CN109404049B - Helium turbine connecting structure capable of being quickly disassembled and assembled - Google Patents
Helium turbine connecting structure capable of being quickly disassembled and assembled Download PDFInfo
- Publication number
- CN109404049B CN109404049B CN201811625049.0A CN201811625049A CN109404049B CN 109404049 B CN109404049 B CN 109404049B CN 201811625049 A CN201811625049 A CN 201811625049A CN 109404049 B CN109404049 B CN 109404049B
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- China
- Prior art keywords
- turbine
- casing
- rotor
- guide vane
- stator
- Prior art date
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- 239000001307 helium Substances 0.000 title claims abstract description 29
- 229910052734 helium Inorganic materials 0.000 title claims abstract description 29
- SWQJXJOGLNCZEY-UHFFFAOYSA-N helium atom Chemical compound [He] SWQJXJOGLNCZEY-UHFFFAOYSA-N 0.000 title claims abstract description 29
- 239000007789 gas Substances 0.000 claims abstract description 10
- 238000007789 sealing Methods 0.000 claims description 49
- 238000001816 cooling Methods 0.000 claims description 29
- 239000007787 solid Substances 0.000 claims description 2
- 238000007599 discharging Methods 0.000 claims 1
- 238000000034 method Methods 0.000 claims 1
- 239000000203 mixture Substances 0.000 description 8
- 238000010276 construction Methods 0.000 description 1
- 238000013016 damping Methods 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
Classifications
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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
- 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
- F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
- F01D25/243—Flange connections; Bolting 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
- F01D25/246—Fastening of diaphragms or stator-rings
-
- 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
- F01D25/26—Double casings; Measures against temperature strain in casings
-
- 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
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/025—Fixing blade carrying members on shafts
-
- 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
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/027—Arrangements for balancing
-
- 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
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/06—Rotors for more than one axial stage, e.g. of drum or multiple disc type; Details thereof, e.g. shafts, shaft connections
-
- 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
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/08—Heating, heat-insulating or cooling means
- F01D5/085—Heating, heat-insulating or cooling means cooling fluid circulating inside the rotor
-
- 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
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
- F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
Abstract
A helium turbine connecting structure capable of being quickly disassembled and assembled relates to the field of helium compressors. The invention solves the problems that the existing helium gas compressor has a turbine casing with a non-middle-split integrated structure, a turbine shell is not easy to disassemble and assemble, and a turbine rotor wheel disc with an integrated structure is difficult to assemble. The turbine stator is sleeved on the turbine rotor, two ends of the turbine stator are respectively connected with an external air inlet casing and an external air outlet casing, long pull rod bolts of the turbine rotor sequentially penetrate through first bolt holes of six rotor wheel discs, one ends of the long pull rod bolts are bolted with a turbine front shaft which is coaxially arranged, and the other ends of the long pull rod bolts are bolted with a turbine rear shaft which is coaxially arranged; the turbine casing is of an integral cylindrical structure, six stator guide vane rings of the turbine stator are sequentially arranged on the inner circumference of the turbine casing from front to back, and the six stator guide vane rings and the six rotor wheel discs are arranged in a staggered mode. The quick dismounting device is used for quick dismounting of the turbine shell of the helium gas compressor.
Description
Technical Field
The invention relates to the field of helium compressors, in particular to a helium turbine connecting structure capable of being quickly disassembled and assembled.
Background
The turbine is a component in a gas turbine engine, which utilizes high-temperature gas to push blades to rotate at a high speed to drive a load to perform work. Helium is mainly used as a working medium for the helium compressor. The turbine is an important component of the helium compressor, and mainly comprises a turbine rotor, a turbine casing, an air inlet casing, an exhaust casing, a stator guide and each stator blade ring in terms of assembly structure and functions. Because the overall size of the unit is smaller and the rotating speed is high, the sealing requirement is higher. The turbine casing adopts a non-middle-divided integral structure, so that the structural design difficulty of the turbine rotor is high. Because the turbine temperature field is more complex, the turbine is deformed and complicated at high temperature and high rotating speed, internal part faults are very easy to generate, and the existing turbine casing is of an integrated structure, so that the turbine casing is not easy to disassemble and assemble, and great difficulty is brought to maintenance and replacement of parts in the turbine casing.
In summary, the existing helium gas compressor has the problems that the turbine casing is of a non-split integrated structure, the turbine shell is not easy to disassemble and assemble, the turbine rotor wheel disc is of an integrated structure, and the assembly difficulty is high.
