CN115467844A - Large-diameter integral composite impeller - Google Patents
Large-diameter integral composite impeller Download PDFInfo
- Publication number
- CN115467844A CN115467844A CN202211152377.XA CN202211152377A CN115467844A CN 115467844 A CN115467844 A CN 115467844A CN 202211152377 A CN202211152377 A CN 202211152377A CN 115467844 A CN115467844 A CN 115467844A
- Authority
- CN
- China
- Prior art keywords
- rotor
- rotor blade
- blades
- stage
- blade
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 239000002131 composite material Substances 0.000 title claims abstract description 28
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims description 18
- 229910052782 aluminium Inorganic materials 0.000 claims description 18
- 238000003754 machining Methods 0.000 claims description 8
- 238000010438 heat treatment Methods 0.000 claims description 3
- 230000003647 oxidation Effects 0.000 claims description 3
- 238000007254 oxidation reaction Methods 0.000 claims description 3
- 230000003247 decreasing effect Effects 0.000 claims 1
- 230000003068 static effect Effects 0.000 abstract description 2
- 239000004429 Calibre Substances 0.000 abstract 1
- 238000001816 cooling Methods 0.000 description 2
- 238000009825 accumulation Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 230000007423 decrease Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
Images
Classifications
-
- 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
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D19/00—Axial-flow pumps
- F04D19/02—Multi-stage pumps
- F04D19/04—Multi-stage pumps specially adapted to the production of a high vacuum, e.g. molecular pumps
- F04D19/042—Turbomolecular vacuum 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
- 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
Abstract
The invention discloses a large-caliber integral composite impeller, which comprises turbine blades (7 stages in total) with different diameters, a rotor spindle, a rotor blade (3 stages) and a large-disc traction stage blade, wherein the turbine blades (7 stages in total) are shown in figure 1; the turbine-stage blades and the traction-stage blades are integrally formed on the core shaft, mounting grooves are formed in the middle of the first stage and the next stage of the blades, and the mounting grooves are reserved for mounting the static blades; the rotor part comprises a set of rotor traction stage blades, a set of rotor turbine stage blades and a set of rotor spindle, wherein the set of rotor traction stage blades, the set of rotor turbine stage blades and the set of rotor spindle are arranged along the axial direction of the power spindle. This kind of whole composite impeller of heavy-calibre, through design dabber and rotor part integrated into one piece, machining center integrated into one piece's big disk composite impeller, so design, impeller shaft symmetry is good, and is more steady during the operation, and the running life is longer.
Description
Technical Field
The invention relates to the technical field of composite impellers, in particular to a large-caliber integral composite impeller.
Background
A turbo-molecular pump is a vacuum pump that transfers momentum to gas molecules by using a moving impeller rotating at a high speed to generate a directional flow of the gas to pump the gas, and is widely used in engineering practice, such as aerospace, medical equipment, instruments and meters, and the like. The impeller of the turbomolecular pump includes a plurality of blades extending radially from the rotating body, the stator blade includes a plurality of blades extending radially toward the rotating shaft of the rotating body, and the linear velocity of the outer edge of the impeller of the turbomolecular pump is as high as the velocity of thermal motion of gas molecules (typically 150 to 400 m/s). The compression ratio of a single impeller is small, and the turbomolecular pump consists of more than ten movable impellers and static impellers which are alternately arranged. At present, the movable impeller of the domestic large-caliber molecular pump is processed by a single piece, then assembled and fastened by screws to be connected into a whole.
The assembled impeller has large error formed by the error accumulation of each single impeller, is difficult to adjust the dynamic balance, and can generate resonance and noise in the running process of the impeller in actual work, so that the bearing is damaged, and the service life of the molecular pump is shortened. Therefore, we improve the above and provide a large-caliber integral composite impeller.
Disclosure of Invention
In order to solve the technical problems, the invention provides the following technical scheme:
the invention relates to a large-diameter integral composite impeller, which comprises a traction-stage blade part, a turbine-stage blade part and a rotor mandrel part, wherein the rotor mandrel part comprises a rotor mandrel;
turbine stage blade part includes that rotor blade is a set of, rotor blade is two and three groups of rotor blade, rotor blade is a set of, rotor blade is two and three axial direction settings along the rotor spindle of group of rotor blade and rotor blade three groups, the setting of the different angle slopes respectively of the leaf tooth that rotor blade is a set of, rotor blade is two and three groups of rotor blade.
