CN112196813A - Lubricating oil cooling fan for unmanned helicopter - Google Patents
Lubricating oil cooling fan for unmanned helicopter Download PDFInfo
- Publication number
- CN112196813A CN112196813A CN202011028748.4A CN202011028748A CN112196813A CN 112196813 A CN112196813 A CN 112196813A CN 202011028748 A CN202011028748 A CN 202011028748A CN 112196813 A CN112196813 A CN 112196813A
- Authority
- CN
- China
- Prior art keywords
- cooling fan
- impeller
- blades
- air guide
- guide barrel
- 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
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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
- F04D19/002—Axial flow fans
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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
- F04D29/325—Rotors specially for elastic fluids for axial flow pumps for axial flow fans
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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
- F04D29/384—Blades characterised by form
- F04D29/386—Skewed blades
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/40—Casings; Connections of working fluid
- F04D29/52—Casings; Connections of working fluid for axial pumps
- F04D29/522—Casings; Connections of working fluid for axial pumps especially adapted for elastic fluid pumps
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/40—Casings; Connections of working fluid
- F04D29/52—Casings; Connections of working fluid for axial pumps
- F04D29/54—Fluid-guiding means, e.g. diffusers
- F04D29/541—Specially adapted for elastic fluid pumps
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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
- F04D29/60—Mounting; Assembling; Disassembling
- F04D29/64—Mounting; Assembling; Disassembling of axial pumps
- F04D29/644—Mounting; Assembling; Disassembling of axial pumps especially adapted for elastic fluid pumps
- F04D29/646—Mounting or removal of fans
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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
- F04D29/668—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps damping or preventing mechanical vibrations
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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
- F04D29/70—Suction grids; Strainers; Dust separation; Cleaning
- F04D29/701—Suction grids; Strainers; Dust separation; Cleaning especially adapted for elastic fluid pumps
- F04D29/703—Suction grids; Strainers; Dust separation; Cleaning especially adapted for elastic fluid pumps specially for fans, e.g. fan guards
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16N—LUBRICATING
- F16N39/00—Arrangements for conditioning of lubricants in the lubricating system
- F16N39/02—Arrangements for conditioning of lubricants in the lubricating system by cooling
Landscapes
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention belongs to the technical field of an oil lubricating system of an unmanned helicopter, and particularly relates to an oil lubricating cooling fan for the unmanned helicopter, which comprises: the air guide device comprises a plurality of screws, a plurality of bushings, an air inlet net component, an air guide barrel component, a hoop, a transition cover, a transition air duct and an impeller; the air inlet net component is fixed at the front end of the air guide barrel component through a plurality of screws and a plurality of bushings, the transition air channel is fixed at the rear end of the air guide barrel component through a hoop and a transition cover, and the impeller is arranged inside the air guide barrel component 4; the vanes on the impeller are distributed at unequal intervals, and the lubricating oil cooling fan adopting the impeller-stage plate type twisted vane structure reduces the nonuniformity of flow fields in the vane channels, reduces the flow loss among the flow channels, improves the efficiency of the lubricating oil cooling fan and ensures the normal work of a lubricating oil system.
Description
Technical Field
The invention belongs to the technical field of an oil lubricating system of an unmanned helicopter, and particularly relates to an oil lubricating cooling fan for an unmanned helicopter.
Background
When the lubricating oil cooling fan impeller rotates, mechanical energy transmitted by the main speed reducer is converted into kinetic energy of an air medium, and the kinetic energy and the air guide cylinder jointly act to transmit cold air to a cold edge of the lubricating oil radiator, so that high-temperature lubricating oil flowing through the lubricating oil radiator is cooled.
Conventional oil cooling fans generally employ an arrangement of blades that are equally spaced, and a plate-type or airfoil-type blade structure. The rigidity of the blade of the conventionally used lubricating oil cooling fan is far less than that of the hub, and the blade is thin, so that the vibration of the impeller is mainly the vibration of the blade, and simultaneously, the lift force of the blade is constantly changed due to the instability of inlet airflow, so that the vibration of the blade is easily excited; second, blade flutter may be induced due to flow-solid coupling, causing premature blade fatigue damage.
Disclosure of Invention
Aiming at the problems in the background art, the invention provides a lubricating oil cooling fan for an unmanned helicopter, which adopts an impeller-level plate-type twisted blade structure to reduce the nonuniformity of a flow field in a blade channel, reduce the flow loss among channels, improve the efficiency of the lubricating oil cooling fan and ensure the normal operation of a lubricating oil system.
In order to achieve the purpose, the invention is realized by adopting the following technical scheme.
A lubricant cooling fan for an unmanned helicopter, the lubricant cooling fan comprising: the device comprises a plurality of screws 1, a plurality of bushings 2, an air inlet net component 3, an air duct component 4, a hoop 5, a transition cover 6, a transition air duct 7 and an impeller 8;
the air inlet net component 3 is fixed at the front end of the air guide barrel component 4 through a plurality of screw rods 1 and a plurality of bushings 2, the transition air duct 7 is fixed at the rear end of the air guide barrel component 4 through a hoop 5 and a transition cover 6, and the impeller 8 is arranged inside the air guide barrel component 4;
the blades on the impeller 8 are distributed at unequal intervals.
The technical scheme of the invention has the characteristics and further improvements that:
(1) each blade on the impeller 8 adopts a plate-type twisted structure.
(2) The allowable unbalance amount of the impeller 8 is smaller than a preset value.
(3) When the dynamic balance precision of the impeller is controlled according to G5.6 grade, the preset value is designed to be 0.0995g.cm, and g.cm represents g.cm.