Disclosure of Invention
The invention aims to solve the problems that the existing helium gas compressor has a turbine casing with a non-middle-split integrated structure, a turbine shell is not easy to disassemble and assemble, a turbine rotor wheel disc with an integrated structure is difficult to assemble, and further provides a helium gas turbine connecting structure capable of being disassembled and assembled quickly.
The technical scheme of the invention is as follows:
a helium turbine connecting structure capable of being quickly disassembled and assembled comprises a turbine rotor and a turbine stator, wherein the turbine stator is sleeved on the turbine rotor, two ends of the turbine stator are respectively connected with an external steam inlet casing and an external steam outlet casing,
the turbine rotor comprises a turbine front shaft, a turbine rear shaft, six rotor wheel discs and 2N long pull rod bolts, wherein N is a positive integer greater than or equal to the positive integer,
the outer diameters of the six rotor disks are the same, N first cooling air flow holes are uniformly distributed on the end face of each rotor disk along the circumferential direction, two first bolt holes are uniformly distributed between every two adjacent first cooling air flow holes, a front shaft end flange is arranged at one end of a turbine front shaft, a rear shaft end flange is arranged at one end of a turbine rear shaft, 2N long pull rod bolts sequentially penetrate through the first bolt holes of the six rotor disks respectively, one end of each long pull rod bolt is in bolt connection with the front shaft end flange of the coaxially arranged turbine front shaft, and the other end of each long pull rod bolt is in bolt connection with the rear shaft end flange of the coaxially arranged turbine rear shaft;
the turbine stator comprises a turbine casing and six stator guide vane rings, the turbine casing is of an integral cylindrical structure, the six stator guide vane rings are sequentially arranged on the inner circumference of the turbine casing from front to back, and the six stator guide vane rings are staggered with the six rotor wheel discs.
Further, the turbine rotor also comprises six step tooth sealing rings, one step tooth sealing ring is arranged between two adjacent rotor wheel discs in the six rotor wheel discs, one step tooth sealing ring is arranged between the turbine front shaft and the rotor wheel disc adjacent to the turbine front shaft, the six step tooth sealing rings are in one-to-one correspondence with the six stator guide vane rings, the six stator guide vane rings are in sealing fit with the step teeth of the step tooth sealing rings,
the outer diameters of the six step tooth sealing rings are the same, N second cooling air flow holes are uniformly distributed on the end surface of each step tooth sealing ring along the circumferential direction, the N second cooling air flow holes on each step tooth sealing ring are in one-to-one correspondence with the N first cooling air flow holes on each rotor disk,
two second bolt holes are uniformly distributed between two adjacent second cooling air flow holes, 2N second bolt holes on each step tooth sealing ring are in one-to-one correspondence with 2N first bolt holes on each rotor wheel disc, and six step tooth sealing rings are connected with the rotor wheel disc through long pull rod bolts.
Further, the turbine rotor further comprises six moving blade units, each moving blade unit comprises a plurality of moving blades, the root of each moving blade is provided with a tenon tooth, a plurality of tenon grooves matched with the tenon tooth are circumferentially and uniformly distributed on the outer circumference of each rotor wheel disc, and the moving blades are connected with the rotor wheel disc through the tenon teeth and the tenon grooves which are matched with each other.
Further, the turbine stator further comprises six guard rings, one guard ring is arranged between two adjacent stator guide vane rings in the six stator guide vane rings, one guard ring is arranged between the outer steam outlet casing and the stator guide vane ring adjacent to the outer steam outlet casing, the six guard rings are sequentially arranged on the inner cylindrical surface of the turbine casing, the six guard rings correspond to the six moving blade units one by one, and the guard rings are in sealing fit with the blade teeth at the tail ends of the moving blades of the moving blade units.
Further, six annular guide vane grooves are uniformly formed in the inner circumference of the turbine casing, annular guide vane bosses matched with the annular guide vane grooves are arranged at the root of each stator guide vane ring, and the six stator guide vane rings are connected with the turbine casing through the annular guide vane grooves and the annular guide vane bosses which are matched with each other.
Further, an annular guard ring groove is arranged between two adjacent annular guide vane grooves on the inner circumference of the turbine box, an annular guard ring groove is arranged between the outer steam inlet casing and the annular guide vane groove adjacent to the annular guard ring groove, an annular guard ring boss matched with the annular guard ring groove is arranged at the root of each guard ring, and the six guard rings are connected with the turbine box through the annular guard ring grooves and the annular guard ring bosses matched with each other.