Furthermore, a set of rotor blades and three sets of rotor blades all comprise a plurality of independent rotor blades, the rotor blades are arranged in an annular array mode along a rotating mandrel, gaps for compressing gas are arranged between the rotor blades, and an exhaust channel is formed.
Further, rotor blade is a set of, rotor blade is two and three interior rotor blade's of group of rotor blade length is the linearity and decreases progressively, rotor blade is a set of, rotor blade is two and three sets of surfaces that set gradually at the rotation dabber of rotor blade, a set of setting of rotor blade is topmost at the rotor dabber.
Furthermore, the inclination angle of the rotor blade in the turbine-grade blade part is 20-40 degrees, the integral composite impeller is formed by machining 7075-H112 aluminum profiles, the tensile strength of the aluminum profiles is 570MPa, the yield strength of the aluminum profiles is 517MPa, the elongation of the aluminum profiles is 10.5-13.5%, the hardness of the aluminum profiles is 60-120 HB, the machining stress is eliminated during machining of the aluminum profiles by heating to 140 ℃ and keeping the temperature for 16 hours and cooling along with a furnace, and the surface of the aluminum profiles is subjected to aluminum oxidation treatment.
Furthermore, an axis taper through hole is formed in the rotor mandrel and penetrates through the center line of the rotor mandrel, and the taper through hole has a taper ratio of 1:10 and has a self-locking function.
Furthermore, a dynamic balance hole is formed in the uppermost end of the rotor mandrel, the dynamic balance hole is a screw hole, and 16-M4 MM deep and 12MM and 4-M8 MM deep and 14MM are reserved for high-speed dynamic balance.
The invention has the beneficial effects that: the large-caliber integral composite impeller is integrally formed by designing the rotor mandrel part, the turbine-stage blade part and the traction-stage blade part, and is integrally formed by a machining center.
Drawings
The accompanying drawings, which are included to provide a further understanding of the invention and are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and together with the description serve to explain the principles of the invention and not to limit the invention. In the drawings:
FIG. 1 is a first perspective view of a large diameter integral composite impeller of the present invention;
FIG. 2 is a second perspective view of a large diameter integral composite impeller of the present invention;
FIG. 3 is a cross-sectional perspective view of a large diameter integral composite impeller of the present invention;
fig. 4 is an inside elevational view of a large bore integral composite impeller of the present invention.
FIG. 5 is a tooth parameter diagram of a large-diameter integral composite impeller according to the present invention
In the figure: 1. a drag stage blade component; 2. a rotor spindle component; 3. a turbine stage blade component; 31. a set of rotor blades; 32. two groups of rotor blades; 33. three groups of rotor blades; 4. a dynamic balance hole; 5. an axis taper through hole;
Detailed Description
The preferred embodiments of the present invention will be described in conjunction with the accompanying drawings, and it will be understood that they are described herein for the purpose of illustration and explanation and not limitation.
Example (b): as shown in fig. 1 to 5, the large-diameter integral composite impeller of the present invention includes a traction-stage blade component 1, a turbine-stage blade component 3, and a rotor spindle component 2, wherein the rotor spindle component 2 includes a rotor spindle, the traction-stage blade component 1, the turbine-stage blade component 3, and the rotor spindle component 2 are integrally formed, and a taper hole is formed in the middle of the rotor spindle component 2, and the taper hole penetrates through the rotor spindle and is reserved for connecting with a driving spindle.
The turbine stage blade component 3 includes a set of rotor blades 31, a set of rotor blades 32, and a set of rotor blades 33, the set of rotor blades 31, the set of rotor blades 32, and the set of rotor blades 33 are arranged along the axial direction of the rotor spindle, and the teeth of the set of rotor blades 31, the set of rotor blades 32, and the set of rotor blades 33 are respectively arranged in different angles.
Wherein, a set of 31 of rotor blade, two sets of 32 of rotor blade and three sets of 33 of rotor blade all include a plurality of solitary rotor blade, and rotor blade is the annular array along rotating the dabber and setting up, is provided with the clearance that is used for compressed gas between the rotor blade to form exhaust passage.
Wherein, rotor blade's length is linear degressive in a set of 31, two 32 and three 33 interior rotor blade of rotor blade, and a set of 31, two 32 and three 33 of rotor blade set gradually on the surface of rotating the dabber, and a set of 31 of rotor blade sets up at the rotor dabber top.
