine; the high-low pressure turbine fulcrum force transmission scheme is that a turbine rotating shaft between a high-low pressure turbine is connected and supported by a bearing casing and then is connected to the turbine casing by a turbine guide blade, so that the turbine rotating shaft is supported to the middle part of a flame tube, namely: a turbine guide blade, an arc area part on a bearing casing correspondingly connected with the turbine guide blade and an arc part on the turbine casing form a turbine fulcrum, and the turbine fulcrum is used for supporting a turbine rotating shaft at a position between a high-pressure turbine blade and a low-pressure turbine blade; the high-low pressure turbine fulcrum force transmission scheme has the advantages that the length of a low pressure turbine rotating shaft can be shortened, and the stability of a rotor is improved; in the above turbine supporting structure, the tie rod body for connecting and transferring force between the turbine guide blade and the turbine casing or the bearing casing often adopts a solid cylindrical structure, and when the tie rod body passes through and is connected with the inside of the turbine guide blade, the turbine casing and the bearing casing can be combined into a frame load-carrying structure. The cylindrical pull rod body structure has the advantages of simple structure, but the defects of low bearing capacity, weak environmental temperature resistance and the like exist, the reason is that the inner space of the turbine guide vane is smaller, the diameter size of the applicable cylindrical pull rod body is limited, the wall surface of the turbine guide vane is higher in temperature, the temperature of the pull rod body can be increased by heat radiation to the pull rod body, and the bearing uniformity of the turbine supporting structure and the concentricity of the bearing casing can be influenced when the pull rod body is thermally deformed. Therefore, designing a turbine fulcrum structure that remains sufficiently rigid at high temperatures is a currently highly desirable problem.
Disclosure of Invention
It is an object of the present invention to provide a gas turbine fulcrum structure for solving the above-mentioned problems of the prior art.
In order to achieve the above purpose, the present invention adopts the following technical scheme: the turbine fulcrum structure of the gas turbine comprises a turbine casing, a turbine blade assembly and a bearing casing, wherein the turbine blade assembly is arranged between the turbine casing and the bearing casing, a bearing oil cavity is arranged between the bearing casing and a turbine rotor, and an air cooling cavity capable of exchanging heat with the bearing oil cavity is arranged inside the bearing casing; the turbine engine comprises a turbine blade assembly, and is characterized by further comprising a conduit assembly, wherein the conduit assembly is arranged inside the turbine blade assembly in a penetrating manner, two ends of the conduit assembly are respectively connected with the turbine casing and the bearing casing, the conduit assembly comprises an oil pipe group and an air pipe group, the oil pipe group is communicated with the bearing oil cavity and forms an oil circuit circulation flow channel, and the air pipe group is communicated with the air cooling cavity and forms an air circulation flow channel.
As an optional implementation manner of the above technical solution, the turbine casing includes a turbine outer casing assembly and a turbine inner casing assembly, the turbine outer casing assembly is disposed at an outer side of the turbine inner casing assembly, and a first heat insulation ring block and a second heat insulation ring block are disposed between the turbine inner casing assembly and the turbine blade assembly.
As an optional implementation manner of the above technical scheme, the first heat insulation ring block comprises a plurality of heat insulation blocks which are annularly distributed, an expansion compensation plate is embedded between two adjacent heat insulation blocks, and inner lining rings are arranged on the inner sides of the plurality of heat insulation blocks which are annularly distributed.
As an optional implementation manner of the technical scheme, an opening positioning ring is arranged between one side of the first heat insulation ring block and the inner casing component of the turbine, and a plugging cover is arranged on the other side of the first heat insulation ring block and is fixed on the inner casing component of the turbine through bolts.
As an optional implementation manner of the above technical solution, the bearing casing includes an outer casing component and an inner casing component, the outer casing component is connected with the turbine blade component, the inner casing component is disposed on the inner side of the outer casing component, the air cooling cavity is formed between the inner casing component and the outer casing component, and the bearing oil cavity is formed between the inner casing component and the turbine rotor.
As an optional implementation manner of the technical scheme, an air cavity communicated with the air cooling cavity is formed between the bearing outer casing assembly and the turbine blade assembly, a bearing pull rod is connected between the turbine casing and the bearing outer casing assembly, an air channel is arranged in the bearing pull rod, one end of the air channel is communicated with the external environment, and the other end of the air channel is communicated with the air cavity.
