CN109505773B - Helium low-pressure compressor integral sealing structure - Google Patents
Helium low-pressure compressor integral sealing structure Download PDFInfo
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- CN109505773B CN109505773B CN201811625067.9A CN201811625067A CN109505773B CN 109505773 B CN109505773 B CN 109505773B CN 201811625067 A CN201811625067 A CN 201811625067A CN 109505773 B CN109505773 B CN 109505773B
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D3/00—Axial-flow pumps
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/05—Shafts or bearings, or assemblies thereof, specially adapted for elastic fluid pumps
- F04D29/056—Bearings
- F04D29/058—Bearings magnetic; electromagnetic
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/08—Sealings
- F04D29/083—Sealings especially adapted for elastic fluid pumps
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/26—Rotors specially for elastic fluids
- F04D29/32—Rotors specially for elastic fluids for axial flow pumps
- F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/40—Casings; Connections of working fluid
- F04D29/52—Casings; Connections of working fluid for axial pumps
- F04D29/522—Casings; Connections of working fluid for axial pumps especially adapted for elastic fluid pumps
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/40—Casings; Connections of working fluid
- F04D29/52—Casings; Connections of working fluid for axial pumps
- F04D29/54—Fluid-guiding means, e.g. diffusers
- F04D29/541—Specially adapted for elastic fluid pumps
- F04D29/542—Bladed diffusers
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Electromagnetism (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
An integral sealing structure of a helium low-pressure compressor relates to the field of helium low-pressure compressors. The invention solves the problems that the prior low-pressure compressor has poor sealing effect, so that the internal air pressure of the low-pressure compressor shell is unstable due to the interference of external air pressure, and the overall effect of the helium turbine compressor set is affected. The low-pressure rotor is arranged in a low-pressure stator, a rotor front shaft is fixed on the front end face of a rotor wheel disc combination, a stator casing is positioned between an air inlet casing and an air outlet casing, a first honeycomb sealing ring is embedded in the rear part of an air inlet inner shell, the air inlet inner shell is in sealing connection with the rotor wheel disc through the first honeycomb sealing ring, a second honeycomb sealing ring is embedded in the front part of an air outlet inner shell, and the air outlet inner shell is in sealing connection with the rotor wheel disc through the second honeycomb sealing ring. The invention is used for improving the overall sealing performance of the helium low-pressure compressor.
Description
Technical Field
The invention relates to the field of helium low-pressure compressors, in particular to an integral sealing structure of a helium low-pressure compressor.
Background
The high-temperature pile helium turbine circulation is characterized in that a helium turbine is combined with a modular high-temperature pile, high-temperature helium generated by the high-temperature pile is utilized to directly push a gas turbine to do work for high-efficiency power generation, and compared with a steam turbine power generation system adopted by the existing high-temperature pile, the helium turbine circulation power generation system is compact in structure and is arranged in a loop pressure boundary; the power generation efficiency is very high, and the commercial high-temperature pile helium turbine cycle power generation efficiency is expected to reach 45% -50% according to the prediction of the prior art.
The energy conversion unit of the overall structure of the helium turbine consists of a high (low) pressure compressor, a turbine, an intercooler, a precooler, a heat regenerator, an inner (outer) cavity shell, a high-temperature helium gas inflow pipe, a footing, a supporting seat, related auxiliary parts and the like.
Helium is a colorless, odorless rare gas having a molecular weight of 4.0026 ×10 -3 kg/mol; boiling point at standard atmospheric pressure-268.94 ℃; melting point-267.96 ℃; a gas constant 2077.25J/kg.K; a critical pressure 0.22695MPa; the critical density was 69.3kg/m3. Helium molecules are monoatomic molecules that are only heavier than hydrogen, 7.25 times lighter than air.
Helium is very close to ideal gas in the range of 0.1 to 10MPa at 0 to 3000 ℃ with specific heat C p And an adiabatic index κ of almost constant, C p = 5.1931kJ/kg·k, κ=1.67. Helium has a higher specific heat (about 5 times that of air) than air or gas, so that the compression ratio of helium is small under the same temperature difference condition, and the mass flow rate of helium is small under the same output power condition.
The molecular weight of helium is less than 1/7 of that of air, and for a compressor, the smaller the molecular weight of a compressed working medium is, the more difficult the gas is to be compressed, and the larger the corresponding compressor through-flow design difference is. At the same dimensionless pressure ratioUnder the conditions, the work necessary to compress 1 kg of helium in the compressor is about 4 times greater than the work necessary to compress 1 kg of nitrogen. Because ofIn this case, the design of the axial compressor with helium device, which is a common stage head for the air compressor, increases the number of stages by almost 4 times.