Wherein, the inclination angle of the rotor blade in the turbine-grade blade component 3 is 20-40 degrees, the integral composite impeller is formed by machining 7075-H112 aluminum profiles, the tensile strength of the aluminum profiles is 570MPa, the yield strength is 517MPa, the elongation is 10.5-13.5 percent, the hardness is 60-120 HB, when the aluminum profiles are machined, the machining stress is eliminated by heating to 140 ℃, keeping the temperature for 16 hours, cooling along with a furnace, and carrying out aluminum oxidation treatment on the surfaces of the aluminum profiles.
Wherein, an axis taper through hole 5 is arranged in the rotor mandrel, the axis taper through hole 5 penetrates through the center line of the rotor mandrel, the taper through hole has the taper of 1:10, and the self-locking function is realized.
The uppermost end of the rotor mandrel is provided with a dynamic balance hole 4, the dynamic balance hole 4 is a screw hole, and 16-M4 MM deep and 12MM and 4-M8 MM deep and 14MM are reserved for high-speed dynamic balance.
The working principle is as follows: the large-caliber integral composite impeller is characterized in that an installation shaft of the impeller penetrates through an axial taper through hole 5, the composite impeller can be installed in a molecular pump, a turbine-stage blade part 3 is in clearance fit with a stationary blade in the molecular pump and rotates to form an air exhaust channel, the rotor mandrel part 2, the turbine-stage blade part 3 and a traction-stage blade part 1 are integrally formed, and a machining center integrally machines and forms the large-disc composite impeller.
Finally, it should be noted that: in the description of the present invention, it should be noted that the terms "vertical", "upper", "lower", "horizontal", and the like indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience of describing the present invention and simplifying the description, but do not indicate or imply that the referred device or element must have a specific orientation, be constructed in a specific orientation, and be operated, and thus, should not be construed as limiting the present invention.
In the description of the present invention, it should also be noted that, unless otherwise explicitly specified or limited, the terms "disposed," "mounted," "connected," and "connected" are to be construed broadly and may, for example, be fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood by those skilled in the art according to specific situations.
Although the present invention has been described in detail with reference to the foregoing embodiments, it will be apparent to those skilled in the art that changes may be made in the embodiments and/or equivalents thereof without departing from the spirit and scope of the invention. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (6)
1. The large-caliber integral composite impeller is characterized by comprising a traction-stage blade part (1), a turbine-stage blade part (3) and a rotor mandrel part (2), wherein the rotor mandrel part (2) comprises a rotor mandrel, the traction-stage blade part (1), the turbine-stage blade part (3) and the rotor mandrel part (2) are of an integrally formed structure, a taper hole is formed in the middle of the rotor mandrel part (2), and the taper hole penetrates through the rotor mandrel and is reserved for connecting a driving main shaft;
turbine stage blade part (3) include that rotor blade is a set of (31), two (32) of rotor blade and three (33) of rotor blade, the axial direction setting along the rotor spindle is organized to a set of (31), two (32) of rotor blade and three (33) of rotor blade, the lobe tooth that a set of (31), two (32) of rotor blade and three (33) of rotor blade is different angle slope respectively and sets up.
2. A large-bore integral composite impeller according to claim 1, characterized in that the first set (31), the second set (32) and the third set (33) of rotor blades comprise a plurality of individual rotor blades, which are arranged in a ring-shaped array along a rotating spindle, and gaps for compressed gas are provided between the rotor blades and form exhaust channels.
3. The large-caliber integral composite impeller according to claim 1, wherein the lengths of the rotor blades in the rotor blade group (31), the rotor blade group (32) and the rotor blade group (33) are linearly decreased, the rotor blade group (31), the rotor blade group (32) and the rotor blade group (33) are sequentially arranged on the surface of the rotating mandrel, and the rotor blade group (31) is arranged at the uppermost end of the rotating mandrel.
4. The large-caliber integral composite impeller according to claim 2, wherein the inclination angle of the rotor blade in the turbine-stage blade component (3) is 20-40 °, the integral composite impeller is formed by machining 7075-H112 aluminum profile, the aluminum profile has the tensile strength of 570MPa, the yield strength of 517MPa, the elongation of 10.5-13.5% and the hardness of 60-120 HB, the machining stress is eliminated by heating to 140 ℃ and keeping the temperature for 16 hours during machining of the aluminum profile, and the surface of the aluminum profile is subjected to aluminum oxidation treatment.
5. The large-caliber integral composite impeller according to claim 1, wherein an axial taper through hole (5) is formed in the rotor mandrel, the axial taper through hole (5) penetrates through the center line of the rotor mandrel, and the taper through hole has a 1.