Further, the turbine casing comprises an inner casing and an outer casing, the inner diameters of the inner casing and the outer casing are equal, an inner casing connecting flange is arranged at one end of the inner casing, a first outer casing connecting flange is arranged at one end of the outer casing, and one end of the inner casing is bolted with one end of the outer casing through the inner casing connecting flange and the first outer casing connecting flange which are matched with each other.
Further, the other end of the inner casing is embedded into the outer casing 3, and the outer cylindrical surface of the inner casing is in clearance fit with the inner cylindrical surface of the outer casing.
Further, the other end of the outer casing is provided with a second outer casing connecting flange for being connected with an external steam outlet casing.
Compared with the prior art, the invention has the following effects:
1. the turbine rotor 1 of this embodiment is detachable in the axial direction, so that the turbine casing 2-1 that cooperates with the turbine rotor can adopt a non-split integral structure, so that the turbine rotor has good strength compared with the turbine casing adopting the split structure, and the thickness can be thinner under the condition of ensuring stability. The structure of the turbine rotor 1 can be simple and compact under the condition of meeting the use requirement. When the internal parts of the machine body need to be maintained and replaced, the disassembly and assembly of the parts are convenient, and the replacement speed and the working efficiency of the internal parts of the machine body are effectively improved.
2. The first cooling air flow holes 1-3-1 on the end faces of the six rotor disks 1-3 of the embodiment play a role in balancing air pressure, so that air pressure between the disk faces of the rotor disks 1-3 is effectively balanced, the rotor disks 1-3 only bear the tensile force of the long pull rod bolts 1-4 in the axial direction, the strength safety margin of the long pull rod bolts 1-4 is effectively protected, air in a sealing cavity formed by combining the six rotor disks 1-3 can be discharged, and air pressure in the six rotor disks 1-3 is equal to air pressure outside the turbine rotor 1. Because the rotor wheel disc 1-3 is of a solid circular structure, after the six rotor wheel discs 1-3 are combined, a sealing cavity is formed between the wheel discs, if the sealing cavity is designed to be of a dead space structure, gas in the sealing cavity of the wheel disc is heated when the helium turbine works, the temperature rises to generate thermal expansion force, and the long pull rod bolt 1-4 can be damaged, so that the long pull rod bolt 1-4 can be protected by the first cooling air flow hole 1-3-1, and the long pull rod bolt 1-4 is prevented from being damaged and deformed.
3. The turbine casing 2-1 of this embodiment adopts embedded structural design, and interior receiver 2-A one end is connected with the outer receiver 2-B of coaxial setting, and interior receiver 2-A other end embeds the inside of outside admission casing 3, has shortened six-level helium compressor turbine's overall length effectively, has saved the usage space.
4. The vibration-damping device has the advantages of good strength and vibration characteristics, safe and reliable structure and firm connection and positioning among parts.
Drawings
FIG. 1 is a schematic view of the assembly of the present invention with an external inlet and outlet casing;
FIG. 2 is a schematic illustration of the construction of a quick removable six helium compressor turbine housing of the present invention;
FIG. 3 is a schematic view of the turbine rotor structure of the present invention;
FIG. 4 is a schematic view of the turbine stator structure of the present invention;
FIG. 5 is a front view of the rotor disk of the present invention;
FIG. 6 is a cross-sectional view of a step tooth seal ring of the present invention.