Because of the physical property parameter specificity of helium gas, the Reynolds number and Mach number of the gas flowing through the gas compressor are lower than those of the common air gas compressor, the helium gas compressor can realize the same type design, and has good aerodynamic performance.
The compressor of the helium turbine compressor unit is of an axial flow type, high-pressure and low-pressure parts and a single-shaft vertical structure. The low pressure compressor is an important component of the helium turbine compressor train. However, the existing low-pressure compressor has the problem that the sealing effect is poor, so that the internal air pressure of the low-pressure compressor shell is disturbed by the external air pressure and is unstable, and the overall effect of the helium turbine compressor unit is affected.
Disclosure of Invention
The invention aims to solve the problem that the internal air pressure of the low-pressure compressor shell is unstable due to the interference of external air pressure and influences the overall effect of a helium turbine compressor set due to poor sealing effect of the existing low-pressure compressor, and further provides an overall sealing structure of the helium low-pressure compressor.
The technical scheme of the invention is as follows:
the utility model provides a helium low pressure compressor integral sealing structure, which comprises a low pressure rotor, a low pressure stator, an air inlet casing and an exhaust casing, wherein the low pressure rotor is arranged in the low pressure stator,
the low-voltage rotor comprises a rotor front shaft and a rotor wheel disc combination, wherein the rotor front shaft is fixed on the front end face of the rotor wheel disc combination, the rotor wheel disc combination comprises four rotor wheel discs and eight moving blades, the outer diameters of the four rotor wheel discs are the same, the four rotor wheel discs are fixedly connected in sequence from front to back, and the eight moving blades are installed on the outer circumference of the rotor wheel disc combination step by step;
the low-pressure stator comprises a stator case and a plurality of stator blade rings, wherein the stator case is positioned between the air inlet case and the air outlet case, one end of the stator case is connected with the air inlet case, the other end of the stator case is connected with the air outlet case, the stator case is of a horizontal semi-cylindrical structure, a T-shaped annular groove for installing the stator blade rings is arranged on the inner cylindrical surface of the stator case, and the stator blade rings are arranged on the T-shaped annular groove of the stator case step by step from front to back;
the air inlet casing is of a full-ring cylindrical structure, the air inlet casing comprises an air inlet inner shell, an air inlet outer shell, a first honeycomb sealing ring, a front radial electromagnetic bearing, a protection bearing, a bearing seat and a plurality of first guide support plates, the air inlet inner shell is coaxially arranged in the air inlet outer shell, a gap is formed between the air inlet inner shell and the air inlet outer shell to form a low-pressure air inlet channel, the plurality of first guide support plates are arranged in the low-pressure air inlet channel between the air inlet inner shell and the air inlet outer shell, one ends of the plurality of first guide support plates are fixedly connected with the air inlet inner shell, the other ends of the plurality of first guide support plates are fixedly connected with the air inlet outer shell, the rear part of the air inlet inner shell is embedded with the first honeycomb sealing ring, the air inlet inner shell is in sealing connection with a rotor wheel disc through the first honeycomb sealing ring, a shell flange support is arranged on the inner wall of the air inlet inner shell, the front radial electromagnetic bearing and the protection bearing are arranged between the rotor front shaft and the air inlet inner shell, the front radial electromagnetic bearing and the protection bearing are connected with the shell flange support of the air inlet inner shell through the bearing seat,
the exhaust casing is of a whole-ring cylindrical structure, the exhaust casing comprises an exhaust inner shell, an exhaust outer shell, a second honeycomb sealing ring and a plurality of second guide support plates, the exhaust inner shell is coaxially arranged in the exhaust outer shell, a gap is formed between the exhaust inner shell and the exhaust outer shell to form a low-pressure exhaust runner, the plurality of second guide support plates are arranged in the low-pressure exhaust runner between the exhaust inner shell and the exhaust outer shell, one ends of the plurality of second guide support plates are fixedly connected with the exhaust inner shell, the other ends of the plurality of second guide support plates are fixedly connected with the exhaust outer shell, the second honeycomb sealing ring is embedded in the front of the exhaust inner shell, and the exhaust inner shell is in sealing connection with the rotor wheel disc through the second honeycomb sealing ring.
Further, the four rotor disks are the first-stage disk, the second-stage disk, the third-stage disk and the fourth-stage disk from front to back in sequence, two dovetail mortises are circumferentially formed in the outer circumference of the first-stage disk, two dovetail mortises are circumferentially formed in the outer circumference of the second-stage disk, three dovetail mortises are circumferentially formed in the outer circumference of the third-stage disk, one dovetail mortises are circumferentially formed in the outer circumference of the fourth-stage disk, dovetail tenons are machined at the root of each moving blade, and eight moving blades are connected with the first-stage disk, the second-stage disk, the third-stage disk and the fourth-stage disk which correspond to the first-stage disk, the second-stage disk and the fourth-stage disk step by step through the dovetail tenons and the dovetail mortises which are mutually matched.
