CN117419058B - Compact type breathing machine supercharger suitable for plateau environment - Google Patents
Compact type breathing machine supercharger suitable for plateau environment Download PDFInfo
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- CN117419058B CN117419058B CN202311733550.XA CN202311733550A CN117419058B CN 117419058 B CN117419058 B CN 117419058B CN 202311733550 A CN202311733550 A CN 202311733550A CN 117419058 B CN117419058 B CN 117419058B
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- blades
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- 230000029058 respiratory gaseous exchange Effects 0.000 title abstract description 15
- 238000007789 sealing Methods 0.000 claims abstract description 5
- 230000007704 transition Effects 0.000 claims description 3
- 230000009467 reduction Effects 0.000 abstract description 6
- 239000012530 fluid Substances 0.000 abstract description 2
- 239000007789 gas Substances 0.000 description 17
- 238000013461 design Methods 0.000 description 5
- 238000010586 diagram Methods 0.000 description 5
- 206010021143 Hypoxia Diseases 0.000 description 3
- 230000007423 decrease Effects 0.000 description 3
- 238000009792 diffusion process Methods 0.000 description 3
- 230000007954 hypoxia Effects 0.000 description 3
- 238000000034 method Methods 0.000 description 3
- 230000008569 process Effects 0.000 description 3
- 208000004756 Respiratory Insufficiency Diseases 0.000 description 2
- 238000006243 chemical reaction Methods 0.000 description 2
- 239000003814 drug Substances 0.000 description 2
- 230000000241 respiratory effect Effects 0.000 description 2
- 201000004193 respiratory failure Diseases 0.000 description 2
- 230000007306 turnover Effects 0.000 description 2
- 206010002091 Anaesthesia Diseases 0.000 description 1
- 206010010071 Coma Diseases 0.000 description 1
- 206010067671 Disease complication Diseases 0.000 description 1
- 206010019233 Headaches Diseases 0.000 description 1
- 208000006083 Hypokinesia Diseases 0.000 description 1
- 206010028813 Nausea Diseases 0.000 description 1
- 206010037423 Pulmonary oedema Diseases 0.000 description 1
- 208000027418 Wounds and injury Diseases 0.000 description 1
- 230000001133 acceleration Effects 0.000 description 1
- 230000037005 anaesthesia Effects 0.000 description 1
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 description 1
- 238000005452 bending Methods 0.000 description 1
- 230000017531 blood circulation Effects 0.000 description 1
- 210000004556 brain Anatomy 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 230000006378 damage Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 208000002173 dizziness Diseases 0.000 description 1
- 230000009977 dual effect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 231100000869 headache Toxicity 0.000 description 1
- 208000014674 injury Diseases 0.000 description 1
- 230000007774 longterm Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000008693 nausea Effects 0.000 description 1
- 239000001301 oxygen Substances 0.000 description 1
- 229910052760 oxygen Inorganic materials 0.000 description 1
- 208000005333 pulmonary edema Diseases 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 238000001356 surgical procedure Methods 0.000 description 1
- 208000024891 symptom Diseases 0.000 description 1
- 238000009423 ventilation Methods 0.000 description 1
- 210000004916 vomit Anatomy 0.000 description 1
- 230000008673 vomiting Effects 0.000 description 1
Classifications
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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
- 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
- F04D17/125—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 the casing being vertically split
-
- A—HUMAN NECESSITIES
- A61—MEDICAL OR VETERINARY SCIENCE; HYGIENE
- A61M—DEVICES FOR INTRODUCING MEDIA INTO, OR ONTO, THE BODY; DEVICES FOR TRANSDUCING BODY MEDIA OR FOR TAKING MEDIA FROM THE BODY; DEVICES FOR PRODUCING OR ENDING SLEEP OR STUPOR
- A61M16/00—Devices for influencing the respiratory system of patients by gas treatment, e.g. mouth-to-mouth respiration; Tracheal tubes
- A61M16/0057—Pumps therefor
- A61M16/0066—Blowers or centrifugal 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
- F04D25/00—Pumping installations or systems
- F04D25/02—Units comprising pumps and their driving means
- F04D25/08—Units comprising pumps and their driving means the working fluid being air, e.g. for ventilation
-
- 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
-
- 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
- F04D29/30—Vanes
-
- 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
-
- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02K—DYNAMO-ELECTRIC MACHINES
- H02K7/00—Arrangements for handling mechanical energy structurally associated with dynamo-electric machines, e.g. structural association with mechanical driving motors or auxiliary dynamo-electric machines
- H02K7/14—Structural association with mechanical loads, e.g. with hand-held machine tools or fans
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Health & Medical Sciences (AREA)
- Biomedical Technology (AREA)
- Emergency Medicine (AREA)
- Pulmonology (AREA)
- Anesthesiology (AREA)
- Power Engineering (AREA)
- Heart & Thoracic Surgery (AREA)
- Hematology (AREA)
- Life Sciences & Earth Sciences (AREA)
- Animal Behavior & Ethology (AREA)
- General Health & Medical Sciences (AREA)
- Public Health (AREA)
- Veterinary Medicine (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
A compact type breathing machine supercharger suitable for a plateau environment belongs to the technical field of medical appliances. The invention solves the problems that the flow of fluid in the centrifugal compressor is influenced by the reduction of the mass flow of the inlet of the supercharger under the plateau environment of the existing respirator, and the efficiency of the compressor is further influenced. The centrifugal impeller comprises a volute and a two-stage centrifugal impeller, wherein a shell is arranged outside the two-stage centrifugal impeller in a surrounding mode, gaps are reserved between the shell and the one-stage centrifugal impeller and between the shell and the two-stage centrifugal impeller, the bottom end of the shell is fixedly connected with the volute in a sealing mode, and an interstage flow channel is formed between the one-stage centrifugal impeller and the two-stage centrifugal impeller through the shell arranged in a surrounding mode. According to the invention, the two centrifugal impellers with different sizes are coaxially and fixedly connected to form the compact double-stage centrifugal impeller, so that compared with the centrifugal impeller in the prior art, the supercharging capacity of the centrifugal impeller is improved on the basis that the size of the centrifugal impeller is smaller and the centrifugal impeller is suitable for the smaller size of a breathing machine.
Description
Technical Field
The invention relates to a compact type breathing machine supercharger suitable for a plateau environment, and belongs to the technical field of medical appliances.
Background
In modern clinical medicine, a respirator is used as an effective means capable of providing energy to replace autonomous ventilation of a person by the outside, and is widely used in respiratory failure caused by various reasons, anesthesia respiratory management during major surgery, respiratory support treatment and emergency resuscitation, and occupies a very important position in the field of modern medicine. The breathing machine is a vital medical device which can prevent and treat respiratory failure, reduce disease complications, save and prolong the life of patients. Under the plateau environment, the organism accelerates respiration and blood circulation for the purpose of compensating hypoxia due to the reduction of air pressure, and the phenomenon of rapid breathing and acceleration of heart rate occurs, and the serious person even can generate pulmonary edema and coma due to the symptoms of dizziness, headache, nausea, vomit, hypodynamia and the like due to the hypoxia of human body (especially brain), and the long-term hypoxia can cause the functional injury of the organism.
The key part of the pressurizing design of the breathing machine is a centrifugal impeller, and the centrifugal impeller can provide compressed air with certain pressure and flow rate so as to obtain mixed gas with oxygen concentration and flow rate required in clinical treatment. In the field of centrifugal impeller applications, particularly in the civil field, the direction of development and the aim pursued by centrifugal impellers are mainly high efficiency, wide working range, low noise, long life and low cost.
Due to the air characteristics in the plateau environment: the reduced atmospheric pressure and lower air density require a stronger pressurization capability and a greater inlet volumetric flow rate in addition to the high efficiency requirements for the ventilator. In a plateau environment, as the altitude increases, the air rarefaction degree increases, the atmospheric pressure and the temperature decrease, the mass flow rate of the inlet of the breathing machine supercharger in the prior art decreases, the highest pressure ratio of the turbine at the same rotating speed is basically kept unchanged, the Reynolds number in the compressor decreases, the fluid flow in the centrifugal compressor is influenced, the pressure of a low-pressure area of the relative total pressure of the radial surface of the turbine is smaller, the high-entropy area between the blade top gaps and the outlet of the impeller increases, and the range is advanced. The tip clearance flow is enhanced, the leakage loss is increased, the main flow of the pressure side of the splitter blade is mixed with the low-speed leakage flow, the wake area is increased, the mixing loss is increased, and the internal loss of the micro turbine impeller is increased, so that the efficiency of the compressor is reduced. Accordingly, there is a need for a compact ventilator booster suitable for use in a plateau environment to meet the needs for its boost capability in a low-pressure, low-density plateau environment, while minimizing the size of the ventilator booster.
Disclosure of Invention
The invention aims to solve the technical problems and further provides a compact type breathing machine supercharger suitable for a plateau environment.
The technical scheme adopted by the invention for solving the technical problems is as follows:
a compact type breathing machine supercharger suitable for a plateau environment comprises a volute and a two-stage centrifugal impeller, wherein,
the volute comprises a spiral volute chamber, the spiral volute chamber is provided with an annular gas inlet,
the two-stage centrifugal impeller comprises a first-stage centrifugal impeller, a second-stage centrifugal impeller and a shell,
the first-stage centrifugal impeller comprises a first chassis, a first hollow shaft and a plurality of first blades, the second-stage centrifugal impeller comprises a second chassis, a second hollow shaft and a plurality of second blades, the first chassis and the second chassis are fixedly connected with each other through the upper and lower coaxial shafts of the second hollow shaft, the first hollow shaft is fixedly arranged on the first chassis and is communicated with the upper and lower coaxial shafts of the second hollow shaft, the plurality of first blades are circumferentially fixed outside the first hollow shaft and fixedly connected with the top surface of the first chassis, the plurality of second blades are circumferentially fixed outside the second hollow shaft and fixedly connected with the top surface of the second chassis,
the shell is enclosed outside the two-stage centrifugal impeller along with the shell, gaps exist between the shell and the one-stage centrifugal impeller and between the shell and the two-stage centrifugal impeller, the bottom end of the shell is fixedly connected with the volute in a sealing way, and an interstage flow channel is formed between the one-stage centrifugal impeller and the two-stage centrifugal impeller through the shell arranged along with the shell.
Further, the plurality of first blades and the plurality of second blades are backward bending blades.
Further, the air inlet of the first-stage centrifugal impeller is larger than the air inlet of the second-stage centrifugal impeller.
Further, the second hollow shaft is in arc transition connection with the first chassis.
Further, the line of intersection between the trailing edge of each blade and its pressure face, and the line of intersection with its suction face, are rounded.
Further, the number of the first blades is 12-15, and the number of the second blades is 6-10.
Further, the inlet airflow direction at the front edge blade root of the primary centrifugal impeller and the tangential line of the front edge blade root circle at the front edge blade root form an included angleIn the range of not more than 50 DEG, the angle between the direction of the outlet air flow at the trailing edge of the primary centrifugal impeller and the tangent of the trailing edge circle at the trailing edge +.>The range of (2) is not less than 75 DEG, and the included angle between the inlet airflow direction at the front edge blade root of the secondary centrifugal impeller and the tangent line of the front edge blade root circle at the front edge blade root is ∈>In the range of not more than 60 DEG, the included angle between the direction of the outlet air flow at the trailing edge of the secondary centrifugal impeller and the tangent of the trailing edge circle at the trailing edge +.>Is in the range of not less than 40 deg..
Further, the base circle diameter D of the first chassis 3 Is (1.03-1.10) D 2 Wherein D is 2 The distance from the curved trailing edge of the first blade to the first chassis centerline is the diameter of the circle formed by the radius.
Further, the thickness d of the first blade 1 0.5 mm-1 mm, the thickness d of the second blade 2 0.5mm to 1mm.
Further, the thickness of the first chassis is 0.4 mm-0.8 mm, and the thickness of the second chassis is 0.4 mm-0.8 mm.
Compared with the prior art, the invention has the following effects:
according to the invention, two centrifugal impellers with different sizes are coaxially and fixedly connected to form a compact two-stage centrifugal impeller, and compared with the centrifugal impeller in the prior art, the supercharging capacity of the centrifugal impeller is improved on the basis that the size of the centrifugal impeller is smaller and the centrifugal impeller is suitable for the smaller size of a breathing machine;
in addition, the motor for controlling the rotation of the centrifugal impeller is arranged at the outer position of the centrifugal impeller, and the motor is connected with the first blade and the second blade in the two-stage centrifugal impeller by the rotating shaft to rotate, so that the axial size of the supercharger is effectively shortened, the along-distance loss of the air flow flowing through the flow channel and the local loss of the air flow flowing through the turn-over and the bend pipe in the flowing process are reduced, and compared with the prior art, the two-stage centrifugal impeller has stronger supercharging capacity and smaller size.
According to the invention, the two-stage centrifugal impeller is arranged, so that the compressor has higher pressure ratio and better flow efficiency, and the reduction of air pressure and the reduction of Reynolds number in a plateau environment are relieved, thereby improving the efficiency of the compressor, and being suitable for the high requirements of the ventilator in the plateau environment.
Drawings
FIG. 1 is a first perspective view of the present invention;
fig. 2 is a second perspective view of the present invention (the housing is not shown);
FIG. 3 is a third perspective view of the present invention (the housing and primary centrifugal impeller are not shown);
FIG. 4 is a schematic top view of a primary centrifugal impeller;
FIG. 5 is a schematic top view of a two-stage centrifugal impeller;
FIG. 6 is a schematic diagram of gas flow in a dual stage centrifugal impeller;
fig. 7 is a schematic view of a radial cross-section of the volute.
In the figure:
1. a volute; 2. a two-stage centrifugal impeller; 3. a spiral volute; 4. a gas inlet; 5. a diffusion tube; 6. a volute tongue; 7. a primary centrifugal impeller; 8. a secondary centrifugal impeller; 9. a housing; 10. a first chassis; 11. a first hollow shaft; 12. a first blade; 13. a first pressure surface; 14. a first suction surface; 15. a second chassis; 16. a second hollow shaft; 17. a second blade; 18. a second pressure surface; 19. and a second suction surface.
Detailed Description
The first embodiment is as follows: the technical solution in the embodiments of the present invention will be clearly and completely described by referring to fig. 1 to 7, and it is apparent that the described embodiments are only some embodiments, but not all embodiments of the present invention, and all other embodiments obtained by those skilled in the art without making any creative effort based on the embodiments of the present invention are all within the protection scope of the present invention.
It should be noted that, the descriptions of the directions of "left", "right", "upper", "lower", "top", "bottom", and the like of the present invention are defined based on the relation of orientations or positions shown in the drawings, and are only for convenience in describing the present invention and simplifying the description, and do not indicate or imply that the structures must be constructed and operated in a specific orientation, and thus, the present invention should not be construed as being limited thereto. In the description of the present invention, the meaning of "plurality" is two or more unless specifically defined otherwise.
In the description of the present invention, unless explicitly stated and limited otherwise, the terms "mounted," "connected," and "connected" are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected; can be directly connected or indirectly connected through an intermediate medium, and can be communication between two elements. The specific meaning of the above terms in the present invention will be understood in specific cases by those of ordinary skill in the art.
In the present embodiment, the blade height direction refers to a direction from the blade root to the tip or a direction from the disk to the tip; the axial direction refers to the arrangement direction along the two shaft holes; the blade profile direction is the direction from the leading edge to the trailing edge in the camber line of the blade profile.
A compact type breathing machine supercharger suitable for a plateau environment comprises a volute 1 and a two-stage centrifugal impeller 2, wherein,
the volute 1 comprises a spiral volute 3, the spiral volute 3 being provided with an annular gas inlet 4,
the two-stage centrifugal impeller 2 comprises a first-stage centrifugal impeller 7, a second-stage centrifugal impeller 8 and a shell 9,
the first-stage centrifugal impeller 7 comprises a first chassis 10, a first hollow shaft 11 and a plurality of first blades 12, the second-stage centrifugal impeller 8 comprises a second chassis 15, a second hollow shaft 16 and a plurality of second blades 17, the first chassis 10 and the second chassis 15 are fixedly connected with each other coaxially through the second hollow shaft 16, the first hollow shaft 11 is fixedly arranged on the first chassis 10 and is communicated with the second hollow shaft 16 coaxially up and down, the plurality of first blades 12 are circumferentially fixedly arranged outside the first hollow shaft 11 and fixedly connected with the top surface of the first chassis 10, the plurality of second blades 17 are circumferentially fixedly arranged outside the second hollow shaft 16 and fixedly connected with the top surface of the second chassis 15,
the shell 9 is arranged outside the two-stage centrifugal impeller 2 in a surrounding mode, gaps are reserved between the shell and the one-stage centrifugal impeller 7 and between the shell and the two-stage centrifugal impeller 8, the bottom end of the shell 9 is fixedly connected with the volute 1 in a sealing mode, and an interstage flow channel is formed between the one-stage centrifugal impeller 7 and the two-stage centrifugal impeller 8 through the shell 9 arranged in a surrounding mode.
The first hollow shaft 11 is fixedly connected with an output shaft of a motor, and the output shaft of the motor rotates to drive the first-stage centrifugal impeller 7 and the second-stage centrifugal impeller 8 to rotate. The first hollow shaft 11 and the second hollow shaft 16 are rigidly connected with an external motor, so that the two-stage impellers are connected to coaxially rotate, and the structure is simple and the strength is better.
The bottom of the volute 1 is provided with a bottom plate in a sealing manner, and a second chassis 15 of the secondary centrifugal impeller 8 is positioned between the shell 9 and the bottom plate and rotates along with the motor. The gas inlet 4 on the volute 1 is circumferentially open, and the trailing edge of the second vane 17 is arranged towards the gas inlet 4 of the volute 1.
The gas outlet end of the volute 1 is provided with a diffusion pipe 5, so that the pressurized gas can flow out conveniently. The cross section of the diffuser 5 is circular. The length of the diffuser pipe 5 is as short as possible within the allowable range.
The primary centrifugal impeller 7 and the secondary centrifugal impeller 8 are both formed into semi-open impellers by a shell 9 enclosed outside the two-stage centrifugal impeller 2.
The first pressure surface 13 and the first suction surface 14 on the first blade 12 are both connected to the upper surface of the first chassis 10 along the direction of the line of the first blade 12, and the second pressure surface 18 and the second suction surface 19 on the second blade 17 are both connected to the upper surface of the second chassis 15 along the direction of the line of the second blade 17.
The leading edge of the first blade 12 and the leading edge of the second blade 17 are both linear, and the trailing edge of the first blade 12 and the trailing edge of the second blade 17 are both curved.
The first pressure surface 13 and the first suction surface 14 of the first blade 12 are curved surfaces perpendicular to the upper surface of the first chassis 10; the first pressure surface 13 and the first suction surface 14 are determined by Bezier curves of the leading edge and the trailing edge of the first blade 12;
the second pressure surface 18 and the second suction surface 19 of the second blade 17 are curved surfaces perpendicular to the upper surface of the second chassis 15; the second pressure surface 18 and the second suction surface 19 are determined by bezier curves of the leading edge and the trailing edge of the second blade 17.
According to the invention, two centrifugal impellers with different sizes are coaxially and fixedly connected to form the compact double-stage centrifugal impeller 2, and compared with the centrifugal impellers in the prior art, the supercharging capacity of the centrifugal impeller is improved on the basis that the size of the centrifugal impeller is smaller and the centrifugal impeller is suitable for the smaller size of a breathing machine;
in addition, the motor for controlling the rotation of the centrifugal impeller is arranged at the outer position of the centrifugal impeller, and the motor is connected with the first blade 12 and the second blade 17 in the two-stage centrifugal impeller 2 by the rotating shaft to rotate, so that the axial size of the supercharger is effectively shortened, the along-distance loss of the air flow flowing through the flow channel and the local loss of the air flowing through the turn-over and the bent pipe in the flowing process are reduced, and compared with the prior art, the two-stage centrifugal impeller has stronger supercharging capacity and smaller size.
According to the invention, the two-stage centrifugal impeller 2 is arranged, so that the compressor has higher pressure ratio and better flow efficiency, and the reduction of air pressure and the reduction of Reynolds number in a plateau environment are relieved, thereby improving the efficiency of the compressor, and being suitable for the high requirements of the ventilator in the plateau environment.
Working principle:
external air enters from the front edge of the first blade 12 in the primary centrifugal impeller 7, contacts with the linear front edge of the primary centrifugal impeller 7, is connected with the first hollow shaft 11 through a shaft by a motor to drive the primary centrifugal impeller and the secondary centrifugal impeller to rotate,
the air flow contacting with the linear front edge of the first blade 12 is divided into two parts, and flows to the curve-shaped tail edge of the first blade 12 along the first pressure surface 13 and the first suction surface 14 respectively, and in the flowing process, the air flow in the two-stage centrifugal impeller 2 is acted due to the rotation of the first blade 12, and the total air flow pressure and static pressure at the curve-shaped tail edge of the first blade 12 are higher than those of the linear front edge of the first blade 12, so that the aim of improving the air kinetic energy and pressure is fulfilled.
After passing through the primary centrifugal impeller 7, the gas flows to the secondary centrifugal impeller 8 through an interstage flow passage, and is driven by the second blades 17 as in the primary centrifugal impeller 7, so that the kinetic energy and pressure of the gas are further improved.
After passing through the two-stage centrifugal impeller 2, gas is converged into the spiral casing 1 through the gas inlet 4 on the spiral casing 1, firstly enters the spiral casing 3, and the gas speed is reduced, the pressure is increased, the kinetic energy is converted into pressure energy and then flows out of the diffusion pipe 5 due to the expansion of the sectional area of the gas flow passage.
The diameter D at the root of the straight leading edge of the first blade 12 can be adjusted according to the desired inlet flow and velocity 0 And diameter D at the linear leading edge tip of the first blade 12 1 Optionally, the diameter D at the root of the straight leading edge blade 0 The range of (2) is 3-6 mm, and the range is 5mm in the schematic diagram of the invention. Diameter D at the tip of the straight leading edge blade 1 The range of (2) is 15-25 mm, and 18mm is shown in the schematic diagram of the invention. Optionally, the distance from the curved trailing edge of the first blade 12 to the first chassis centerline is the diameter D of a radius-formed circle 2 The radial dimension of the centrifugal impeller is 34-60 mm, 46mm in the schematic diagram of the invention.
The impeller inlet width b, which in the present schematic illustration is 3mm, can be adjusted depending on the desired inlet flow and velocity.
Spiral angle of volute tongueThe included angle between the tangent line of the spiral line and the tangent line of the base circle is at the starting point of the spiral line of the scroll chamber. In order to allow gas to pass from the impeller into the volute without impact, optionally +.>The angle of flow, equal to the absolute velocity of the impeller outlet at a later time, the angle of the volute tongue helix in the schematic of the invention +.>Is 3.14 deg..
Volute tongue setting angleTheoretically, the volute tongue 6 should be at the base circle D of the spiral starting point of the spiral chamber 3 3 However, this would make the gap between the volute tongue 6 and the impeller too small, so that vibration and noise are easily generated, and the volute tongue 6 is too thin, so that the volute tongue 6 is generally moved along the volute spiral line +.>And (5) corners. Optionally, the volute tongue placement angle is selected based on the specific rotational speed. Radius r of volute tongue 6 shown 3 The volute tongue is provided with a corner>And the relevant parameters of the diffuser 5, in the present schematic diagram of the invention the volute tongue setting angle +.>36.2 deg..
The radial dimension of the outer wall of the spiral volute 3 is gradually increased along the gas flow direction in the spiral volute 3, the increasing proportion is formed by using the speed-based Pleiderer theory, and the flow rate of the centrifugal compressor and the proportional relation of the cross sections are obtained, wherein the cross sections are common circular cross sections.
The tip of each blade and the upper surface (i.e., the root) of the disk are designed by Bezier curves.
The first blades 12 and the second blades 17 are backward curved blades.
The air inlet of the first-stage centrifugal impeller 7 is larger than the air inlet of the second-stage centrifugal impeller 8. By design, the front edge width of the first blade 12 determines the size of the air inlet of the primary centrifugal impeller 7, and the larger inlet of the front edge of the primary centrifugal impeller 7 provides conditions for increasing the air flow so as to effectively improve the efficiency of the air compressor.
The second hollow shaft 16 is in arc transition connection with the first chassis 10. By the design, the interstage channel is smooth, and the incoming flow of the first-stage centrifugal impeller 7 is ensured to smoothly enter the second-stage centrifugal impeller 8.
The line of intersection between the trailing edge of each blade and its pressure face, and the line of intersection with its suction face, are rounded. Specifically, the line of intersection between the trailing edge of each first blade 12 and the first pressure surface 13 of that first blade 12, the line of intersection between the trailing edge of each first blade 12 and the first suction surface 14 of that first blade 12, the line of intersection between the trailing edge of each second blade 17 and the second pressure surface 18 of that second blade 17, and the line of intersection between the trailing edge of each second blade 17 and the second suction surface 19 of that second blade 17 are all rounded. By the design, the strength of end wall corner vortex generated in the clearance flow of air flow is reduced, loss in the flow is reduced, the aerodynamic performance of the turbine is facilitated, and the supercharging efficiency is improved.
The number of the first blades 12 is 12-15, and the number of the second blades 17 is 6-10. So designed, for example, the number of first blades 12 is 15 and the number of second blades 17 is 10.
In the range of not more than 50 DEG,/or more>In the range of not less than 75 DEG,/or more>In the range of not more than 60 DEG,/or more>Is in the range of not less than 40 deg.. Designed in such a way that in the primary centrifugal impeller 7, -a centrifugal impeller is provided>: the inlet air flow direction at the leading edge blade root is at an angle to the tangent of the leading edge blade root circle at the leading edge blade root. />: inlet airflow direction at leading edge tip and leading edgeThe angle of tangent to the tip circle at the tip of the leading edge. />: the direction of the outlet airflow at the trailing edge is at an angle to the tangent of the trailing edge circle at the trailing edge.