As an optional implementation manner of the above technical solution, the force-bearing pull rod includes a rod body, the rod body is in clearance fit with the blade cavity of the turbine blade assembly, and an outer wall surface of the rod body is not in contact with a wall surface of the blade cavity.
As an alternative implementation manner of the above technical solution, a connecting portion is provided at one end of the shaft, the connecting portion is provided with a tightening connecting hole and an exhaust hole, the tightening connecting hole can be connected with a tightening screw for fixing the bearing pull rod, and the exhaust hole is communicated with the air channel; the other end of the rod body is provided with a rod cap part protruding outwards.
As an optional implementation manner of the above technical solution, the cross section shape of the force-bearing pull rod is elliptical, chamfered rectangle or chamfered trapezoid, and the cross section shape of the air channel is correspondingly elliptical, chamfered rectangle or chamfered trapezoid.
As an optional implementation manner of the above technical scheme, the bearing outer casing assembly comprises a bearing outer casing ring, one end of the air pipe group is connected with the bearing outer casing ring, two sides of the bearing outer casing ring are respectively provided with a left side plate assembly and a right side plate assembly, the left side plate assembly and the right side plate assembly are connected with the turbine blade assembly, and the left side plate assembly, the bearing outer casing ring, the right side plate assembly and the turbine blade assembly enclose the air cooling cavity.
As an optional implementation manner of the above technical scheme, an annular partition plate is arranged in the air cavity, and a through hole matched with the catheter assembly is formed in the annular partition plate.
As an optional implementation manner of the above technical scheme, the bearing inner casing assembly comprises a bearing inner casing ring, one end of the oil pipe group is connected with the bearing inner casing ring, one side of the bearing inner casing ring is provided with a front outer sealing ring and a front inner sealing ring, and the other side of the bearing inner casing ring is provided with a rear outer sealing ring and a rear inner sealing ring.
As an optional implementation manner of the technical scheme, the oil pipe group comprises at least one oil inlet pipe and at least two oil outlet pipes, the oil inlet pipe and the oil outlet pipes are both used for connecting the turbine casing and the bearing casing, and the oil inlet pipe and the oil outlet pipes are both communicated with the bearing oil cavity.
As an optional implementation manner of the above technical scheme, the air tube set comprises an air inlet tube and an air outlet tube which are oppositely arranged, the air inlet tube and the air outlet tube are both used for connecting the turbine casing and the bearing casing, and the air inlet tube and the air outlet tube are both communicated with the air cooling cavity.
As an optional implementation manner of the foregoing technical solution, the catheter assembly further includes a gas exhaust pipe group, and the gas exhaust pipe group is communicated with the bearing oil cavity; the exhaust pipe group comprises at least three exhaust pipes, the exhaust pipes are used for connecting the turbine casing and the bearing casing, and the exhaust pipes are communicated with the bearing oil cavity.
As an optional implementation manner of the above technical solution, the turbine blade assembly includes a turbine outer ring, a turbine inner ring and a plurality of guide blades, the turbine outer ring is connected with the turbine casing, the turbine inner ring is connected with the bearing casing, the turbine inner ring is disposed inside the turbine outer ring, and two ends of the guide blades are respectively connected with the turbine outer ring and the turbine inner ring.
The beneficial effects of the invention are as follows:
the invention provides a turbine fulcrum structure of a gas turbine, wherein an oil pipe group and an air pipe group are connected with a turbine casing and a bearing casing, the turbine casing and the bearing casing have radial supporting functions, the oil pipe group is communicated with a bearing oil cavity and forms an oil circuit circulation flow channel, the bearing casing can be lubricated and cooled, the air pipe group is communicated with an air cooling cavity and forms an air circulation flow channel, so that external cold air can enter the air cooling cavity to cool the bearing casing, and stable continuous operation of equipment is ensured. According to the invention, the air circulation flow channel is established between the air pipe group and the air cooling cavity, and the bearing oil cavity can exchange heat with the air cooling cavity, so that the air pipe group can cool the bearing oil cavity and form a blowing system of the bearing oil cavity, thereby effectively cooling the bearing casing and lubricating oil and ensuring the rigidity of the turbine fulcrum structure.
Drawings
FIG. 1 is a schematic perspective view of a turbine fulcrum structure of a gas turbine in accordance with one embodiment of the present invention;
FIG. 2 is an enlarged view of portion a of FIG. 1;
FIG. 3 is a schematic front view of a gas turbine fulcrum structure in accordance with an embodiment of the present invention;
FIG. 4 is a partial cross-sectional view of A-A of FIG. 3;
FIG. 5 is an enlarged view of section b of FIG. 4;
FIG. 6 is an enlarged view of section c of FIG. 4;
FIG. 7 is a partial cross-sectional view of B-B of FIG. 3;
FIG. 8 is a partial cross-sectional view of C-C of FIG. 3;
FIG. 9 is a schematic view of the structure of a first insulating ring block in one embodiment of the invention;
FIG. 10 is an enlarged view of section d of FIG. 9;
fig. 11 is a schematic structural view of a load-bearing tie according to an embodiment of the present invention.
In the figure: 1-a turbine casing; 2-a turbine blade assembly; 3-bearing casing;
101-a turbine outer casing assembly; 102-a turbine inner casing assembly; 103-a first insulating ring block; 104-a second insulating ring block; 105-insulating blocks; 106-an expansion compensation plate; 107-inner liner ring; 108-an open positioning ring; 109-a closure cap;
201-turbine outer ring; 202-a turbine inner ring; 203-guide vanes;
301-bearing oil chamber; 302-an air cooling chamber; 303-bearing outer casing assembly; 304-an inner casing assembly of the bearing; 305-air lumen; 306-a force-bearing pull rod; 307-air channels; 308-shaft; 309-vent holes; 310-tightening the screw; 311-a cap; 312-bearing outer casing ring; 313-left side panel assembly; 314-right side plate assembly; 315-annular separator; 316-inner casing ring of bearing; 317-front outer layer sealing ring; 318-front inner layer sealing ring; 319-sealing the outer layer; 320-a rear inner layer sealing ring;
401-an oil inlet pipe; 402-an oil outlet pipe; 403-air inlet pipe; 404-an outlet pipe; 405-exhaust pipe.
Detailed Description
The following describes specific embodiments of the present invention in detail with reference to the drawings.
As shown in fig. 1-11, the present embodiment provides a turbine fulcrum structure of a gas turbine, including a turbine casing 1, a turbine blade assembly 2 and a bearing casing 3, wherein the turbine blade assembly 2 is disposed between the turbine casing 1 and the bearing casing 3, a bearing oil cavity 301 is disposed between the bearing casing 3 and a turbine rotor, and an air cooling cavity 302 capable of exchanging heat with the bearing oil cavity 301 is disposed inside the bearing casing 3. The bearing casing 3 is cast by adopting the alloy ZG1Cr11Ni2W2MoV, and the alloy ZG1Cr11Ni2W2MoV is a heat-resistant stainless steel material, has good comprehensive mechanical properties, and excellent high-temperature, high-pressure and corrosion properties, and can bear a severe working environment.
The turbine blade assembly 2 comprises a turbine outer ring 201, a turbine inner ring 202 and a plurality of guide blades 203, wherein the turbine outer ring 201 is connected with the turbine casing 1, the turbine inner ring 202 is connected with the bearing casing 3, the turbine inner ring 202 is arranged inside the turbine outer ring 201, and two ends of the guide blades 203 are respectively connected with the turbine outer ring 201 and the turbine inner ring 202. The guide vane 203 has a vane cavity, and the surface of the guide vane 203 has a through hole, so that the heat dissipation of the guide vane 203 is facilitated. The turbine outer ring 201 and the turbine inner ring 202 are designed in a segmented mode, and the turbine outer ring 201 and the turbine inner ring 202 are divided into 15 sector sections, and each sector section is connected with two guide blades 203. The segments are secured circumferentially by pins and axially compressed by rings. Both the sector section and the guide vane 203 are cast and processed by K640S material, which can be used for a long term under high temperature condition, has excellent mechanical property and is very suitable for gas turbine. The gas turbine output continues to rise and the inlet temperature becomes higher, the guide vanes 203 first experience more severe temperature conditions than before. Each guide vane 203 is hollow and is a cooling system component for passing cooling gas.