6. The large-caliber integral composite impeller according to claim 1, wherein the uppermost end of the rotor mandrel is provided with a dynamic balance hole (4), the dynamic balance hole (4) is a screw hole, and 16-M4 MM deep and 12MM deep and 4-M8 MM deep and 14MM deep are reserved for high-speed dynamic balance.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211152377.XA CN115467844A (en) | 2022-09-21 | 2022-09-21 | Large-diameter integral composite impeller |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211152377.XA CN115467844A (en) | 2022-09-21 | 2022-09-21 | Large-diameter integral composite impeller |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN115467844A true CN115467844A (en) | 2022-12-13 |
Family
ID=84335875
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202211152377.XA Pending CN115467844A (en) | 2022-09-21 | 2022-09-21 | Large-diameter integral composite impeller |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN115467844A (en) |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN87103994A (en) * | 1987-06-03 | 1988-12-21 | 中国科学院北京真空物理实验室 | A kind of disk Shaped turbine compounded molecular pump |
| CN102536853A (en) * | 2012-03-06 | 2012-07-04 | 北京北仪创新真空技术有限责任公司 | High-performance compound molecular pump |
| CN203214351U (en) * | 2013-05-07 | 2013-09-25 | 天津飞旋科技研发有限公司 | Vacuum molecular pump impeller |
| CN203488431U (en) * | 2013-09-18 | 2014-03-19 | 北京北仪创新真空技术有限责任公司 | Molecular pump rotor capable of resisting atmospheric impact |
| CN110085498A (en) * | 2019-04-30 | 2019-08-02 | 上海联影医疗科技有限公司 | A kind of CT bulb and its assembly method |
-
2022
- 2022-09-21 CN CN202211152377.XA patent/CN115467844A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN87103994A (en) * | 1987-06-03 | 1988-12-21 | 中国科学院北京真空物理实验室 | A kind of disk Shaped turbine compounded molecular pump |
| CN102536853A (en) * | 2012-03-06 | 2012-07-04 | 北京北仪创新真空技术有限责任公司 | High-performance compound molecular pump |
| CN203214351U (en) * | 2013-05-07 | 2013-09-25 | 天津飞旋科技研发有限公司 | Vacuum molecular pump impeller |
| CN203488431U (en) * | 2013-09-18 | 2014-03-19 | 北京北仪创新真空技术有限责任公司 | Molecular pump rotor capable of resisting atmospheric impact |
| CN110085498A (en) * | 2019-04-30 | 2019-08-02 | 上海联影医疗科技有限公司 | A kind of CT bulb and its assembly method |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN1058774C (en) | Axial-flow blower with guiding in channel | |
| CN101297118B (en) | Stationary seal ring for a centrifugal compressor | |
| CN1177145C (en) | Propeller type centrofugal compressor structure | |
| US20050042118A1 (en) | Turbo vacuum pump and semiconductor manufacturing apparatus having the same | |
| US8109744B2 (en) | Turbo vacuum pump | |
| US9416784B2 (en) | Exhaust pump | |
| CN101287911A (en) | Centrifugal compressor including a seal system | |
| EP2623791A1 (en) | Exhaust pump | |
| CN109790847A (en) | Modularization turbocompressor shaft | |
| CN112628161A (en) | Air-cooled compressor | |
| JP5445143B2 (en) | Turbo molecular pump | |
| JP2020511615A (en) | Bearing device for drive shaft of turbomachine, and turbomachine equipped with such bearing device | |
| US6412173B1 (en) | Miniature turbomolecular pump | |
| US8105013B2 (en) | Vacuum pump | |
| CN110439847B (en) | Centrifugal compressor shafting structure and centrifugal compressor | |
| US6409468B1 (en) | Turbo-molecular pump | |
| CN1705203A (en) | Gas cooling electric machine with pressure unit | |
| EP1668256B1 (en) | Vacuum pump | |
| CN115467844A (en) | Large-diameter integral composite impeller | |
| US7938619B2 (en) | Turbo vacuum pump | |
| CN110714985A (en) | Microminiature air bearing system with middle air supply | |
| US11732722B2 (en) | Vacuum pump | |
| CN209805569U (en) | Unidirectional rotation permanent magnet high-speed motor and bidirectional air bearing thereof | |
| CN107061315B (en) | Molecular pump | |
| WO2021161010A1 (en) | Axial flow vacuum pump with curved rotor and stator blades |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination |