CN108150434B - Involute type air inlet multistage turbofan - Google Patents
Involute type air inlet multistage turbofan Download PDFInfo
- Publication number
- CN108150434B CN108150434B CN201810043237.6A CN201810043237A CN108150434B CN 108150434 B CN108150434 B CN 108150434B CN 201810043237 A CN201810043237 A CN 201810043237A CN 108150434 B CN108150434 B CN 108150434B
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- CN
- China
- Prior art keywords
- air inlet
- involute
- shell
- rotating shaft
- multistage turbofan
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- 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.)
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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
- F04D19/00—Axial-flow pumps
- F04D19/02—Multi-stage pumps
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/05—Shafts or bearings, or assemblies thereof, specially adapted for elastic fluid pumps
- F04D29/056—Bearings
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/26—Rotors specially for elastic fluids
- F04D29/32—Rotors specially for elastic fluids for axial flow pumps
- F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/26—Rotors specially for elastic fluids
- F04D29/32—Rotors specially for elastic fluids for axial flow pumps
- F04D29/38—Blades
- F04D29/388—Blades characterised by construction
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/40—Casings; Connections of working fluid
- F04D29/52—Casings; Connections of working fluid for axial pumps
- F04D29/522—Casings; Connections of working fluid for axial pumps especially adapted for elastic fluid pumps
Abstract
The invention discloses an involute air inlet multistage turbofan, which comprises an involute air inlet shell, a main rotating shaft, a fixed turbine, a movable impeller, a middle shell and an air outlet shell, wherein the fixed turbine is fixedly arranged in the middle shell, the movable impeller is fixedly arranged on the main rotating shaft, rotates along with the main rotating shaft and is positioned on one side of the fixed turbine, the involute air inlet shell is arranged at one end of the middle shell, the air outlet shell is arranged at the other end of the middle shell, the involute air inlet shell is an involute spiral-shaped pipe body structure air inlet shell, and air enters along the tangential direction of the involute air inlet shell. The invention solves the problem of lubricating grease splashing, and the structure has better air inlet effect, reduces pressure loss and enhances the overall performance of the fan.
Description
Technical Field
The invention relates to a turbofan, in particular to an involute type air inlet multistage turbofan.
Background
The pneumatic ship unloader is a machine for sucking and unloading bulk materials (such as grains, cement and the like) from a cabin by utilizing negative pressure airflow formed by a fan in a pipeline. The requirement on the fan is that the efficiency is high, the air quantity and the air pressure meet the requirement on conveying materials, and when the air pressure changes, the air quantity changes little, so that the fan is convenient to maintain. The research and development of the multistage turbofan with high efficiency, environmental protection and low noise enables companies to really master the core technology of the pneumatic ship unloader. As shown in fig. 4, the air inlet bearing is built in the conventional multistage turbofan, so that lubricating grease is easily splashed onto the movable turbine, the dynamic balance of the movable turbine is affected, and the performance of the whole turbofan is affected. And the whole bearing seat is positioned in the center of the air inlet pipeline, so that the pressure loss of the pipeline is increased, and the performance of the whole machine is reduced.
Disclosure of Invention
The invention aims to solve the technical problem of providing an involute type air inlet multistage turbofan, which solves the problem that lubricating grease at an air inlet splashes to blades in the prior art.
In order to solve the technical problems, the technical scheme adopted by the invention is as follows:
the utility model provides a multistage turbofan of involute type air inlet which characterized in that: contain involute type air inlet casing, main pivot, decide the turbine, the movable vane wheel, middle casing and air outlet casing, decide the fixed setting of turbine in the middle casing, the movable vane wheel is fixed and is rotatory and be located and decide turbine one side along main pivot in main pivot, involute type air inlet casing sets up casing one end in the middle, the air outlet casing sets up the casing other end in the middle, involute type air inlet casing is involute spiral shape's body structure air inlet casing, wind gets into along involute type air inlet casing's tangential direction.
Furthermore, the pipeline size of the involute air inlet shell is gradually reduced from the inlet end to the outlet end.
Further, be provided with the vortex blade in the involute air inlet casing, the vortex blade is fixed to be set up at involute air inlet casing inboard, is provided with a plurality of openings on the vortex blade, and a plurality of openings set up and every opening periphery is provided with bellied strengthening rib along vortex blade circumference equidistant.