The turbine fulcrum structure further comprises a conduit assembly, the conduit assembly penetrates through the turbine blade assembly 2, two ends of the conduit assembly are respectively connected with the turbine casing 1 and the bearing casing 3, the conduit assembly comprises an oil pipe group and an air pipe group, the oil pipe group is communicated with the bearing oil cavity 301 and forms an oil circuit circulation flow channel, and the air pipe group is communicated with the air cooling cavity 302 and forms an air circulation flow channel. The oil tube group and the air tube group are both connected with the turbine casing 1 and the bearing casing 3, the oil tube group has a radial supporting function, the oil tube group is communicated with the bearing oil cavity 301 to form an oil circuit circulation flow channel, the bearing casing 3 can be lubricated and cooled, the air tube group is communicated with the air cooling cavity 302 to form an air circulation flow channel, so that external cold air can enter the air cooling cavity 302 to cool the bearing casing 3, and stable continuous operation of equipment is ensured. In the invention, the air circulation flow passage is established between the air tube group and the air cooling cavity 302, and the bearing oil cavity 301 can exchange heat with the air cooling cavity 302, so that the air tube group can cool the bearing oil cavity 301 and form a blowing system of the bearing oil cavity 301, thereby effectively cooling the bearing casing 3 and lubricating oil and ensuring the rigidity of the turbine fulcrum structure.
As shown in fig. 3, in the present embodiment, the turbine casing 1 includes a turbine outer casing assembly 101 and a turbine inner casing assembly 102, the turbine outer casing assembly 101 is disposed outside the turbine inner casing assembly 102, and one ends of an oil pipe group and an air pipe group are both fixed to the turbine outer casing assembly 101. As shown in fig. 5 and 6, a first heat insulation ring block 103 and a second heat insulation ring block 104 are arranged between the inner casing assembly 102 and the outer ring 201 of the turbine, so that heat transfer of the turbine blade assembly 2 to the inner casing assembly 102 of the turbine is reduced.
As shown in fig. 5, 9 and 10, the first heat insulating ring block 103 preferably includes a plurality of heat insulating blocks 105 arranged in a ring shape, and a lining ring 107 is provided inside the plurality of heat insulating blocks 105 arranged in a ring shape to secure the strength of the first heat insulating ring block 103. An expansion compensation plate 106 is embedded between two adjacent heat insulation blocks 105, and the expansion compensation plate 106 can compensate cold and hot deformation of the heat insulation blocks 105, so that tightness between the heat insulation blocks 105 is ensured. The heat insulation block 105 is made of nickel-based alloy GH4099, and the material alloy structure is stable, is a reinforced high-temperature alloy, has satisfactory cold forming and welding process performances, and is suitable for high Wen Chengli welding structural members.
As shown in fig. 5, an opening positioning ring 108 is arranged between one side of the first heat insulation ring block 103 and the inner casing assembly 102 of the turbine, a blocking cover 109 is arranged on the other side of the first heat insulation ring block 103, and the blocking cover 109 is fixed on the inner casing assembly 102 of the turbine through bolts, so that the first heat insulation ring block 103 is convenient to install.
As shown in fig. 3, in the present embodiment, the bearing casing 3 includes an outer bearing casing assembly 303 and an inner bearing casing assembly 304, the outer bearing casing assembly 303 is connected to the turbine inner ring 202, the inner bearing casing assembly 304 is disposed inside the outer bearing casing assembly 303, an air cooling chamber 302 is formed between the inner bearing casing assembly 304 and the outer bearing casing assembly 303, and a bearing oil chamber 301 is formed between the inner bearing casing assembly 304 and the turbine rotor.
As shown in fig. 4, in order to further improve the heat dissipation effect of the bearing casing 3, an air cavity 305 communicating with the air cooling cavity 302 is provided between the bearing outer casing assembly 303 and the turbine blade assembly 2, a bearing pull rod 306 is connected between the turbine casing 1 and the bearing outer casing assembly 303, an air channel 307 is provided in the bearing pull rod 306, one end of the air channel 307 communicates with the external environment, and the other end of the air channel 307 communicates with the air cavity 305. The cross-sectional shape of the load-bearing tie rod 306 is elliptical, chamfered rectangular or chamfered trapezoidal, and the cross-sectional shape of the air passage 307 corresponds to an elliptical, chamfered rectangular or chamfered trapezoidal shape.