Detailed Description
The first embodiment is as follows: referring to fig. 1 to 5, a helium turbine connecting structure capable of being quickly assembled and disassembled according to the present embodiment includes a turbine rotor 1 and a turbine stator 2, the turbine stator 2 is sleeved on the turbine rotor 1, two ends of the turbine stator 2 are respectively connected with an external steam inlet casing 3 and an external steam outlet casing 4,
the turbine rotor 1 comprises a turbine front shaft 1-1, a turbine rear shaft 1-2, six rotor wheel discs 1-3 and 2N long pull rod bolts 1-4, wherein N is a positive integer greater than or equal to 4,
the outer diameters of the six rotor disks 1-3 are the same, N first cooling air flow holes 1-3-1 are uniformly distributed on the end face of each rotor disk 1-3 along the circumferential direction, two first bolt holes 1-3-2 are uniformly distributed between two adjacent first cooling air flow holes 1-3-1, one end of a turbine front shaft 1-1 is provided with a front shaft end flange 1-1, one end of a turbine rear shaft 1-2 is provided with a rear shaft end flange 1-2-1,2N long pull rod bolts 1-4 respectively sequentially penetrate through the first bolt holes 1-3-2 of the six rotor disks 1-3, one end of each long pull rod bolt 1-4 is in bolt connection with the front shaft end flange 1-1-1 of the coaxially arranged turbine front shaft 1-1, and the other end of each long pull rod bolt 1-4 is in bolt connection with the rear shaft end flange 1-2-1 of the coaxially arranged turbine rear shaft 1-2;
the turbine stator 2 comprises a turbine casing 2-1 and six stator guide vane rings 2-2, the turbine casing 2-1 is of an integral cylindrical structure, the six stator guide vane rings 2-2 are sequentially arranged on the inner circumference of the turbine casing 2-1 from front to back, and the six stator guide vane rings 2-2 and the six rotor wheel discs 1-3 are arranged in a staggered mode.
When the number of the long stay bolts 1-4 is 8, the number of the first cooling air flow holes 1-3-1 on the end face of each rotor disk 1-3 is 4, and the number of the first bolt holes 1-3-2 on the end face of each rotor disk 1-3 is 8;
when the number of the long stay bolts 1-4 is 10, the number of the first cooling air flow holes 1-3-1 on the end face of each rotor disk 1-3 is 5, and the number of the first bolt holes 1-3-2 on the end face of each rotor disk 1-3 is 8;
when the number of the long stay bolts 1-4 is 12, the number of the first cooling air flow holes 1-3-1 on the end face of each rotor disk 1-3 is 6, and the number of the first bolt holes 1-3-2 on the end face of each rotor disk 1-3 is 8;
when the number of the long stay bolts 1-4 is 14, the number of the first cooling air flow holes 1-3-1 on the end face of each rotor disk 1-3 is 7, and the number of the first bolt holes 1-3-2 on the end face of each rotor disk 1-3 is 8.
The second embodiment is as follows: the turbine rotor 1 of the present embodiment further includes six step tooth seal rings 1-5, one step tooth seal ring 1-5 is provided between two adjacent rotor disks 1-3 of the six rotor disks 1-3, one step tooth seal ring 1-5 is provided between the turbine front shaft 1-1 and the rotor disk 1-3 adjacent thereto, the six step tooth seal rings 1-5 are in one-to-one correspondence with the six stator vane rings 2-2, the six stator vane rings 2-2 are in sealing engagement with the step teeth 1-5-3 of the step tooth seal ring 1-5,
the outer diameters of the six step tooth sealing rings 1-5 are the same, N second cooling air flow holes 1-5-1 are uniformly distributed on the end surface of each step tooth sealing ring 1-5 along the circumferential direction, N second cooling air flow holes 1-5-1 on each step tooth sealing ring 1-5 are in one-to-one correspondence with N first cooling air flow holes 1-3-1 on each rotor wheel disc 1-3,
two second bolt holes 1-5-2 are uniformly distributed between two adjacent second cooling air flow holes 1-5-1, 2N second bolt holes 1-5-2 on each step tooth sealing ring 1-5 are in one-to-one correspondence with 2N first bolt holes 1-3-2 on each rotor wheel disc 1-3, and six step tooth sealing rings 1-5 are connected with the rotor wheel discs 1-3 through long pull rod bolts 1-4. The six step tooth sealing rings 1-5 are in sealing fit with the six stator guide vane rings 2-2, and the step tooth sealing rings 1-5 comprise honeycomb sealing rings and have good sealing effects. The second cooling air flow holes 1-5-1 are in one-to-one correspondence with the first cooling air flow holes 1-3-1 on the rotor wheel disc 1-3, the second cooling air flow holes 1-5-1 on the end faces of the six step tooth sealing rings 1-5 play a role in balancing air pressure, the air pressure between each step tooth sealing ring 1-5 and the rotor wheel disc 1-3 is effectively balanced, the strength safety margin of the long pull rod bolts 1-4 is effectively protected, and air in the combined turbine rotor 1 sealing cavity can be discharged, so that the air pressure in the turbine rotor 1 is equal to the air pressure outside the turbine rotor 1. Other compositions and connection relationships are the same as those of the first embodiment.
And a third specific embodiment: referring to fig. 3 and 5, the turbine rotor 1 of the present embodiment further includes six rotor blade units, each rotor blade unit includes a plurality of rotor blades 1-6, each rotor blade root is provided with a tooth, a plurality of grooves 1-3-3 matching with the tooth are circumferentially distributed on the outer circumference of each rotor disk 1-3, and the rotor blades are connected with the rotor disks 1-3 through the teeth and grooves 1-3 matching with each other. Other compositions and connection relationships are the same as those of the first or second embodiment.
The specific embodiment IV is as follows: the turbine stator 2 of the present embodiment further includes six guard rings 2-3, one guard ring 2-3 is disposed between two adjacent stator vane rings 2-2 of the six stator vane rings 2-2, one guard ring 2-3 is disposed between the outer casing 4 and the stator vane ring 2-2 adjacent thereto, the six guard rings 2-3 are sequentially mounted on the inner cylindrical surface of the turbine casing 2-1, the six guard rings 2-3 are in one-to-one correspondence with the six moving vane units, and the guard rings 2-3 are in sealing fit with the blade teeth 1-6-1 at the ends of the moving vanes 1-6 of the moving vane units. The six guard rings 2-3 are in sealing fit with the blade teeth 1-6-1 of the moving blades 1-6 of the six moving blade units, so that a good sealing effect is achieved. Other compositions and connection relationships are the same as those of the first, second or third embodiments.
Fifth embodiment: referring to fig. 4, six annular vane grooves 2-1-1 are uniformly formed in the inner circumference of the turbine casing 2-1 of the present embodiment, an annular vane boss 2-2-1 matched with the annular vane groove 2-1-1 is formed at the root of each stator vane ring 2-2, and the six stator vane rings 2-2 are connected with the turbine casing 2-1 through the annular vane grooves 2-1-1 and the annular vane bosses 2-2-1 matched with each other. By the arrangement, the connection strength between the stator vane ring 2-2 and the turbine casing 2-1 is effectively ensured. Other compositions and connection relationships are the same as those of the first, second, third or fourth embodiments.
Specific embodiment six: referring to fig. 4, in the present embodiment, an annular shroud ring groove 2-1-2 is provided between two adjacent annular vane grooves 2-1-1 on the inner circumference of a turbine casing 2-1, an annular shroud ring groove 2-1-2 is provided between an external inlet casing 3 and the adjacent annular vane groove 2-1-1, an annular shroud ring boss 2-3-1 is provided at the root of each shroud ring 2-3, which is matched with the annular shroud ring groove 2-1-2, and six shroud rings 2-3 are connected with the turbine casing 2-1 through the annular shroud ring groove 2-1-2 and the annular shroud ring boss 2-3-1, which are mutually matched. By the arrangement, the connection strength between the shroud ring 2-3 and the turbine casing 2-1 is effectively ensured. Other compositions and connection relationships are the same as those of the first, second, third, fourth or fifth embodiments.
Seventh embodiment: referring to fig. 2 and 4, the turbine casing 2-1 of the present embodiment includes an inner casing 2-a and an outer casing 2-B, the inner diameters of the inner casing 2-a and the outer casing 2-B are equal, an inner casing connecting flange 2-a-1 is provided at one end of the inner casing 2-a, a first outer casing connecting flange 2-B-1 is provided at one end of the outer casing 2-B, and one end of the inner casing 2-a is bolted to one end of the outer casing 2-B through the inner casing connecting flange 2-a-1 and the first outer casing connecting flange 2-B-1 that are mutually matched. The arrangement adopts a flange connection mode, so that the disassembly and assembly between the inner casing 2-A and the outer casing 2-B are convenient. Other compositions and connection relationships are the same as those of the first, second, third, fourth, fifth or sixth embodiments.
Eighth embodiment: the present embodiment will be described with reference to fig. 1 and 4, in which the other end of the inner casing 2-a is fitted into the inside of the outer intake casing 3, and the outer cylindrical surface of the inner casing 2-a is clearance-fitted with the inner cylindrical surface of the outer intake casing 3. The arrangement is that the turbine casing 2-1 adopts an embedded structural design, one end of the inner casing 2-A is connected with the outer casing 2-B which is coaxially arranged, the other end of the inner casing 2-A is embedded into the outer admission casing 3, the whole length of the six-stage helium gas compressor turbine is effectively shortened, and the use space is saved. Other compositions and connection relationships are the same as those of the first, second, third, fourth, fifth, sixth or seventh embodiments.