Further, a first air seal tooth is processed on the front end face of the first-stage wheel disc and is in sealing connection with a first honeycomb sealing ring at the rear part of the air inlet inner shell.
Further, a second air seal tooth is processed on the rear end face of the fourth-stage wheel disc, and the second air seal tooth is in sealing connection with a second honeycomb sealing ring at the front part of the exhaust inner shell.
Further, both ends of the stator casing are provided with stator casing connecting flanges, one end of the air inlet outer casing is provided with an air inlet casing connecting flange, one end of the stator casing is bolted with the air inlet outer casing through the mutually matched stator casing connecting flanges and the air inlet casing connecting flanges, both ends of the air outlet outer casing are provided with air outlet casing connecting flanges, the other end of the stator casing is bolted with one end of the air outlet outer casing through the mutually matched stator casing connecting flanges and the air outlet casing connecting flanges, and the other end of the air outlet outer casing is connected with an external transition casing through the air outlet casing connecting flanges.
Further, the front end face center of the first-stage wheel disc is provided with a wheel disc connecting flange, one end of the rotor front shaft is provided with a rotor front shaft connecting flange, and the first-stage wheel disc is bolted with the rotor front shaft through the wheel disc connecting flange and the rotor front shaft connecting flange which are matched with each other.
Further, the center of the rear end face of the fourth-stage wheel disc is provided with an overhanging journal flange.
Further, the inner diameter of the air inlet outer shell gradually decreases from front to back, and the low-pressure air inlet channel between the air inlet inner shell and the air inlet outer shell is a convergent channel.
Further, the two adjacent rotor wheel discs are connected in an electron beam welding mode to form a non-detachable structure, and gaps are sealed between the rotor wheel discs.
Further, it also comprises a piston ring type sealing ring, the outer circumference of the air inlet outer shell is provided with a sealing ring mounting groove, and the piston ring type sealing ring is mounted in the sealing ring mounting groove of the outer shell.
Compared with the prior art, the invention has the following effects:
1. the whole sealing structure of the helium low-pressure compressor has a good sealing effect. The rotor wheel disc combination is a disc drum type structure formed by sequentially fixedly connecting four rotor wheel discs from front to back. The first-stage wheel disc of the rotor wheel disc combination is in sealing connection with the air inlet inner shell of the air inlet casing through a first air seal tooth and a first honeycomb seal ring which are matched with each other to form labyrinth seal. The fourth-stage wheel disc of the rotor wheel disc combination is in sealing connection with the exhaust inner shell of the exhaust casing through the second air seal teeth and the second honeycomb seal ring which are matched with each other to form labyrinth seal. And the sealing between the two ends of the low-pressure rotor and the air inlet casing and the air outlet casing is ensured. The front shaft of the rotor and the front radial electromagnetic bearing form clearance fit, so that the rotor has a good sealing effect. The piston ring type sealing ring is arranged on the air inlet outer shell and forms a sealing structure with the outer cylinder of the external unit to prevent air leakage.
Drawings
FIG. 1 is a schematic view of the overall seal structure of the helium low pressure compressor of the present invention;
FIG. 2 is a schematic view of the structure of the low pressure rotor of the present invention;
fig. 3 is an assembly view of the low-pressure stator, the intake casing, and the exhaust casing of the present invention.