As shown in fig. 11, specifically, the load-bearing tie 306 includes a shaft 308, the shaft 308 is clearance-fitted with the blade cavity of the turbine blade assembly 2, and the outer wall surface of the shaft 308 is not in contact with the wall surface of the blade cavity. One end of the rod body 308, which is close to the turbine outer casing assembly 101, is provided with a connecting part for connecting with the turbine outer casing assembly 101, the connecting part is provided with a tensioning connecting hole and an exhaust hole 309, the tensioning connecting hole can be connected with a tensioning screw 310 for fixing the bearing pull rod 306, the exhaust hole 309 is communicated with the air channel 307, the exhaust hole 309 is provided with a connector, the connector is provided with a vent hole, and the vent hole is communicated with the air channel 307; the other end of the shaft 308 is provided with a shaft cap portion 311 protruding outward, and the shaft cap portion 311 is adapted to be connected to the bearing housing 3.
After the bearing pull rod 306 penetrates into the turbine blade assembly 2, the bearing pull rod 306 can be fastened and connected through the connecting part, and the connecting mode is not different from the screw connection or the bolt connection mode in the prior art; however, since the existing bearing tie rods 306 mostly adopt a cylindrical structure, the space occupied by the bearing tie rods 306 in the circumferential direction of the turbine casing 1 and the bearing casing 3 is more, so that holes with larger width in the circumferential direction need to be formed at the joints of the bearing tie rods, and therefore, more factors need to calculate stress when designing the turbine blade assembly 2, if the bearing tie rods 306 adopting the cylindrical structure are adopted, higher material structures need to be adopted at the joints when designing, or the diameter of the bearing tie rods 306 needs to be reduced; both of which are detrimental to the stability of the turbine blade assembly 2. Therefore, in this embodiment, the bearing pull rod 306 adopts a non-cylindrical special-shaped structure, and the special-shaped structure adopts a flat structural design, so that the occupied space of the bearing pull rod 306 in the circumferential direction of the turbine casing 1 is lower, and meanwhile, the radial width of the bearing pull rod 306 can be reinforced, so that the reinforced supporting force can be provided in the radial direction of the turbine casing 1, and the turbine blade assembly 2, the bearing casing 3 and the turbine casing 1 have good stability at the joint and long service life.
As shown in fig. 4, in the present embodiment, the bearing outer casing assembly 303 includes a bearing outer casing ring 312, one end of the air tube set is connected to the bearing outer casing ring 312, two sides of the bearing outer casing ring 312 are respectively provided with a left side plate assembly 313 and a right side plate assembly 314, the left side plate assembly 313 and the right side plate assembly 314 are connected to the turbine blade assembly 2, and the left side plate assembly 313, the bearing outer casing ring 312, the right side plate assembly 314 and the turbine blade assembly 2 enclose an air cavity 305. To facilitate air flow and dispersion, an annular spacer 315 is disposed within the air chamber 305, and the annular spacer 315 is provided with through holes adapted to the conduit assembly. The oil tube group and the air tube group can pass through the through holes on the annular partition 315, so that the oil and air can be conveniently conveyed. The bearing inner casing assembly 304 comprises a bearing inner casing ring 316, one end of the oil pipe group is connected with the bearing inner casing ring 316, one side of the bearing inner casing ring 316 is provided with a front outer sealing ring 317 and a front inner sealing ring 318, and the other side of the bearing inner casing ring 316 is provided with a rear outer sealing ring 319 and a rear inner sealing ring 320.
The front outer seal ring 317, the front inner seal ring 318, the rear outer seal ring 319, and the rear inner seal ring 320 are each manufactured from alloy 0Cr11Ni2MoVNb for establishing the bearing oil chamber 301. Bearing oil chamber 301 may exchange heat with air cooling chamber 302, thereby reducing the oil temperature.
As shown in fig. 3, 4, 7 and 8, in the present embodiment, the oil pipe group includes at least one oil inlet pipe 401 and at least two oil outlet pipes 402, and the oil inlet pipe 401 and the oil outlet pipe 402 are each used for connecting the turbine outer casing assembly 101 and the bearing inner casing assembly 304, and the oil inlet pipe 401 and the oil outlet pipe 402 are each in communication with the bearing oil chamber 301. The air pipe group comprises an air inlet pipe 403 and an air outlet pipe 404 which are oppositely arranged, wherein the air inlet pipe 403 and the air outlet pipe 404 are respectively used for connecting the turbine outer casing assembly 101 and the bearing outer casing assembly 303, and the air inlet pipe 403 and the air outlet pipe 404 are respectively communicated with the air cooling cavity 302. The catheter assembly further includes a set of exhaust tubing in communication with the bearing oil chamber 301; specifically, the exhaust pipe group includes at least three exhaust pipes 405, and exhaust pipe 405 is used for connecting the outer casing assembly 101 of turbine and the inner casing assembly 304 of bearing, and exhaust pipe 405 communicates with bearing oil chamber 301, sets up the seal head on the exhaust pipe 405, ensures the leakproofness of bearing oil chamber 301.
The oil inlet pipe 401, the oil outlet pipe 402, the air inlet pipe 403, the air outlet pipe 404 and the air outlet pipe 405 are all cast or punched by the material K414, K414 is nickel-based precipitation hardening type equiaxial crystal cast superalloy, is high-temperature alloy used in high-temperature sections of aeroengines and gas turbines, and has good wear resistance, stretch resistance and impact resistance.
In the description of the present invention, the terms "mounted," "connected," "secured," and the like are to be construed broadly and may be fixedly connected, detachably connected, or integrally formed; may be a mechanical or electrical connection; may be directly connected or indirectly connected through an intermediate medium, and may be in communication with the inside of two elements or in interaction with the two elements, the specific meaning of the terms being understood by those skilled in the art. Furthermore, the particular features, structures, etc. described in the examples are included in at least one embodiment and those of skill in the art may combine features of different embodiments without contradiction. The scope of the present invention is not limited to the above-described specific embodiments, and embodiments which can be suggested to those skilled in the art without inventive effort according to the basic technical concept of the present invention are all within the scope of the present invention.

Claims (10)

1. The gas turbine fulcrum structure comprises a turbine casing (1), a turbine blade assembly (2) and a bearing casing (3), wherein the turbine blade assembly (2) is arranged between the turbine casing (1) and the bearing casing (3), a bearing oil cavity (301) is arranged between the bearing casing (3) and a turbine rotor, and the gas turbine fulcrum structure is characterized in that an air cooling cavity (302) capable of exchanging heat with the bearing oil cavity (301) is arranged inside the bearing casing (3); the turbine engine comprises a turbine blade assembly (2), and is characterized by further comprising a conduit assembly, wherein the conduit assembly is arranged inside the turbine blade assembly (2) in a penetrating manner, two ends of the conduit assembly are respectively connected with a turbine casing (1) and a bearing casing (3), the conduit assembly comprises an oil pipe group and an air pipe group, the oil pipe group is communicated with a bearing oil cavity (301) and forms an oil circuit circulation flow channel, and the air pipe group is communicated with an air cooling cavity (302) and forms an air circulation flow channel.
2. The gas turbine fulcrum structure according to claim 1, wherein the turbine casing (1) comprises a turbine outer casing assembly (101) and a turbine inner casing assembly (102), the turbine outer casing assembly (101) is arranged outside the turbine inner casing assembly (102), and a first heat insulation ring block (103) and a second heat insulation ring block (104) are arranged between the turbine inner casing assembly (102) and the turbine blade assembly (2).
3. The turbine fulcrum structure of claim 2, wherein the first heat-insulating ring block (103) comprises a plurality of heat-insulating blocks (105) arranged in a ring shape, an expansion compensation plate (106) is embedded between two adjacent heat-insulating blocks (105), and an inner lining ring (107) is arranged on the inner side of the plurality of heat-insulating blocks (105) arranged in a ring shape.
4. The gas turbine fulcrum structure of claim 2, wherein an open positioning ring (108) is provided between one side of the first heat insulating ring block (103) and the turbine inner casing assembly (102), and a plugging cover (109) is provided on the other side of the first heat insulating ring block (103), and the plugging cover (109) is fixed on the turbine inner casing assembly (102) through bolts.
5. The gas turbine fulcrum structure of claim 1, wherein the bearing casing (3) comprises an outer casing assembly (303) and an inner casing assembly (304), the outer casing assembly (303) is connected with the turbine blade assembly (2), the inner casing assembly (304) is disposed inside the outer casing assembly (303), the air cooling cavity (302) is formed between the inner casing assembly (304) and the outer casing assembly (303), and the bearing oil cavity (301) is formed between the inner casing assembly (304) and the turbine rotor.
6. The gas turbine fulcrum structure according to claim 5, characterized in that an air cavity (305) communicated with the air cooling cavity (302) is arranged between the bearing outer casing assembly (303) and the turbine blade assembly (2), a bearing pull rod (306) is connected between the turbine casing (1) and the bearing outer casing assembly (303), an air channel (307) is arranged in the bearing pull rod (306), one end of the air channel (307) is communicated with the external environment, and the other end of the air channel (307) is communicated with the air cavity (305); the bearing pull rod (306) comprises a rod body (308), the rod body (308) is in clearance fit with the inner cavity of the blade of the turbine blade assembly (2), and the outer wall surface of the rod body (308) is not contacted with the wall surface of the inner cavity of the blade; one end of the rod body (308) is provided with a connecting part, the connecting part is provided with a tensioning connecting hole and an exhaust hole (309), the tensioning connecting hole can be connected with a tensioning screw (310) for fixing the bearing pull rod (306), and the exhaust hole (309) is communicated with the air channel (307); the other end of the rod body (308) is provided with a rod cap part (311) protruding outwards; the cross section of the bearing pull rod (306) is elliptical, chamfered rectangle or chamfered trapezoid, and the cross section of the air channel (307) is correspondingly elliptical, chamfered rectangle or chamfered trapezoid.
7. The gas turbine fulcrum structure of claim 6, wherein the bearing outer casing assembly (303) comprises a bearing outer casing ring (312), one end of the air pipe group is connected with the bearing outer casing ring (312), two sides of the bearing outer casing ring (312) are respectively provided with a left side plate assembly (313) and a right side plate assembly (314), the left side plate assembly (313) and the right side plate assembly (314) are both connected with the turbine blade assembly (2), and the left side plate assembly (313), the bearing outer casing ring (312), the right side plate assembly (314) and the turbine blade assembly (2) enclose the air cooling cavity (302); an annular partition plate (315) is arranged in the air cavity (305), and a through hole matched with the catheter assembly is formed in the annular partition plate (315).
8. The gas turbine fulcrum structure of claim 7, wherein the bearing inner casing assembly (304) comprises a bearing inner casing ring (316), one end of the oil pipe group is connected with the bearing inner casing ring (316), one side of the bearing inner casing ring (316) is provided with a front outer sealing ring (317) and a front inner sealing ring (318), and the other side of the bearing inner casing ring (316) is provided with a rear outer sealing ring (319) and a rear inner sealing ring (320).
9. The gas turbine fulcrum structure of claim 1, wherein the oil tube set comprises at least one oil inlet tube (401) and at least two oil outlet tubes (402), the oil inlet tube (401) and the oil outlet tubes (402) are each used for connecting a turbine casing (1) and a bearing casing (3), and the oil inlet tube (401) and the oil outlet tubes (402) are each in communication with a bearing oil chamber (301);
the air pipe group comprises an air inlet pipe (403) and an air outlet pipe (404) which are oppositely arranged, the air inlet pipe (403) and the air outlet pipe (404) are both used for connecting the turbine casing (1) and the bearing casing (3), and the air inlet pipe (403) and the air outlet pipe (404) are both communicated with the air cooling cavity (302);
the conduit assembly further comprises a drain tube set in communication with the bearing oil chamber (301); the exhaust pipe group comprises at least three exhaust pipes (405), the exhaust pipes (405) are used for connecting the turbine casing (1) and the bearing casing (3), and the exhaust pipes (405) are communicated with the bearing oil cavity (301).
10. The gas turbine fulcrum structure according to claim 1, wherein the turbine blade assembly (2) comprises a turbine outer ring (201), a turbine inner ring (202) and a plurality of guide blades (203), the turbine outer ring (201) is connected with the turbine casing (1), the turbine inner ring (202) is connected with the bearing casing (3), the turbine inner ring (202) is arranged inside the turbine outer ring (201), and two ends of the guide blades (203) are respectively connected with the turbine outer ring (201) and the turbine inner ring (202).
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