Detailed description nine: the present embodiment will be described with reference to fig. 2 and 4, in which the other end of the outer casing 2-B of the present embodiment is provided with a second outer casing connecting flange 2-B-2 for connecting with the outer casing 4. The arrangement is convenient for the disassembly and assembly between the outer casing 2-B and the outer steam outlet casing 4 by adopting a flange connection mode. Other compositions and connection relationships are the same as those of the first, second, third, fourth, fifth, sixth, seventh or eighth embodiments.
Claims (9)
1. A helium turbine connecting structure capable of being quickly disassembled and assembled comprises a turbine rotor (1) and a turbine stator (2), wherein the turbine stator (2) is sleeved on the turbine rotor (1), two ends of the turbine stator (2) are respectively connected with an external steam inlet casing (3) and an external steam outlet casing (4),
the method is characterized in that: the turbine rotor (1) comprises a turbine front shaft (1-1), a turbine rear shaft (1-2), six rotor wheel discs (1-3) and 2N long pull rod bolts (1-4), wherein N is a positive integer greater than or equal to 4,
the outer diameters of the six rotor disks (1-3) are the same, N first cooling air flow holes (1-3-1) are uniformly distributed on the end face of each rotor disk (1-3) along the circumferential direction, two first bolt holes (1-3-2) are uniformly distributed between every two adjacent first cooling air flow holes (1-3-1), one end of a turbine front shaft (1-1) is provided with a front shaft end flange (1-1-1), one end of a turbine rear shaft (1-2) is provided with a rear shaft end flange (1-2-1), 2N long pull rod bolts (1-4) sequentially penetrate through the first bolt holes (1-3-2) of the six rotor disks (1-3), one end of each long pull rod bolt (1-4) is in bolt connection with the front shaft end flange (1-1-1) of the coaxially arranged turbine front shaft (1), and the other end of each long pull rod bolt (1-4) is in bolt connection with the rear shaft end flange (1-2-1-1) of the coaxially arranged turbine rear shaft (1-2);
the turbine stator (2) comprises a turbine casing (2-1) and six stator guide vane rings (2-2), the turbine casing (2-1) is of an integral cylindrical structure, the six stator guide vane rings (2-2) are sequentially arranged on the inner circumference of the turbine casing (2-1) from front to back, and the six stator guide vane rings (2-2) and the six rotor wheel discs (1-3) are arranged in a staggered mode;
the turbine rotor (1) further comprises six step tooth sealing rings (1-5), one step tooth sealing ring (1-5) is arranged between two adjacent rotor wheel discs (1-3) in the six rotor wheel discs (1-3), one step tooth sealing ring (1-5) is arranged between the turbine front shaft (1-1) and the rotor wheel disc (1-3) adjacent to the turbine front shaft, the six step tooth sealing rings (1-5) are in one-to-one correspondence with the six stator guide vane rings (2-2), and the six stator guide vane rings (2-2) are in sealing fit with the step teeth (1-5-3) of the step tooth sealing rings (1-5);
the outer diameters of the six step tooth sealing rings (1-5) are the same, N second cooling air flow holes (1-5-1) are uniformly distributed on the end face of each step tooth sealing ring (1-5) along the circumferential direction, and the N second cooling air flow holes (1-5-1) on each step tooth sealing ring (1-5) are in one-to-one correspondence with the N first cooling air flow holes (1-3-1) on each rotor wheel disc (1-3);
the rotor wheel discs (1-3) are of solid round structures, and after the six rotor wheel discs (1-3) are combined, a sealing cavity is formed between the wheel discs; the first cooling air flow holes (1-3-1) and the second cooling air flow holes (1-5-1) balance the gas pressure between the disk surfaces of the rotor disks (1-3) and between the step tooth sealing rings (1-5) and the rotor disks (1-3); and discharging air in the sealing cavity of the combined turbine rotor (1) to make the air pressure in the turbine rotor (1) equal to the air pressure outside the turbine rotor (1).
2. The quick detachable helium turbine connecting structure according to claim 1, wherein: two second bolt holes (1-5-2) are uniformly distributed between two adjacent second cooling air flow holes (1-5-1), 2N second bolt holes (1-5-2) on each step tooth sealing ring (1-5) are in one-to-one correspondence with 2N first bolt holes (1-3-2) on each rotor wheel disc (1-3), and six step tooth sealing rings (1-5) are connected with the rotor wheel discs (1-3) through long pull rod bolts (1-4).