Detailed Description
The first embodiment is as follows: the helium low-pressure compressor integral sealing structure of the present embodiment is described with reference to fig. 1 to 3, and includes a low-pressure rotor 1, a low-pressure stator 2, an intake casing 3, and an exhaust casing 4, the low-pressure rotor 1 being disposed inside the low-pressure stator 2,
the low-voltage rotor 1 comprises a rotor front shaft 1-1 and a rotor wheel disc combination 1-2, wherein the rotor front shaft 1-1 is fixed on the front end face of the rotor wheel disc combination 1-2, the rotor wheel disc combination 1-2 comprises four rotor wheel discs and eight moving blades 1-2-1, the outer diameters of the four rotor wheel discs are the same, the four rotor wheel discs are fixedly connected in sequence from front to back, and the eight moving blades 1-2-1 are installed on the outer circumference of the rotor wheel disc combination 1-2 step by step;
the low-pressure stator 2 comprises a stator case 2-1 and a plurality of stator blade rings 2-2, wherein the stator case 2-1 is positioned between an air inlet case 3 and an air outlet case 4, one end of the stator case 2-1 is connected with the air inlet case 3, the other end of the stator case 2-1 is connected with the air outlet case 4, the stator case 2-1 is of a horizontal semi-cylindrical structure, a T-shaped annular groove 2-1-1 for installing the stator blade rings 2-2 is arranged on the inner cylindrical surface of the stator case 2-1, and the stator blade rings 2-2 are installed on the T-shaped annular groove 2-1-1 of the stator case 2-1 step by step from front to back;
the air inlet casing 3 is of a full-ring cylindrical structure, the air inlet casing 3 comprises an air inlet inner shell 3-1, an air inlet outer shell 3-2, a first honeycomb seal ring 3-3, a front radial electromagnetic bearing 3-4, a protection bearing 3-5, a bearing seat 3-6 and a plurality of first guide support plates, the air inlet inner shell 3-1 is coaxially arranged inside the air inlet outer shell 3-2, a gap is arranged between the air inlet inner shell 3-1 and the air inlet outer shell 3-2 to form a low-pressure air inlet channel 3-7, a plurality of first guide support plates are arranged in the low-pressure air inlet channel 3-7 between the air inlet inner shell 3-1 and the air inlet outer shell 3-2, one ends of the first guide support plates are fixedly connected with the air inlet inner shell 3-1, the other ends of the first guide support plates are fixedly connected with the air inlet outer shell 3-2, the first honeycomb seal ring 3-3 is embedded at the rear part of the air inlet inner shell 3-1, the air inlet inner shell 3-1 is connected with a rotor disc 3-3 through the first honeycomb seal ring 3-3, the radial bearing 3-1 is connected with the front bearing 3-1 and the front bearing 3-1 through the front radial electromagnetic bearing 3-4, the front bearing 1-1 is arranged on the radial bearing 1-1 and the front bearing 1-1 is connected with the front flange 1 and the front bearing 3-1 through the front radial electromagnetic bearing 3-4,
the exhaust casing 4 is of a full-ring cylindrical structure, the exhaust casing 4 comprises an exhaust inner shell 4-1, an exhaust outer shell 4-2, a second honeycomb sealing ring 4-3 and a plurality of second guide support plates, the exhaust inner shell 4-1 is coaxially arranged in the exhaust outer shell 4-2, a gap is formed between the exhaust inner shell 4-1 and the exhaust outer shell 4-2 to form a low-pressure exhaust runner 4-4, the plurality of second guide support plates are arranged in the low-pressure exhaust runner 4-4 between the exhaust inner shell 4-1 and the exhaust outer shell 4-2, one ends of the plurality of second guide support plates are fixedly connected with the exhaust inner shell 4-1, the other ends of the plurality of second guide support plates are fixedly connected with the exhaust outer shell 4-2, and the second honeycomb sealing ring 4-3 is embedded in the front part of the exhaust inner shell 4-1 and is in sealed connection with the rotor wheel disc through the second honeycomb sealing ring 4-3.
The low-pressure rotor 1 is of a drum-type structure, and a rotor front shaft 1-1 is connected with a rotor wheel disc and forms clearance fit with a front radial electromagnetic bearing 3-4.
In order to ensure the running stability of the unit, the low-pressure rotor 1 needs to be subjected to dynamic balance for many times during processing and assembly, and the dynamic balance of the low-pressure rotor 1 adopts a method for installing a balancing weight to eliminate unbalance.
The air inlet inner casing 3-1 and the air inlet outer casing 3-2 are welded to each other by a first deflector support plate. The six first flow guide support plates are used for connecting the air inlet inner shell 3-1 and the air inlet outer shell 3-2, supporting and transmitting torque, the first flow guide support plates are internally provided with hollow structures, and the first flow guide support plates are internally provided with total pressure measuring holes and static pressure measuring holes and are used for arranging measurement transmission pipelines, outgoing lines of pressure sensors, power lines of electromagnetic bearings and control signal lines.
The rear part of the air inlet inner shell 3-1 is embedded with a first honeycomb sealing ring 3-3, and a first air sealing tooth 1-2-2-1 on the front end surface of the first-stage wheel disc 1-2-2 forms a sealing assembly.
The stator case 2-1 is of a horizontal half-structure, and is convenient to assemble and disassemble. Each stator blade ring 2-2 comprises a stator blade outer ring, a stator blade inner ring and stator blades, and the stator blade rings 2-2 are connected with the stator blade outer ring and the stator blade inner ring in an argon arc welding mode.
Considering the assembly problem of the helium low-pressure compressor, the exhaust casing 4 is of a full-ring structure, and the low-pressure exhaust runner 4-4 between the exhaust inner casing 4-1 and the exhaust outer casing 4-2 is formed by welding a second guide support plate.