Furthermore, one end of the main rotating shaft penetrates out of the center of the involute air inlet shell and is rotatably arranged in the involute air inlet shell.
Furthermore, an air inlet bearing is arranged at one end of the main rotating shaft and fixed on the outer side of the involute air inlet shell.
Furthermore, the multiple groups of fixed turbines and movable turbines are arranged in parallel in the middle shell, and the middle shell is connected and fixed through a connecting rod.
Compared with the prior art, the invention has the following advantages and effects: according to the invention, the traditional central air inlet opening is improved into the involute air inlet shell, so that the air inlet avoids the middle rotating shaft, and the rotating shaft bearing is externally arranged on the outer side of the involute air inlet shell, so that the problem of lubricating grease splashing is completely solved, the air inlet effect of the structure is better, the pressure loss is reduced, and the overall performance of the fan is enhanced.
Drawings
FIG. 1 is a schematic view of an involute air inlet multistage turbofan of the present invention.
Fig. 2 is a cross-sectional view of an involute air inlet multistage turbofan of the present invention.
Fig. 3 is a schematic view of the inside of an involute air intake housing of an involute air intake multistage turbofan according to the present invention.
FIG. 4 is a schematic view of a prior art turbofan.
Detailed Description
The present invention will be described in further detail below by way of examples with reference to the accompanying drawings, which are illustrative of the present invention and are not to be construed as limiting the present invention.
As shown in fig. 1 and 2, the involute type air inlet multistage turbofan according to the present invention includes an involute type air inlet casing 1, a main rotating shaft 2, a fixed turbine 3, a movable turbine 4, a middle casing 5 and an air outlet casing 6, wherein the fixed turbine 3 is fixedly disposed in the middle casing 5, the movable turbine 4 is fixed on the main rotating shaft 2 and rotates with the main rotating shaft 2 and is located at one side of the fixed turbine 3, the involute type air inlet casing 1 is disposed at one end of the middle casing 5, the air outlet casing 6 is disposed at the other end of the middle casing 5, the involute type air inlet casing 1 is an involute spiral pipe body structure air inlet casing, and air enters along a tangential direction of the involute type air inlet casing.
The pipeline size of the involute air inlet shell 1 is gradually reduced from the inlet end to the outlet end. As shown in fig. 3, a vortex blade 9 is arranged in the involute air inlet housing 1, the vortex blade 9 is fixedly arranged on the inner side of the involute air inlet housing 1, a plurality of openings 10 are arranged on the vortex blade 9, the plurality of openings 10 are arranged at equal intervals along the circumferential direction of the vortex blade 9, and a raised reinforcing rib 11 is arranged on the periphery of each opening 10. Therefore, the air at the air inlet is compressed and accelerated in the pipeline of the involute air inlet shell 1, and then is expanded in the cavity between the vortex blade 9 and the involute air inlet shell 1 and then is uniformly distributed on the fixed turbine 3 and the movable turbine 4 through the plurality of openings 10 to drive the turbines, so that the integral structure is reasonable, and air inlet loss is avoided.
One end of the main rotating shaft 2 penetrates out of the center of the involute air inlet housing 1 and is rotatably arranged in the involute air inlet housing 1. An air inlet bearing 7 is arranged at one end part of the main rotating shaft 2, and the air inlet bearing 7 is fixed at the outer side of the involute air inlet shell 1.
The fixed turbines 3 and the movable turbines 4 are arranged in parallel in the middle shell 5, and the middle shell 5 is fixedly connected through a connecting rod 8.
According to the structure, the air inlet of the fan completely avoids the main rotating shaft, the bearing of the air inlet of the main rotating shaft is externally arranged on the outer side of the involute air inlet shell, so that the air inlet of the air inlet can not pass through the bearing completely, the problem that bearing lubricating grease splashes on the impeller is solved perfectly, in addition, the air inlet is not blocked by the bearing and the rotating shaft, the air inlet is utilized to the maximum, the pressure loss of a pipeline is reduced, and the overall performance of the fan is improved.
The above description of the present invention is intended to be illustrative. Various modifications, additions and substitutions for the specific embodiments described may be made by those skilled in the art without departing from the scope of the invention as defined in the accompanying claims.
Claims (5)
1. The utility model provides a multistage turbofan of involute type air inlet which characterized in that: the involute type air inlet shell is an involute spiral pipe body structure air inlet shell, and wind enters along the tangential direction of the involute type air inlet shell; be provided with the vortex blade in the involute air inlet casing, the vortex blade is fixed to be set up at involute air inlet casing inboard, is provided with a plurality of openings on the vortex blade, and a plurality of openings set up and every opening periphery is provided with bellied strengthening rib along vortex blade circumference equidistant.
2. An involute air inlet multistage turbofan according to claim 1 wherein: the pipeline size of the involute air inlet shell is gradually reduced from the inlet end to the outlet end.
3. An involute air inlet multistage turbofan according to claim 1 wherein: one end of the main rotating shaft penetrates out of the center of the involute air inlet shell and is rotatably arranged in the involute air inlet shell.
4. An involute air inlet multistage turbofan according to claim 1 wherein: and an air inlet bearing is arranged at one end part of the main rotating shaft and is fixed at the outer side of the involute air inlet shell.
5. An involute air inlet multistage turbofan according to claim 1 wherein: the middle shell is provided with a plurality of groups, the plurality of groups of middle shells are arranged in parallel and are fixedly connected through connecting rods, and the plurality of groups of fixed turbines and movable impellers correspond to the plurality of groups of middle shells one to one.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810043237.6A CN108150434B (en) | 2018-01-17 | 2018-01-17 | Involute type air inlet multistage turbofan |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810043237.6A CN108150434B (en) | 2018-01-17 | 2018-01-17 | Involute type air inlet multistage turbofan |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN108150434A CN108150434A (en) | 2018-06-12 |
| CN108150434B true CN108150434B (en) | 2020-08-25 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810043237.6A Active CN108150434B (en) | 2018-01-17 | 2018-01-17 | Involute type air inlet multistage turbofan |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108150434B (en) |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201982326U (en) * | 2011-02-24 | 2011-09-21 | 任昊君 | Multistage turbofan |
| CN202971312U (en) * | 2012-08-31 | 2013-06-05 | 湖北微特风机制造有限公司 | Novel two-stage low-speed centrifugal blower structure |
| CN104154009A (en) * | 2014-08-13 | 2014-11-19 | 深圳市锐钜科技有限公司 | Multistage supercharging suction fan with centrifugal wind wheels |
| CN205714827U (en) * | 2016-02-22 | 2016-11-23 | 柴俊麟 | A kind of spiral centrifugal blower and airhandling equipment |
| CN206129644U (en) * | 2016-08-29 | 2017-04-26 | 北京航天长峰股份有限公司 | A turbofan for automatically controlled breathing machine |
| CN106870379A (en) * | 2017-04-11 | 2017-06-20 | 浙江上建风机有限公司 | A kind of Multi-stage centrifugal fan device |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP2333245A1 (en) * | 2009-12-01 | 2011-06-15 | Siemens Aktiengesellschaft | Rotor assembly for a reheat steam turbine |
-
2018
- 2018-01-17 CN CN201810043237.6A patent/CN108150434B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201982326U (en) * | 2011-02-24 | 2011-09-21 | 任昊君 | Multistage turbofan |
| CN202971312U (en) * | 2012-08-31 | 2013-06-05 | 湖北微特风机制造有限公司 | Novel two-stage low-speed centrifugal blower structure |
| CN104154009A (en) * | 2014-08-13 | 2014-11-19 | 深圳市锐钜科技有限公司 | Multistage supercharging suction fan with centrifugal wind wheels |
| CN205714827U (en) * | 2016-02-22 | 2016-11-23 | 柴俊麟 | A kind of spiral centrifugal blower and airhandling equipment |
| CN206129644U (en) * | 2016-08-29 | 2017-04-26 | 北京航天长峰股份有限公司 | A turbofan for automatically controlled breathing machine |
| CN106870379A (en) * | 2017-04-11 | 2017-06-20 | 浙江上建风机有限公司 | A kind of Multi-stage centrifugal fan device |
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| Publication number | Publication date |
|---|---|
| CN108150434A (en) | 2018-06-12 |
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