3. A quick detachable helium turbine connection according to claim 1 or 2, wherein: the turbine rotor (1) further comprises six moving blade units, each moving blade unit comprises a plurality of moving blades (1-6), the root of each moving blade is provided with a tenon tooth, a plurality of mortises (1-3-3) matched with the tenon tooth are circumferentially and uniformly distributed on the outer circumference of each rotor wheel disc (1-3), and the moving blades are connected with the rotor wheel discs (1-3) through the tenon teeth and the mortises (1-3-3) matched with each other.
4. A quick detachable helium turbine connection according to claim 3, wherein: the turbine stator (2) further comprises six guard rings (2-3), one guard ring (2-3) is arranged between two adjacent stator guide vane rings (2-2) in the six stator guide vane rings (2-2), one guard ring (2-3) is arranged between the outer steam turbine casing (4) and the stator guide vane ring (2-2) adjacent to the outer steam turbine casing, the six guard rings (2-3) are sequentially arranged on the inner cylindrical surface of the turbine casing (2-1), the six guard rings (2-3) correspond to the six moving blade units one by one, and the guard rings (2-3) are in sealing fit with the blade teeth (1-6-1) at the tail ends of the moving blades (1-6) of the moving blade units.
5. The quick detachable helium turbine connecting structure according to claim 4, wherein: six annular guide vane grooves (2-1-1) are uniformly formed in the inner circumference of the turbine casing (2-1), annular guide vane bosses (2-2-1) matched with the annular guide vane grooves (2-1-1) are arranged at the root of each stator guide vane ring (2-2), and the six stator guide vane rings (2-2) are connected with the turbine casing (2-1) through the annular guide vane grooves (2-1-1) and the annular guide vane bosses (2-2-1) which are matched with each other.
6. A quick detachable helium turbine connection according to claim 3, wherein: an annular ring protection groove (2-1-2) is arranged between two adjacent annular guide vane grooves (2-1-1) on the inner circumference of the turbine casing (2-1), an annular ring protection groove (2-1-2) is arranged between the external steam inlet casing (3) and the adjacent annular guide vane groove (2-1-1), annular ring protection bosses (2-3-1) matched with the annular ring protection groove (2-1-2) are arranged at the root of each ring protection (2-3), and the six rings (2-3) are connected with the turbine casing (2-1) through the annular ring protection grooves (2-1-2) and the annular ring protection bosses (2-3-1) which are matched with each other.
7. The quick detachable helium turbine connecting structure according to claim 6, wherein: the turbine casing (2-1) comprises an inner casing (2-A) and an outer casing (2-B), the inner diameters of the inner casing (2-A) and the outer casing (2-B) are equal, an inner casing connecting flange (2-A-1) is arranged at one end of the inner casing (2-A), a first outer casing connecting flange (2-B-1) is arranged at one end of the outer casing (2-B), and one end of the inner casing (2-A) is connected with one end of the outer casing (2-B) in a bolting mode through the inner casing connecting flange (2-A-1) and the first outer casing connecting flange (2-B-1) which are matched with each other.
8. The quick detachable helium turbine connecting structure according to claim 7, wherein: the other end of the inner casing (2-A) is embedded into the outer casing (3), and the outer cylindrical surface of the inner casing (2-A) is in clearance fit with the inner cylindrical surface of the outer casing (3).
9. The quick detachable helium turbine connecting structure according to claim 8, wherein: the other end of the outer casing (2-B) is provided with a second outer casing connecting flange (2-B-2) which is used for being connected with an outer steam outlet casing (4).
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| CN201811625049.0A CN109404049B (en) | 2018-12-28 | 2018-12-28 | Helium turbine connecting structure capable of being quickly disassembled and assembled |
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| CN201811625049.0A CN109404049B (en) | 2018-12-28 | 2018-12-28 | Helium turbine connecting structure capable of being quickly disassembled and assembled |
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| CN109798153B (en) * | 2019-03-28 | 2023-08-22 | 中国船舶重工集团公司第七0三研究所 | Cooling structure applied to turbine wheel disc of marine gas turbine |
| CN114882784B (en) * | 2022-04-14 | 2023-03-10 | 西北工业大学 | Assembly high-pressure turbine teaching model and method for bearing force by using turbine guider |
Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB656088A (en) * | 1944-06-22 | 1951-08-08 | British Thomson Houston Co Ltd | Improvements in and relating to gas turbine power plant |
| GB723882A (en) * | 1951-09-05 | 1955-02-16 | Vickers Electrical Co Ltd | Improvements in the construction of rotors for steam- and gas-turbines |
| DE2364430A1 (en) * | 1972-12-26 | 1974-06-27 | Gen Electric | GAS TURBINE ENGINE IN MODULAR DESIGN |
| US5503528A (en) * | 1993-12-27 | 1996-04-02 | Solar Turbines Incorporated | Rim seal for turbine wheel |
| CN102359396A (en) * | 2011-07-08 | 2012-02-22 | 西安交通大学 | Disc type rod fastening rotor structure with circumferential tension rod at turbine section for heavy gas turbine |
| CN202972355U (en) * | 2012-12-04 | 2013-06-05 | 洛阳双瑞特种装备有限公司 | Pressure balanced expansion joint for self-load bearing elbow pipe |
| CN103670531A (en) * | 2012-09-07 | 2014-03-26 | 罗伯特·博世有限公司 | Blade wheel for continuous-flow machine and method for producing turbine wheel for continuous-flow machine |
| CN107355271A (en) * | 2017-07-25 | 2017-11-17 | 航天推进技术研究院 | A kind of organic Rankine bottoming cycle multikilowatt TRT |
| CN207212499U (en) * | 2017-08-22 | 2018-04-10 | 程琪 | A kind of gas turbine with hoisting mechanism |
| CN209163875U (en) * | 2018-12-28 | 2019-07-26 | 中国船舶重工集团公司第七0三研究所 | A kind of helium turbine connection structure of fast demountable |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2875535B1 (en) * | 2004-09-21 | 2009-10-30 | Snecma Moteurs Sa | TURBINE MODULE FOR GAS TURBINE ENGINE |
| US9719425B2 (en) * | 2014-05-23 | 2017-08-01 | General Electric Company | Cooling supply circuit for turbomachinery |
-
2018
- 2018-12-28 CN CN201811625049.0A patent/CN109404049B/en active Active
Patent Citations (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB656088A (en) * | 1944-06-22 | 1951-08-08 | British Thomson Houston Co Ltd | Improvements in and relating to gas turbine power plant |
| GB723882A (en) * | 1951-09-05 | 1955-02-16 | Vickers Electrical Co Ltd | Improvements in the construction of rotors for steam- and gas-turbines |
| DE2364430A1 (en) * | 1972-12-26 | 1974-06-27 | Gen Electric | GAS TURBINE ENGINE IN MODULAR DESIGN |
| CA986730A (en) * | 1972-12-26 | 1976-04-06 | General Electric Company | Modular gas turbine engine |
| US5503528A (en) * | 1993-12-27 | 1996-04-02 | Solar Turbines Incorporated | Rim seal for turbine wheel |
| CN102359396A (en) * | 2011-07-08 | 2012-02-22 | 西安交通大学 | Disc type rod fastening rotor structure with circumferential tension rod at turbine section for heavy gas turbine |
| CN103670531A (en) * | 2012-09-07 | 2014-03-26 | 罗伯特·博世有限公司 | Blade wheel for continuous-flow machine and method for producing turbine wheel for continuous-flow machine |
| CN202972355U (en) * | 2012-12-04 | 2013-06-05 | 洛阳双瑞特种装备有限公司 | Pressure balanced expansion joint for self-load bearing elbow pipe |
| CN107355271A (en) * | 2017-07-25 | 2017-11-17 | 航天推进技术研究院 | A kind of organic Rankine bottoming cycle multikilowatt TRT |
| CN207212499U (en) * | 2017-08-22 | 2018-04-10 | 程琪 | A kind of gas turbine with hoisting mechanism |
| CN209163875U (en) * | 2018-12-28 | 2019-07-26 | 中国船舶重工集团公司第七0三研究所 | A kind of helium turbine connection structure of fast demountable |
Non-Patent Citations (4)
| Title |
|---|
| GTCP85-129H涡轮轴承腔压力大故障原因浅析;许兴德;;航空维修与工程;20180120(第01期);第51-53页 * |
| 氦气涡轮转子系统整体数值仿真研究;李琦;郭金佳;;航空发动机(第02期);第31-34页 * |
| 氦气透平压气机组合弹性环密封试验研究;王旭;徐莉华;单世奎;钟阿霞;;热能动力工程(第06期);第807-811、822页 * |
| 陈光.航空燃气涡轮发动机结构设计.北京航空航天大学出版社,1988,(1988年7月第一版),第104-127页. * |
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