The second embodiment is as follows: in the present embodiment, the four rotor disks are, from front to back, a first stage disk 1-2-2, a second stage disk 1-2-3, a third stage disk 1-2-4 and a fourth stage disk 1-2-5, two dovetail mortises 1-2-6 are circumferentially formed on the outer circumference of the first stage disk 1-2-2, two dovetail mortises 1-2-6 are circumferentially formed on the outer circumference of the second stage disk 1-2-3, three dovetail mortises 1-2-6 are circumferentially formed on the outer circumference of the third stage disk 1-2-4, one dovetail mortises 1-2-6 is circumferentially formed on the outer circumference of the fourth stage disk 1-2-5, dovetail tenons are machined at the root of each rotor blade 1-2-1, and eight rotor blades 1-2-1 are connected with the corresponding first stage disk 1-2-2, second stage 1-3 and fourth stage disk 1-2-5 step by step through mutually matched dovetail mortises 1-2-6. By the arrangement, the rotor blades 1-2-1 of each stage are small in size, but large in number, and a circumferential dovetail-shaped tongue-and-groove structure is adopted in design. Considering the convenience of processing and manufacturing, all stages of moving blades 1-2-1 adopt dovetail tenons with the same size, and all stages of wheel disc mortises are identical. Other compositions and connection relationships are the same as those of the first embodiment.
And a third specific embodiment: referring to fig. 1 and 2, a first air seal tooth 1-2-2-1 is formed on the front end surface of a first-stage wheel disc 1-2-2 of the present embodiment, and the first air seal tooth 1-2-2-1 is in sealing connection with a first honeycomb seal ring 3-3 at the rear part of an air inlet inner casing 3-1. The first-stage wheel disc 1-2-2 is in sealing connection with the air inlet inner shell 3-1 of the air inlet casing 3 through the first air seal teeth 1-2-2-1 and the first honeycomb seal ring 3-3 which are matched with each other to form labyrinth seal. Other compositions and connection relationships are the same as those of the first or second embodiment.
The specific embodiment IV is as follows: in the present embodiment, referring to fig. 1 and 2, a second air seal tooth 1-2-5-1 is formed on the rear end surface of the fourth-stage wheel disc 1-2-5, and the second air seal tooth 1-2-5-1 is in sealing connection with a second honeycomb seal ring 4-3 in front of the exhaust inner casing 4-1. The fourth-stage wheel disc 1-2-5 is in sealing connection with the exhaust inner shell 4-1 of the exhaust casing 4 through the second air seal teeth 1-2-5-1 and the second honeycomb sealing ring 4-3 which are matched with each other to form a labyrinth seal. Other compositions and connection relationships are the same as those of the first, second or third embodiments.
Fifth embodiment: referring to fig. 3, in the present embodiment, a stator case connecting flange 2-1-2 is provided at both ends of a stator case 2-1, an intake case connecting flange 3-2-1 is provided at one end of an intake outer case 3-2, one end of the stator case 2-1 is bolted to the intake outer case 3-2 via the mutually-fitted stator case connecting flange 2-1-2 and intake case connecting flange 3-2-1, an exhaust case connecting flange 4-2-1 is provided at both ends of an exhaust outer case 4-2, the other end of the stator case 2-1 is bolted to one end of the exhaust outer case 4-2 via the mutually-fitted stator case connecting flange 2-1-2 and exhaust case connecting flange 4-2-1, and the other end of the exhaust outer case 4-2 is connected to an external transition case via the exhaust case connecting flange 4-2-1. So set up, the dismantlement and the maintenance of the equipment of being convenient for. Other compositions and connection relationships are the same as those of the first, second, third or fourth embodiments.
Specific embodiment six: referring to fig. 2, in the present embodiment, a disk connection flange 1-2-2-2 is provided at the center of the front end surface of a first-stage disk 1-2-2, a rotor front shaft connection flange 1-1-1 is provided at one end of a rotor front shaft 1-1, and the first-stage disk 1-2-2 is bolted to the rotor front shaft 1-1 via the disk connection flange 1-2-2-2 and the rotor front shaft connection flange 1-1-1 which are mutually matched. So set up, the dismantlement and the maintenance of the equipment of being convenient for. Other compositions and connection relationships are the same as those of the first, second, third, fourth or fifth embodiments.
Seventh embodiment: the present embodiment will be described with reference to fig. 2, in which the center of the rear end face of the fourth-stage wheel disc 1-2-5 is provided with an overhanging journal flange 1-2-5-2. So arranged, the fourth stage disk 1-2-5 is connected to the high pressure rotor connecting shaft by an overhanging journal flange 1-2-5-2. Other compositions and connection relationships are the same as those of the first, second, third, fourth, fifth or sixth embodiments.
Eighth embodiment: in the present embodiment, the inner diameter of the intake outer casing 3-2 is gradually reduced from front to rear, and the low-pressure intake passage 3-7 between the intake inner casing 3-1 and the intake outer casing 3-2 is a convergent passage, as described with reference to fig. 1 and 3. So configured, the converging channel acts to accelerate the fluid. Other compositions and connection relationships are the same as those of the first, second, third, fourth, fifth, sixth or seventh embodiments.
Detailed description nine: in the present embodiment, a non-detachable structure is formed by connecting two adjacent rotor disks by electron beam welding, and a gap is sealed between the rotor disks, as described with reference to fig. 1 and 2. This arrangement provides the rotor disc assembly 1-2 with a high stiffness at a low weight. Other compositions and connection relationships are the same as those of the first, second, third, fourth, fifth, sixth, seventh or eighth embodiments.
Detailed description ten: the present embodiment will be described with reference to fig. 3, which further includes a packing ring type packing ring, wherein a packing ring installation groove 3-2-2 is provided on the outer circumference of the intake outer casing 3-2, and the packing ring type packing ring is installed in the packing ring installation groove 3-2-2 of the outer casing. The piston ring type sealing ring is arranged on the air inlet outer shell 3-2, and forms a sealing structure with the outer cylinder of the external unit to prevent air leakage. Other compositions and connection relationships are the same as those of the first, second, third, fourth, fifth, sixth, seventh, eighth or ninth embodiments.
Claims (7)
1. The utility model provides a helium low pressure compressor overall seal structure, it includes low pressure rotor (1), low pressure stator (2), air inlet casing (3) and exhaust casing (4), and low pressure rotor (1) set up in the inside of low pressure stator (2), its characterized in that:
the low-pressure rotor (1) comprises a rotor front shaft (1-1) and a rotor wheel disc combination (1-2), wherein the rotor front shaft (1-1) is fixed on the front end face of the rotor wheel disc combination (1-2), the rotor wheel disc combination (1-2) comprises four rotor wheel discs and eight moving blades (1-2-1), the outer diameters of the four rotor wheel discs are the same, the four rotor wheel discs are fixedly connected in sequence from front to back, and the eight moving blades (1-2-1) are installed on the outer circumference of the rotor wheel disc combination (1-2) step by step;
the low-pressure stator (2) comprises a stator casing (2-1) and a plurality of stator blade rings (2-2), wherein the stator casing (2-1) is positioned between the air inlet casing (3) and the air outlet casing (4), one end of the stator casing (2-1) is connected with the air inlet casing (3), the other end of the stator casing (2-1) is connected with the air outlet casing (4), the stator casing (2-1) is of a horizontal semi-cylindrical structure, a T-shaped annular groove (2-1-1) for installing the stator blade rings (2-2) is arranged on the inner cylindrical surface of the stator casing (2-1), and the plurality of stator blade rings (2-2) are arranged on the T-shaped annular groove (2-1-1) of the stator casing (2-1) step by step from front to back;
the air inlet casing (3) is of a full-ring cylindrical structure, the air inlet casing (3) comprises an air inlet inner shell (3-1), an air inlet outer shell (3-2), a first honeycomb sealing ring (3-3), a front radial electromagnetic bearing (3-4), a protection bearing (3-5), a bearing seat (3-6) and a plurality of first flow guide support plates, the air inlet inner shell (3-1) is coaxially arranged in the air inlet outer shell (3-2), a gap is formed between the air inlet inner shell (3-1) and the air inlet outer shell (3-2) to form a low-pressure air inlet channel (3-7), the plurality of first flow guide support plates are arranged in the low-pressure air inlet channel (3-7) between the air inlet inner shell (3-1) and the air inlet outer shell (3-2), one end of each first flow guide support plate is fixedly connected with the air inlet inner shell (3-1), the other end of each first flow guide support plate is fixedly connected with the air inlet outer shell (3-2), the rear part of the air inlet inner shell (3-1) is embedded with the first honeycomb sealing ring (3-1), the air inlet inner shell (3-1) is connected with the inner wall (3-1) of the air inlet casing through the first honeycomb sealing ring (3-1), a front radial electromagnetic bearing (3-4) and a protective bearing (3-5) are arranged between the front rotor shaft (1-1) and the air inlet inner shell (3-1), the front rotor shaft (1-1) is connected with a rotor wheel disc and forms clearance fit with the front radial electromagnetic bearing (3-4), and the front radial electromagnetic bearing (3-4) and the protective bearing (3-5) are connected with a shell flange support (3-1-1) of the air inlet inner shell (3-1) through a bearing seat (3-6);
