CN112983853B - High-speed turbine structure applied to large flow and large expansion ratio - Google Patents
High-speed turbine structure applied to large flow and large expansion ratio Download PDFInfo
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- CN112983853B CN112983853B CN202110186414.8A CN202110186414A CN112983853B CN 112983853 B CN112983853 B CN 112983853B CN 202110186414 A CN202110186414 A CN 202110186414A CN 112983853 B CN112983853 B CN 112983853B
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- 230000006835 compression Effects 0.000 claims abstract description 149
- 238000007906 compression Methods 0.000 claims abstract description 149
- 239000012530 fluid Substances 0.000 claims abstract description 69
- 238000009792 diffusion process Methods 0.000 claims description 9
- 230000003068 static effect Effects 0.000 claims description 6
- 238000005057 refrigeration Methods 0.000 abstract description 3
- 239000007789 gas Substances 0.000 description 52
- 239000000411 inducer Substances 0.000 description 6
- 238000011084 recovery Methods 0.000 description 5
- 238000009434 installation Methods 0.000 description 4
- 238000010586 diagram Methods 0.000 description 2
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 238000000926 separation method Methods 0.000 description 2
- 238000010276 construction Methods 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 238000005461 lubrication Methods 0.000 description 1
- 239000003345 natural gas Substances 0.000 description 1
- 230000009466 transformation Effects 0.000 description 1
- 238000000844 transformation Methods 0.000 description 1
- 239000002918 waste heat Substances 0.000 description 1
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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
- F04D25/00—Pumping installations or systems
- F04D25/02—Units comprising pumps and their driving means
- F04D25/04—Units comprising pumps and their driving means the pump being fluid-driven
- F04D25/045—Units comprising pumps and their driving means the pump being fluid-driven the pump wheel carrying the fluid driving means, e.g. turbine blades
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D15/00—Adaptations of machines or engines for special use; Combinations of engines with devices driven thereby
- F01D15/08—Adaptations for driving, or combinations with, pumps
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D17/00—Radial-flow pumps, e.g. centrifugal pumps; Helico-centrifugal pumps
- F04D17/08—Centrifugal pumps
- F04D17/10—Centrifugal pumps for compressing or evacuating
- F04D17/105—Centrifugal pumps for compressing or evacuating with double suction
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D17/00—Radial-flow pumps, e.g. centrifugal pumps; Helico-centrifugal pumps
- F04D17/08—Centrifugal pumps
- F04D17/10—Centrifugal pumps for compressing or evacuating
- F04D17/12—Multi-stage pumps
- F04D17/122—Multi-stage pumps the individual rotor discs being, one for each stage, on a common shaft and axially spaced, e.g. conventional centrifugal multi- stage 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
- F04D25/00—Pumping installations or systems
- F04D25/16—Combinations of two or more pumps ; Producing two or more separate gas flows
- F04D25/163—Combinations of two or more pumps ; Producing two or more separate gas flows driven by a common gearing arrangement
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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
- F04D29/057—Bearings hydrostatic; hydrodynamic
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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
- F04D29/28—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps
- F04D29/284—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps for compressors
- F04D29/285—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps for compressors the compressor wheel comprising a pair of rotatable bladed hub portions axially aligned and clamped together
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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
- F04D29/28—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps
- F04D29/284—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps for compressors
- F04D29/286—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps for compressors multi-stage rotors
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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
- F04D29/42—Casings; Connections of working fluid for radial or helico-centrifugal pumps
- F04D29/4206—Casings; Connections of working fluid for radial or helico-centrifugal 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
- F04D29/58—Cooling; Heating; Diminishing heat transfer
- F04D29/582—Cooling; Heating; Diminishing heat transfer specially adapted for elastic fluid pumps
- F04D29/584—Cooling; Heating; Diminishing heat transfer specially adapted for elastic fluid pumps cooling or heating the machine
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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
- F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
- F04D29/661—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps
- F04D29/662—Balancing of rotors
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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
- F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
- F04D29/661—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps
- F04D29/666—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps by means of rotor construction or layout, e.g. unequal distribution of blades or vanes
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Thermal Sciences (AREA)
- Fluid Mechanics (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention belongs to the field of fluid machinery and the technical field of refrigeration low temperature, and relates to a high-speed turbine structure applied to large flow and large expansion ratio.A forward compression volute, a backward compression volute, an intermediate shell and an expansion volute are sequentially connected, and a nozzle cover plate is arranged between the intermediate shell and the expansion volute; one end of the main shaft is provided with a pair of compression impellers which are arranged back to back, and the other end is provided with an expansion impeller; a pair of gas radial bearings and a pair of gas thrust bearings for supporting the main shaft are arranged inside the middle shell, a small hole is formed in the middle shell, and a filter is arranged at the inlet of the small hole. According to the invention, the two back-to-back compression impellers are arranged on one side of the main shaft, and different flow rates or pressure ratios are distributed, so that the directions of axial forces generated by the two compression impellers are opposite to the directions of axial forces generated by the expansion impeller at the other end of the main shaft, and even completely offset, and faults caused by unbalance of the axial forces are effectively solved.
Description
Technical Field
The invention belongs to the field of fluid machinery and the technical field of refrigeration and low temperature, and relates to a high-speed turbine structure applied to large flow and large expansion ratio.
Background
The turboexpander is a key part necessary for obtaining cold energy and recovering expansion work of air separation equipment, natural gas liquefaction separation equipment, waste heat recovery equipment and the like. In the turbine expander, the temperature and the pressure of the working medium are reduced while the working medium is subjected to adiabatic expansion, and expansion work is output outwards. The expansion work output by the turboexpander can be consumed by a brake fan which is coaxially arranged, and can also be efficiently recycled by a centrifugal compressor which is coaxially arranged.
In some refrigeration systems or energy recovery systems, the expansion ratio of the expander is higher than the pressure ratio of the centrifugal compressor, and particularly, under the working conditions of large enthalpy drop such as large expansion ratio, the output work of the expander is larger, so that the flow rate of the compression wheel needs to be large to be matched with the output work of the expansion impeller. The centrifugal compression impeller designed by the conventional design method is usually more than 20% larger than the expansion impeller, which easily causes the problems of unbalanced axial force and larger structural size of the whole machine, and in addition, for the centrifugal compression impeller with single large air volume, the efficiency of the compression wheel is very low, which causes most of the output power of the expansion impeller to be wasted.
Disclosure of Invention
Accordingly, the present invention is directed to a high-speed turbine structure with high flow rate and high expansion ratio to overcome the above-mentioned disadvantages of the prior art.
The technical scheme for solving the problems is as follows: a high-speed turbine structure applied to large flow and large expansion ratio is characterized by comprising:
the main shaft, the forward compression volute, the backward compression volute, the middle shell and the expansion volute;
the forward compression volute, the backward compression volute, the middle shell and the expansion volute are sequentially connected, and a nozzle cover plate is arranged between the middle shell and the expansion volute;
the main shaft penetrates through the forward compression volute, the backward compression volute, the middle shell and the expansion volute, one end of the main shaft is provided with a pair of compression impellers which are arranged back to back, and the other end of the main shaft is provided with an expansion impeller;
the pair of back-to-back mounted compression impellers are respectively positioned in the forward compression volute and the backward compression volute, the expansion impellers are positioned in the expansion volute, a pair of gas radial bearings and a pair of gas thrust bearings for supporting the main shaft are arranged in the middle shell, a small hole is formed in the middle shell, and a filter is arranged at the inlet of the small hole. Furthermore, a second fluid inlet is arranged on the middle shell close to the backward compression volute, and a third fluid inlet and a second fluid outlet are arranged on the forward compression volute.
Further, a diffuser is arranged between the forward compression volute and the backward compression volute, a third fluid outlet is arranged on the backward compression volute, and the third fluid outlet is connected with a third fluid inlet of the forward compression volute through a pipeline.
Further, the expansion volute includes a first fluid inlet and a first fluid outlet. After entering from the first fluid inlet, the fluid flows into the nozzle cover plate respectively after passing through the airflow channel of the expansion volute. The flow speed of the fluid in the flow channel of the nozzle is accelerated, and the pressure is reduced. Then, the fluid uniformly flows through the expansion impeller from the outlet of the nozzle, continues to expand in the expansion impeller and applies work to the expansion impeller, so that the expansion impeller is driven to rotate, and the expanded fluid flows out through the first fluid outlet on the expansion volute.
Furthermore, the inner diameter of the first fluid outlet of the expansion volute is gradually increased from inside to outside, and the expansion volute plays a role in diffusion and deceleration of fluid flowing through the first fluid outlet.
Furthermore, a front bearing seat cover plate and a rear bearing seat cover plate are arranged in the middle shell.
Further, the pair of gas journal bearings includes a front journal bearing, a rear journal bearing; the pair of gas thrust bearings comprises a front thrust bearing and a rear thrust bearing;
the front radial bearing and the front thrust bearing are arranged on the front bearing seat cover plate, and the rear radial bearing and the rear thrust bearing are arranged on the rear bearing seat cover plate.
Further, the gas thrust bearing and the gas radial bearing may be dynamic pressure gas bearings or static pressure gas bearings.
Furthermore, the small hole on the middle shell is positioned between the rear bearing seat cover plate and the nozzle cover plate, the front bearing seat cover plate and the rear bearing seat cover plate are respectively provided with a through hole,
gas can pass through the small hole, then is through the through-hole on back bearing cover plate and the preceding bearing cover plate by backward compression impeller inhales, and gas bearing that the gas cooling apron was installed when passing through the bearing cover plate improves the bearing capacity and the stability of bearing.
The invention has the advantages that:
1) when the high-speed turbine machinery provided by the invention works, because the two back-to-back compression impellers are arranged at one side of the main shaft, the axial force directions generated by the two compression impellers are opposite to the axial force direction generated by the expansion impeller at the other end of the main shaft by distributing different flow rates or pressure ratios, and even completely offset, thus the fault caused by the unbalance of the axial force can be effectively solved.
2) Compact structure and high efficiency. The high-speed turbo machine provided by the invention adopts the two back-to-back impellers to recover the expansion work with large air quantity and large expansion ratio, not only can effectively reduce the diameter of the impellers to realize compact arrangement, but also can achieve the purpose of high-efficiency recovery, thereby not only reducing the cost, but also improving the recovery yield.
3) The two technical schemes of the high-speed turbo machinery with the back-back compression impeller structure can select series compression or parallel compression according to actual conditions, and realize the function of outputting gas with large flow rate at small pressure ratio or gas with small flow rate at large pressure ratio.
4) Long life and high reliability. The high-speed turbo machinery adopts gas bearings comprising a dynamic pressure gas bearing and a static pressure gas bearing. The gas bearing is cooled by utilizing the suction of the compression impeller, and the bearing capacity and the stability are improved. Meanwhile, the complete machine can realize complete oil-free, and the hidden trouble that the oil lubrication bearing pollutes working media is avoided.
Drawings
FIG. 1 is a schematic diagram of a high speed turbomachine according to the parallel compression aspect of the present invention.
FIG. 2 is a schematic diagram of the construction of a high speed turbomachinery incorporating the present invention in a tandem compression arrangement.
Wherein: 1. first forward compression volute, 2, second fluid outlet, 3, main shaft, 4, first forward compression impeller, 5, first backward compression impeller, 6, first backward compression volute, 7, front bearing seat cover plate, 8, rear bearing seat cover plate, 9, middle housing, 10, nozzle cover plate, 11, expansion impeller, 12, expansion volute, 13, first fluid inlet, 14, second forward compression volute, 15, second forward compression impeller, 16, second backward compression impeller, 17, diffuser, 18, second backward compression volute, 19, second fluid inlet, 20, third fluid inlet, 21, third fluid outlet, 22, first fluid outlet, 23, aperture.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present invention more apparent, the technical solutions of the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings of the embodiments of the present invention, and it is obvious that the described embodiments are some, but not all embodiments of the present invention. All other embodiments, which can be obtained by a person skilled in the art without any inventive step based on the embodiments of the present invention, are within the scope of the present invention. Thus, the following detailed description of the embodiments of the present invention, presented in the figures, is not intended to limit the scope of the invention, as claimed, but is merely representative of selected embodiments of the invention.
A high-speed turbine structure applied to large flow and large expansion ratio comprises a main shaft 3, a forward compression volute, a backward compression volute, an intermediate shell 9 and an expansion volute 12; the forward compression volute, the backward compression volute, the middle shell 9 and the expansion volute 12 are sequentially connected, and a nozzle cover plate 10 is arranged between the middle shell 9 and the expansion volute 12; the main shaft 3 penetrates through the forward compression volute, the backward compression volute, the middle shell 9 and the expansion volute 12, one end of the main shaft 3 is provided with a pair of compression impellers which are arranged back to back, and the other end of the main shaft 3 is provided with an expansion impeller 11; a pair of back-to-back mounted compression impellers are respectively located in the forward compression volute and the backward compression volute, and the expansion impeller 11 is located in the expansion volute 12. A pair of gas radial bearings and a pair of gas thrust bearings for supporting the spindle 3 are arranged inside the middle shell 9, a small hole 23 is formed in the middle shell 9, and a filter is arranged at the inlet of the small hole 23.
As a preferred embodiment of the present invention, the intermediate housing 9 is provided with a second fluid inlet 19 adjacent to the rearward compression volute and a third fluid inlet 20 and a second fluid outlet 2 are provided on the forward compression volute.
As a preferred embodiment of the present invention, a diffuser 17 is disposed between the forward compression volute and the backward compression volute, and a third fluid outlet 21 is disposed on the backward compression volute, and the third fluid outlet 21 is connected to the third fluid inlet 20 of the forward compression volute through a pipeline.
As a preferred embodiment of the present invention, the expansion volute 12 includes a first fluid inlet 13 and a first fluid outlet 22.
As a preferred embodiment of the present invention, the inner diameter of the expansion volute 12 at the first fluid outlet 22 gradually increases from inside to outside, and performs a diffusion and deceleration function on the fluid flowing through the first fluid outlet 22.
In the intermediate housing 9, a front bearing seat cover plate 7 and a rear bearing seat cover plate 8 are provided as a preferred embodiment of the present invention.
As a preferred embodiment of the present invention, the pair of gas radial bearings in the middle housing 9 comprises a front radial bearing, a rear radial bearing; the pair of gas thrust bearings comprises a front thrust bearing and a rear thrust bearing; the front radial bearing and the front thrust bearing are arranged on the front bearing seat cover plate 7, and the rear radial bearing and the rear thrust bearing are arranged on the rear bearing seat cover plate 8.
As a preferred embodiment of the present invention, the gas thrust bearing and the gas radial bearing are dynamic pressure gas bearings or static pressure gas bearings.
In a preferred embodiment of the present invention, the small hole 23 is located between the rear bearing seat cover plate 8 and the nozzle cover plate 10, and the front bearing seat cover plate 7 and the rear bearing seat cover plate 8 are respectively provided with a through hole.
Example 1:
referring to fig. 1, a high-speed turbine structure applied to high flow rate and large expansion ratio comprises a middle housing 9, a main shaft 3, an expansion impeller 11 mounted at one end of the main shaft 3, an expansion volute 12 fitted to the expansion impeller 11 and mounted on the middle housing 9, two back-to-back compression impellers (a first forward compression impeller 4 and a first backward compression impeller 5) mounted at the other end of the main shaft 3, a first backward compression volute 6 mounted on the middle housing 9, and a first forward compression volute 1 mounted on the first backward compression volute 6.
The mounting positions of the two back-to-back compression impellers are located at the center position of the backward compression volute 6. The first forward compression wheel 4 circumferentially cooperates with the inlet of the first forward compression volute 1 and the first backward compression impeller 5 circumferentially cooperates with the inlet of the first backward compression volute 6. The installation position of the expansion impeller 11 is located at the axial center position of the expansion volute 12. The expansion impeller 11 is fitted circumferentially to the outlet of the nozzle cover plate 10.
A diffuser is arranged in the expansion volute 11, and the inlet of the diffuser is matched with the outlet of the expansion impeller 11. Inside said first forward compression volute 1 is arranged a first compression inducer (third fluid inlet 20) the outlet of which cooperates with the inlet of the first forward compression impeller 4. A second compression inducer is arranged inside the backward compression volute 6, and the outlet of the second compression inducer is matched with the inlet of the backward compression impeller 5.
A pair of gas radial bearings and a pair of gas thrust bearings are arranged inside the intermediate housing 9. The front radial bearing and the front thrust bearing are arranged on the front bearing seat cover plate 7, and the rear radial bearing and the rear thrust bearing are arranged on the rear bearing seat cover plate 8. The gas thrust bearing and the gas radial bearing may be dynamic pressure gas bearings or static pressure gas bearings.
Gas can pass through after the filter edulcoration aperture 23 of opening on the middle casing 9, then the warp behind rear bearing apron 8 with behind the through-hole on the preceding bearing apron 7 by first backward compression impeller 5 inhales, gas can cool off when passing through the bearing apron the gas bearing of installation on the apron improves the bearing capacity and the stability of bearing.
The working principle of the embodiment of the invention is as follows:
in the embodiment, the parallel compression condition is adopted, and on the expansion impeller 11 side, fluid with certain speed and pressure flows in from the first fluid inlet 13 arranged on the expansion volute 12, passes through the airflow channel of the expansion volute and then flows into the nozzle cover plate 10 respectively. The flow speed of the fluid in the flow channel of the nozzle is accelerated, and the pressure is reduced. Then, the fluid uniformly flows through the expansion impeller 11 from the outlet of the nozzle, continues to expand in the expansion impeller and applies work to the expansion impeller, thereby driving the expansion impeller 11 to rotate. The expanded fluid flows out after diffusion and deceleration through a first fluid outlet 22 (diffusion section) on the expansion volute 12. The rotation of the expansion impeller 11 will drive the main shaft 3 to rotate, and further drive the two back-to-back first forward and backward compression impellers 4 and 5 at the other end of the main shaft 3 to rotate.
Low-pressure gas is sucked by the first forward centrifugal compression impeller 4 from an inlet (a third fluid inlet 20) on the first forward compression volute 1 and the first backward centrifugal compression impeller 5 from an inlet (a second fluid inlet 19) mounted on the intermediate housing 9, the flow rate is increased in the first forward compression impeller 4 and the first backward centrifugal compression impeller 5, the pressure is increased and then enters the common diffuser, the pressure is increased, the speed is reduced, the low-pressure gas is discharged into the common compression volute 1, and finally the low-pressure gas is discharged from an outlet (a second fluid outlet 2) mounted on the compression volute 1.
The back-to-back impellers in the invention include but are not limited to two identical impellers, as long as the exhaust pressure is the same, the exhaust is convenient for the common exhaust, the flow rates of the two impellers can be different, and the adjustment of the axial force of the impellers is realized by distributing different flow rates so as to balance the axial force on the expansion impeller side. In addition, in order to ensure that the diameters of the two impellers are the same, structural parameters such as the height of the outlet blade of the impeller, the angle of the outlet blade of the impeller and the like need to be adjusted, so that the arrangement of the impeller structure of the back rest is facilitated.
Example 2:
referring to fig. 2, a high-speed turbine structure applied to high flow rate and large expansion ratio comprises a middle housing 9, a main shaft 3, an expansion impeller 11 mounted at one end of the main shaft 3, an expansion volute 12 fitted to the expansion impeller 11 and mounted on the middle housing 9, two back-to-back compression impellers (a second forward compression impeller 15 and a second backward compression impeller 16) mounted at the other end of the main shaft 3, a first backward compression volute 6 mounted on the middle housing 9, and a first forward compression volute 1 mounted on the first backward compression volute 6.
The mounting positions of the two back-to-back compression impellers are located at the center position of the backward compression volute 6. The first forward compression wheel 4 circumferentially mates with the inlet of a second forward compression volute 14 and the second rearward compression impeller 16 circumferentially mates with the inlet of a second rearward compression volute 18. The installation position of the expansion impeller 11 is located at the axial center position of the expansion volute 12. The expansion impeller 11 is fitted circumferentially to the outlet of the nozzle cover plate 10. A diffuser 17 is arranged between the forward compression volute and the backward compression volute, a third fluid outlet 21 is arranged on the backward compression volute, and the third fluid outlet 21 is connected with a third fluid inlet 20 of the forward compression volute through a pipeline.
And a diffusion section is arranged in the expansion volute 11, and an inlet of the diffusion section is matched with an outlet of the expansion impeller 11. Inside said second forward compression volute 14 is arranged a first compression inducer (third fluid inlet 20) the outlet of which cooperates with the inlet of the second forward compression impeller 15. A second compression inducer is disposed within the second rearward compression volute 18 with an outlet of the second compression inducer matching an inlet of the second rearward compression impeller 16.
A pair of gas radial bearings and a pair of gas thrust bearings are arranged inside the intermediate housing 9. The front radial bearing and the front thrust bearing are arranged on the front bearing seat cover plate 7, and the rear radial bearing and the rear thrust bearing are arranged on the rear bearing seat cover plate 8. The gas thrust bearing and the gas radial bearing may be dynamic pressure gas bearings or static pressure gas bearings.
Gas can pass through after the filter edulcoration aperture 23 of opening on the middle casing 9, then the process behind rear bearing apron 8 with behind the through-hole on the preceding bearing apron 7 by the second is inhaled to compression impeller 16 behind, and gas can cool off when passing through the bearing apron the gas bearing of installation on the apron improves the bearing capacity and the stability of bearing.
The working principle of the embodiment is as follows:
in the embodiment of the tandem compression working condition, on the expansion impeller 11 side, fluid with certain speed and pressure flows in from the first fluid inlet 13 installed on the expansion volute 12, and flows into the nozzle cover plate 10 after passing through the airflow channel of the expansion volute. The flow speed of the fluid in the flow channel of the nozzle is accelerated, and the pressure is reduced. Then, the fluid uniformly flows through the expansion impeller 11 from the outlet of the nozzle, continues to expand in the expansion impeller and applies work to the expansion impeller, thereby driving the expansion impeller 11 to rotate. The expanded fluid flows out after diffusion and deceleration through a first fluid outlet 22 (diffusion section) on the expansion volute 12. The rotation of the expansion impeller 11 will drive the main shaft 3 to rotate, and further drive the two back-to-back second forward compression impellers 15 and the second backward compression impeller 16 at the other end of the main shaft 3 to rotate.
Low-pressure gas is sucked from an inlet (a second fluid inlet 19) on the middle shell 9 by a second backward centrifugal compression impeller 16, is compressed in the impeller, is accelerated in flow speed, is increased in pressure and then enters a diffuser 17, is increased in pressure and is reduced in speed, and is discharged into a second backward compression volute 18; the gas enters the inlet of the second forward compression volute 14 through a pipeline, then enters the second forward compression impeller 15, the pressure is increased, the flow rate is increased, then the gas enters the diffuser 17, the pressure is increased, the speed is reduced, the gas is discharged into the second forward compression volute 14, and finally high-pressure gas is discharged from the outlet (the second fluid outlet 2) on the second forward compression volute, so that the purpose of efficiently recovering expansion work is achieved. The pressure ratio of the two impellers can be different, and the adjustment of the axial force of the impellers is realized by distributing different pressure ratios to balance the axial force on the expansion impeller side.
The invention adopts two back-to-back impellers to recover expansion work, not only the diameter of the impeller is small and the structure is compact, but also the two impellers can be selected to be applied by series compression or parallel compression, thereby realizing the function of outputting gas with different flow and pressure. Meanwhile, the two impellers are distributed with different flow rates and proper inlet pressure under the parallel compression working condition, the two impellers are distributed with different pressure ratios under the serial compression working condition, and the axial force of the two impellers on the side can be adjusted, so that the integral axial force of the expansion machine can achieve self balance.
Two back-to-back centrifugal compression impellers are adopted to recover expansion work, the output work of the expansion impeller with large flow rate and large expansion ratio is large, and a single compression impeller needs large flow rate and wheel diameter to recover, so that the efficiency of a single impeller is not high, and the size of parts on the compression side is also large. The two back-to-back impellers are adopted to recover expansion work, so that the diameter of the impeller can be reduced, and the high-efficiency recovery expansion work is realized on the basis of ensuring the compactness.
According to actual use requirements, the two back-to-back compression impellers can adopt a parallel compression scheme or a series compression scheme; and when the parallel compression is carried out, the air inlet pressure of the two impellers is determined according to the actual requirement. The air inlet pressure is high, the braking power of the impeller is large, and the diameter of the impeller can be reduced. When the compression is carried out in series, compared with the compression in parallel, the total pressure ratio of the impeller is high, and the flow is small.
The above description is only an embodiment of the present invention, and not intended to limit the scope of the present invention, and all equivalent structures or equivalent flow transformations made by using the contents of the specification and the drawings, or applied directly or indirectly to other related systems, are included in the scope of the present invention.
Claims (7)
1. The utility model provides a be applied to high-speed turbine structure of big expansion ratio of large-traffic which characterized in that:
comprises a main shaft (3), a forward compression volute, a backward compression volute, an intermediate shell (9) and an expansion volute (12);
the forward compression volute, the backward compression volute, the middle shell (9) and the expansion volute (12) are sequentially connected, and a nozzle cover plate (10) is arranged between the middle shell (9) and the expansion volute (12);
the main shaft (3) penetrates through the forward compression volute, the backward compression volute, the middle shell (9) and the expansion volute (12), one end of the main shaft (3) is provided with a pair of compression impellers which are arranged back to back, and the other end of the main shaft (3) is provided with an expansion impeller (11);
a pair of back-to-back mounted compression impellers are respectively positioned in the forward compression volute and the backward compression volute, and the expansion impeller (11) is positioned in the expansion volute (12);
a pair of gas radial bearings and a pair of gas thrust bearings for supporting the main shaft (3) are arranged in the middle shell (9), a small hole (23) is formed in the middle shell (9), and a filter is arranged at the inlet of the small hole (23);
a front bearing seat cover plate (7) and a rear bearing seat cover plate (8) are arranged in the middle shell (9);
the small hole (23) on the middle shell (9) is positioned between the rear bearing seat cover plate (8) and the nozzle cover plate (10), and the front bearing seat cover plate (7) and the rear bearing seat cover plate (8) are respectively provided with a through hole.
2. The high-speed turbine structure applied to high flow rate and large expansion ratio according to claim 1, characterized in that:
a second fluid inlet (19) is formed in the middle shell (9) and is close to the backward compression volute, and a third fluid inlet (20) and a second fluid outlet (2) are formed in the forward compression volute.
3. The high-speed turbine structure applied to high flow rate and large expansion ratio according to claim 1, characterized in that:
a diffuser (17) is arranged between the forward compression volute and the backward compression volute, a third fluid outlet (21) is arranged on the backward compression volute, and the third fluid outlet (21) is connected with a third fluid inlet (20) of the forward compression volute through a pipeline.
4. A high-speed turbine structure applied to a large flow rate and a large expansion ratio according to claim 2 or 3, wherein:
the expansion volute (12) comprises a first fluid inlet (13) and a first fluid outlet (22).
5. The high-speed turbine structure applied to high flow rate and large expansion ratio according to claim 4, is characterized in that:
the inner diameter of the expansion volute (12) at the first fluid outlet (22) is gradually increased from inside to outside, and the expansion volute plays a role in diffusion and deceleration of fluid flowing through the first fluid outlet (22).
6. The high-speed turbine structure applied to high flow rate and large expansion ratio according to claim 5, wherein:
the pair of gas radial bearings comprises a front radial bearing and a rear radial bearing; the pair of gas thrust bearings comprises a front thrust bearing and a rear thrust bearing; the front radial bearing and the front thrust bearing are arranged on a front bearing seat cover plate (7), and the rear radial bearing and the rear thrust bearing are arranged on a rear bearing seat cover plate (8).
7. The high-speed turbine structure applied to high flow rate and large expansion ratio according to claim 6, wherein:
the gas thrust bearing and the gas radial bearing are dynamic pressure gas bearings or static pressure gas bearings.
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| CN113757134B (en) * | 2021-07-28 | 2023-07-14 | 浙江镕达永能压缩机有限公司 | Centrifugal vapor compressor with double impellers arranged in back-to-back manner |
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| CN1128061A (en) * | 1993-06-15 | 1996-07-31 | 多堆垛国际有限公司 | Compressor |
| JP2008522102A (en) * | 2004-12-03 | 2008-06-26 | ハネウェル・インターナショナル・インコーポレーテッド | Multistage compressor and its housing |
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