In the secondary centrifugal impeller 8 in question,: the inlet air flow direction at the leading edge blade root is at an angle to the tangent of the leading edge blade root circle at the leading edge blade root. />: the inlet airflow direction at the leading edge tip is at an angle to the tangent of the leading edge tip circle at the leading edge tip. />: the direction of the outlet airflow at the trailing edge is at an angle to the tangent of the trailing edge circle at the trailing edge.
From the following components、/>、/>The direction of the airflow and the profile of the first blade 12 may be determined, and since the first blade 12 may perform work on the airflow, the first blade 12 may be subjected to a reaction force by the airflow, and thus the first blade 12 may not meet the strength requirement if it is too curved, alternatively>In the range of not more than 50 DEG,/or more>In the range of not less than 75,can be made of->And->Is determined by the specific value of (c) and the specific shape of the leading edge of the blade. In the schematic of the invention->45.2 DEG>78.4 DEG>50.8 deg.. By->、/>、/>The direction of the airflow and the profile of the second blade 17 may be determined, and the second blade 17 may not meet the strength requirement if it is too curved, since the second blade 17 may work on the airflow and the second blade 17 may be subjected to the reaction force of the airflow, alternatively the strength requirement may be not met>In the range of not more than 60,in the range of not less than 40 DEG,/or->Can be made of->And->Is determined by the specific value of (c) and the specific shape of the leading edge of the blade. The inventionIn the clear schematic->48.1 DEG>48.6 DEG>40.3.
Base circle diameter D of first chassis 10 3 1.03 to 1.10D 2 . So designed, the base circle diameter of the first chassis 10 can be selected within this range so as not to significantly affect the performance of the microturbine.
Base circle diameter D of spiral volute 3 5 1.03 to 1.10D 4 ，D 4 For the diameter at the trailing edge of the second blade 17, the base circle size can be selected within this range so as not to have a significant impact on the performance of the microturbine. The spiral line of the spiral volute 3 is formed by applying the speed-based Pleiderer theory, the circumferential section of the spiral volute 3 is circular, and the spiral volute 3 is formed by the spiral line and a circle formed at a corresponding position. The invention selects the base circle diameter D of the spiral volute 3 5 45mm.
Thickness d of first blade 12 1 The thickness d of the second blade 17 is 0.5mm to 1mm 2 0.5mm to 1mm. The design is so designed as to meet the requirements for blade strength after boost capability is improved. The specific thickness selection is based on the required strength of the blades, the size of the centrifugal impeller and the number of blades, and is determined by combining the width of the straight leading edge, the thickness of the curved trailing edge and the Bezier curve selected for the tip and root.
The thickness of the first chassis 10 is 0.4 mm-0.8 mm, and the thickness of the second chassis 15 is 0.4 mm-0.8 mm. Designed in such a way as to ensure uniformity of axial load. The specific thickness is selected based on the desired strength of the chassis.
The foregoing is only a preferred embodiment of the present invention, but the scope of the present invention is not limited thereto, and any person skilled in the art, who is within the scope of the present invention, should make equivalent substitutions or modifications according to the technical scheme of the present invention and the inventive concept thereof, and should be covered by the scope of the present invention.
Claims (7)
1. A compact ventilator booster suitable for use in a plateau environment, characterized by: comprises a volute (1) and a two-stage centrifugal impeller (2), wherein,
the volute (1) comprises a spiral volute chamber (3), the spiral volute chamber (3) is provided with an annular gas inlet (4),
the two-stage centrifugal impeller (2) comprises a first-stage centrifugal impeller (7), a second-stage centrifugal impeller (8) and a shell (9),
the first-stage centrifugal impeller (7) comprises a first chassis (10), a first hollow shaft (11) and a plurality of first blades (12), the second-stage centrifugal impeller (8) comprises a second chassis (15), a second hollow shaft (16) and a plurality of second blades (17), the first chassis (10) and the second chassis (15) are fixedly connected with each other through the upper and lower coaxial shafts of the second hollow shaft (16), the first hollow shaft (11) is fixedly arranged on the first chassis (10) and is fixedly connected with the upper and lower coaxial shafts of the second hollow shaft (16), the plurality of first blades (12) are circumferentially fixed outside the first hollow shaft (11) and fixedly connected with the top surface of the first chassis (10), the plurality of second blades (17) are circumferentially fixed outside the second hollow shaft (16) and fixedly connected with the top surface of the second chassis (15),
the shell (9) is arranged outside the two-stage centrifugal impeller (2) in a surrounding mode, gaps are reserved among the shell, the one-stage centrifugal impeller (7) and the two-stage centrifugal impeller (8), the bottom end of the shell (9) is fixedly connected with the volute (1) in a sealing mode, and an interstage flow channel is formed between the one-stage centrifugal impeller (7) and the two-stage centrifugal impeller (8) through the shell (9) arranged in the following mode;
the intersection line between the tail edge of each blade and the pressure surface and the intersection line between the tail edge of each blade and the suction surface are rounded;
the included angle between the inlet airflow direction at the front blade root of the primary centrifugal impeller (7) and the tangent line of the front blade root circle at the front blade rootIn the range of not more than 50 DEG, the included angle between the direction of the outlet air flow at the trailing edge of the primary centrifugal impeller (7) and the tangent line of the trailing edge circle at the trailing edge +.>In the range of not less than 75 DEG, the inlet air flow direction at the front blade root of the secondary centrifugal impeller (8) and the tangential line of the front blade root circle at the front blade root are included in->In the range of not more than 60 DEG, the included angle between the direction of the outlet air flow at the trailing edge of the secondary centrifugal impeller (8) and the tangent line of the trailing edge circle at the trailing edge +.>In the range of not less than 40 °;
the air inlet of the first-stage centrifugal impeller (7) is larger than the air inlet of the second-stage centrifugal impeller (8).
2. A compact ventilator booster adapted for use in a highland environment as defined in claim 1, wherein: the first blades (12) and the second blades (17) are backward bent blades.
3. A compact ventilator booster adapted for use in a highland environment as defined in claim 1, wherein: the second hollow shaft (16) is in arc transition connection with the first chassis (10).
4. A compact ventilator booster adapted for use in a highland environment as defined in claim 1, wherein: the number of the first blades (12) is 12-15, and the number of the second blades (17) is 6-10.
5. A compact ventilator booster adapted for use in a highland environment as defined in claim 1, wherein: base of the first chassis (10)Diameter D of circle 3 Is (1.03-1.10) D 2 Wherein D is 2 The distance from the curved trailing edge of the first blade (12) to the first chassis centerline is the diameter of a circle formed by the radius.
6. A compact ventilator booster adapted for use in a highland environment as defined in claim 1, wherein: thickness d of first blade (12) 1 The thickness d of the second blade (17) is 0.5 mm-1 mm 2 0.5mm to 1mm.
7. A compact ventilator booster adapted for use in a highland environment as defined in claim 1, wherein: the thickness of the first chassis (10) is 0.4 mm-0.8 mm, and the thickness of the second chassis (15) is 0.4 mm-0.8 mm.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202311733550.XA CN117419058B (en) | 2023-12-18 | 2023-12-18 | Compact type breathing machine supercharger suitable for plateau environment |
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| CN202311733550.XA CN117419058B (en) | 2023-12-18 | 2023-12-18 | Compact type breathing machine supercharger suitable for plateau environment |
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| CN117419058B true CN117419058B (en) | 2024-03-19 |
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| KR20200079039A (en) * | 2018-12-24 | 2020-07-02 | 엘지전자 주식회사 | Two stage centrifugal compressor |
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| CN114876864A (en) * | 2022-04-11 | 2022-08-09 | 哈尔滨工业大学 | Micro-turbine and breathing machine with same |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| KR20150113580A (en) * | 2014-03-31 | 2015-10-08 | 주식회사 멕 아이씨에스 | Impeller of 2 step radial blower |
| CN108317092A (en) * | 2018-02-02 | 2018-07-24 | 天津快透平科技发展有限公司 | Impeller and centrifugal compressor including the impeller |
| KR20200079039A (en) * | 2018-12-24 | 2020-07-02 | 엘지전자 주식회사 | Two stage centrifugal compressor |
| CH717838A2 (en) * | 2020-09-14 | 2022-03-15 | Imtmedical Ag | Two-stage blower device for a ventilator. |
| CN114526249A (en) * | 2021-12-17 | 2022-05-24 | 可孚医疗科技股份有限公司 | Two-stage centrifugal impeller fan for air pressurization system of breathing machine |
| CN114876864A (en) * | 2022-04-11 | 2022-08-09 | 哈尔滨工业大学 | Micro-turbine and breathing machine with same |
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| CN117419058A (en) | 2024-01-19 |
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