the exhaust casing (4) is of a full-ring cylindrical structure, the exhaust casing (4) comprises an exhaust inner shell (4-1), an exhaust outer shell (4-2), a second honeycomb sealing ring (4-3) and a plurality of second flow guide support plates, the exhaust inner shell (4-1) is coaxially arranged in the exhaust outer shell (4-2), a gap is formed between the exhaust inner shell (4-1) and the exhaust outer shell (4-2) to form a low-pressure exhaust runner (4-4), the plurality of second flow guide support plates are arranged in the low-pressure exhaust runner (4-4) between the exhaust inner shell (4-1) and the exhaust outer shell (4-2), one ends of the plurality of second flow guide support plates are fixedly connected with the exhaust inner shell (4-1), the other ends of the plurality of second flow guide support plates are fixedly connected with the exhaust outer shell (4-2), the second honeycomb sealing ring (4-3) is embedded in the front part of the exhaust inner shell (4-1), and the exhaust inner shell (4-1) is in sealing connection with the rotor disc through the second honeycomb sealing ring (4-3);
the four rotor wheel discs sequentially comprise a first-stage wheel disc (1-2-2), a second-stage wheel disc (1-2-3), a third-stage wheel disc (1-2-4) and a fourth-stage wheel disc (1-2-5) from front to back, wherein two dovetail mortises (1-2-6) are formed in the outer circumference of the first-stage wheel disc (1-2-2) along the circumferential direction, two dovetail mortises (1-2-6) are formed in the outer circumference of the second-stage wheel disc (1-2-3) along the circumferential direction, three dovetail mortises (1-2-6) are formed in the outer circumference of the third-stage wheel disc (1-2-4), one dovetail mortises (1-2-6) are formed in the outer circumference of the fourth-stage wheel disc (1-2-5) along the circumferential direction, and the root of each moving blade (1-2-1) is provided with a dovetail head, and eight moving blades (1-2-1) are connected with the first-2-1) and the fourth-stage wheel disc (1-2-4) in a step-by step mode through the dovetail mortises and the dovetail mortises (1-2-6) which are matched with each other;
the front end face of the first-stage wheel disc (1-2-2) is provided with first air seal teeth (1-2-2-1), and the first air seal teeth (1-2-2-1) are in sealing connection with a first honeycomb sealing ring (3-3) at the rear part of the air inlet inner shell (3-1);
the rear end face of the fourth-stage wheel disc (1-2-5) is provided with a second air seal tooth (1-2-5-1), and the second air seal tooth (1-2-5-1) is in sealing connection with a second honeycomb sealing ring (4-3) at the front part of the exhaust inner shell (4-1).
2. The helium low pressure compressor integral seal of claim 1, wherein: the two ends of the stator casing (2-1) are provided with stator casing connecting flanges (2-1-2), one end of the air inlet casing (3-2) is provided with an air inlet casing connecting flange (3-2-1), one end of the stator casing (2-1) is in bolt connection with the air inlet casing (3-2) through the mutually matched stator casing connecting flanges (2-1-2) and the air inlet casing connecting flange (3-2-1), two ends of the air outlet casing (4-2) are provided with air outlet casing connecting flanges (4-2-1), and the other end of the stator casing (2-1) is in bolt connection with one end of the air outlet casing (4-2) through the mutually matched stator casing connecting flanges (2-1-2) and the air outlet casing connecting flanges (4-2-1), and the other end of the air outlet casing (4-2) is connected with an external transition casing through the air outlet casing connecting flanges (4-2-1).
3. The helium low pressure compressor integral seal of claim 1, wherein: the center of the front end face of the first-stage wheel disc (1-2-2) is provided with a wheel disc connecting flange (1-2-2), one end of the rotor front shaft (1-1) is provided with a rotor front shaft connecting flange (1-1-1), and the first-stage wheel disc (1-2-2) is bolted with the rotor front shaft (1-1) through the wheel disc connecting flange (1-2-2-2) and the rotor front shaft connecting flange (1-1-1) which are matched with each other.
4. The helium low pressure compressor integral seal of claim 1, wherein: the center of the rear end face of the fourth-stage wheel disc (1-2-5) is provided with an overhanging journal flange (1-2-5-2).
5. The helium low pressure compressor integral seal of claim 4, wherein: the inner diameter of the air inlet outer shell (3-2) gradually decreases from front to back, and a low-pressure air inlet channel (3-7) between the air inlet inner shell (3-1) and the air inlet outer shell (3-2) is a convergent channel.
6. The helium low pressure compressor integral seal of claim 5, wherein: the two adjacent rotor wheel discs are connected in an electron beam welding mode to form a non-detachable structure, and gaps between the rotor wheel discs are sealed.
7. The helium low pressure compressor integral seal of claim 6, wherein: the air intake device further comprises a piston ring type sealing ring, wherein a sealing ring mounting groove (3-2-2) is formed in the outer circumference of the air intake outer shell (3-2), and the piston ring type sealing ring is mounted in the sealing ring mounting groove (3-2-2) of the outer shell.
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| CN114087210B (en) * | 2021-11-26 | 2023-12-19 | 江苏飞跃机泵集团有限公司 | Molten salt pump complete device with pressure design in tank |
| CN115319456B (en) * | 2022-07-06 | 2023-12-05 | 中国船舶重工集团公司第七0三研究所 | Assembling method for cylindrical gas turbine compressor casing |
Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3383033A (en) * | 1966-04-27 | 1968-05-14 | Gen Electric | Sealing means for axial flow compressor discharge |
| CN102207093A (en) * | 2010-03-29 | 2011-10-05 | 株式会社日立制作所 | Compressor |
| CN203548348U (en) * | 2013-09-27 | 2014-04-16 | 沈阳黎明航空发动机(集团)有限责任公司 | Low-pressure compressor structure for aircraft-derived gas turbine |
| CN105484871A (en) * | 2015-11-23 | 2016-04-13 | 沈阳黎明航空发动机(集团)有限责任公司 | Vehicle-mounted gas turbine transformed from obsolete fanjet |
| RU2603217C1 (en) * | 2015-06-10 | 2016-11-27 | Открытое Акционерное Общество "Уфимское Моторостроительное Производственное Объединение" (Оао "Умпо") | First stage disc of turbojet engine low-pressure compressor rotor shaft (versions) |
| CN106321157A (en) * | 2016-11-10 | 2017-01-11 | 中国船舶重工集团公司第七0三研究所 | Mechanical air pressure combined sealing structure |
| RU2614708C1 (en) * | 2016-05-19 | 2017-03-28 | Публичное Акционерное Общество "Уфимское Моторостроительное Производственное Объединение" (Пао "Умпо") | Low-pressure compressor of gas turbine engine of aviation type |
| RU2630919C1 (en) * | 2016-12-14 | 2017-09-14 | Публичное Акционерное Общество "Уфимское Моторостроительное Производственное Объединение" (Пао "Умпо") | Rotor forth stage impeller of high-pressure compressor (hpc) of turbojet engine (versions), hpc rotor impeller disc, hpc rotor impeller blade, hpc rotor impeller blade ring |
| CN107605792A (en) * | 2016-07-11 | 2018-01-19 | 通用电气公司 | The passive clearance control of GTC |
Family Cites Families (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6619030B1 (en) * | 2002-03-01 | 2003-09-16 | General Electric Company | Aircraft engine with inter-turbine engine frame supported counter rotating low pressure turbine rotors |
| US8092158B2 (en) * | 2007-08-16 | 2012-01-10 | Johnson Controls Technology Company | Method of positioning seals in turbomachinery utilizing electromagnetic bearings |
| DE102009055888A1 (en) * | 2009-11-26 | 2011-06-01 | Oerlikon Leybold Vacuum Gmbh | vacuum pump |
-
2018
- 2018-12-28 CN CN201811625067.9A patent/CN109505773B/en active Active
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3383033A (en) * | 1966-04-27 | 1968-05-14 | Gen Electric | Sealing means for axial flow compressor discharge |
| CN102207093A (en) * | 2010-03-29 | 2011-10-05 | 株式会社日立制作所 | Compressor |
| CN203548348U (en) * | 2013-09-27 | 2014-04-16 | 沈阳黎明航空发动机(集团)有限责任公司 | Low-pressure compressor structure for aircraft-derived gas turbine |
| RU2603217C1 (en) * | 2015-06-10 | 2016-11-27 | Открытое Акционерное Общество "Уфимское Моторостроительное Производственное Объединение" (Оао "Умпо") | First stage disc of turbojet engine low-pressure compressor rotor shaft (versions) |
| CN105484871A (en) * | 2015-11-23 | 2016-04-13 | 沈阳黎明航空发动机(集团)有限责任公司 | Vehicle-mounted gas turbine transformed from obsolete fanjet |
| RU2614708C1 (en) * | 2016-05-19 | 2017-03-28 | Публичное Акционерное Общество "Уфимское Моторостроительное Производственное Объединение" (Пао "Умпо") | Low-pressure compressor of gas turbine engine of aviation type |
| CN107605792A (en) * | 2016-07-11 | 2018-01-19 | 通用电气公司 | The passive clearance control of GTC |
| CN106321157A (en) * | 2016-11-10 | 2017-01-11 | 中国船舶重工集团公司第七0三研究所 | Mechanical air pressure combined sealing structure |
| RU2630919C1 (en) * | 2016-12-14 | 2017-09-14 | Публичное Акционерное Общество "Уфимское Моторостроительное Производственное Объединение" (Пао "Умпо") | Rotor forth stage impeller of high-pressure compressor (hpc) of turbojet engine (versions), hpc rotor impeller disc, hpc rotor impeller blade, hpc rotor impeller blade ring |
Non-Patent Citations (1)
| Title |
|---|
| 某型航空发动机转子系统动力学特性的有限元分析;缪辉;中国优秀硕士学位论文全文数据库工程科技Ⅱ辑(第8期);C031-43 * |
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