(4) The n adjacent blades on the impeller 8 are marked as a group of blades, and the distance between the first group of blades and the second group of blades is about 53 mm; the spacing between adjacent blades within a certain set of blades is about 36 mm; the first group of blades and the second group of blades are any group of blades.
(5) The transition cover 6 is a flexible device, and the fan can vibrate in the operation process, and the flexible device can prevent the fan from transmitting vibration to the transition air duct.
(6) A plurality of screws 1 connect the oil cooling fan with the final drive housing.
(7) The clearance between the outer edges of the blades and the inner wall of the air guide barrel assembly is 3mm, and the cylindricity of the inner wall of the air guide barrel assembly is not more than 0.3 mm.
The invention provides a lubricating oil cooling fan for an unmanned helicopter, which adopts an impeller-level plate-type twisted blade structure to reduce the nonuniformity of a flow field in a blade channel and reduce the flow loss among channels, thereby improving the efficiency of the lubricating oil cooling fan and ensuring the normal work of a lubricating oil system.
Drawings
FIG. 1 is a schematic structural diagram of a lubricating oil cooling fan for an unmanned helicopter according to an embodiment of the present invention;
FIG. 2 is a schematic structural diagram of an impeller provided in an embodiment of the present invention;
wherein, the device comprises a screw rod 1, a bushing 2, an air inlet network component 3, an air guide barrel component 4, a hoop 5, a transition cover 6, a transition air duct 7, an impeller 8 and a blade 81.
Detailed Description
An embodiment of the present invention provides an oil cooling fan for an unmanned helicopter, as shown in fig. 1, the cooling fan includes a 1-screw; 2-a bushing; 3-an air intake net assembly; 4-an air guide barrel assembly; 5, clamping a hoop; 6-a transition hood; 7-a bushing; 8-impeller.
The impeller is used as a main part of the lubricating oil cooling fan, and the structural size and the blade type line of the impeller play a decisive role in the performance of the fan.
(a) The blade adopts the board type distortion structure: the impact loss of the airflow at the inlet of the blade can be reduced, and the full-pressure efficiency is improved;
(b) the blades are arranged at unequal intervals: in order to improve the reliability of products and reduce aerodynamic noise, the blades are designed to be arranged in a non-equidistant mode, and resonance caused by overlapping of vibration and noise is reduced;
(c) controlling the allowable unbalance amount of the impeller: in order to avoid impeller distortion caused by periodic load, reduce the influence of unbalanced force of the impeller on the service life of the product and reduce the allowable unbalance amount of the impeller as much as possible.
In order to provide forced cooling air for the lubricating oil radiator and ensure the normal work of a lubricating oil system, the system is provided with a lubricating oil cooling fan. The impeller is used as a key part of the lubricating oil cooling fan (as shown in figure 2), on one hand, the structural size and the blade profile of the impeller play a decisive role in the performance of the whole fan; on the other hand, the impeller bears the action of centrifugal force during high-speed rotation and is a main bearing part of a product.
a) The blade adopts the board type distortion structure: the uniform velocity field is formed by airflow under the acceleration condition, the impact loss of the airflow at the inlet of the blade is reduced, and the full pressure efficiency of the axial flow fan can be improved by about 5 percent under the condition of uniform inlet velocity field;
b) the blades are arranged at unequal intervals: the cutting of certain vortex areas (such as channel vortex and gap vortex) in the flow field by the blades can cause airflow pulsation, and the airflow pulsation can be superposed on a characteristic frequency due to the geometric central symmetry of the blades when the blades are uniformly distributed, so that the vibration and the noise are increased. And the non-uniform distribution of 9 blades can eliminate the geometric periodic characteristic on the structure, thereby weakening the gain effect of airflow pulsation at a fixed frequency, converting the airflow pulsation into broadband harmonic waves and further reducing the aerodynamic noise peak value at the downstream of the impeller. Meanwhile, the circumferential layout of the blades is changed within a small angle change range, and the efficiency of the fan is not affected.
c) Controlling the allowable unbalance amount of the impeller: the dynamic balance precision of the impeller is controlled according to G5.6 grade (the allowable unbalance amount is designed to be 0.0995g.cm), the impeller is ensured to rotate stably in the working process, and the influence of the magnitude of periodic load (centrifugal force) on the impeller is reduced; the clearance between the outer edge of the blade and the inner wall of the air guide cylinder is designed to be 3mm, the cylindricity of the inner wall of the air guide cylinder is regulated to be not more than 0.3mm, and the influence of the distortion of the impeller on the radial clearance between the blade and the inner wall of the air guide cylinder is prevented.
The design of the lubricating oil cooling fan impeller can improve the safety margin of a product, avoid the risk of fatigue fracture of the product due to the action of vibration load in the service life, ensure the use reliability of the product and ensure the normal work of a lubricating oil system.
The invention provides a lubricating oil cooling fan for an unmanned helicopter, which adopts an impeller-level plate-type twisted blade structure to reduce the nonuniformity of a flow field in a blade passage and reduce the flow loss among flow passages. The efficiency of the lubricating oil cooling fan is improved, and the normal work of a lubricating oil system can be guaranteed.
Claims (8)
1. A lubricant cooling fan for an unmanned helicopter, said lubricant cooling fan comprising: the air inlet net comprises a plurality of screws (1), a plurality of bushings (2), an air inlet net component (3), an air guide barrel component (4), a hoop (5), a transition cover (6), a transition air duct (7) and an impeller (8);
the air inlet net assembly (3) is fixed at the front end of the air guide barrel assembly (4) through a plurality of screws (1) and a plurality of bushings (2), the transition air duct (7) is fixed at the rear end of the air guide barrel assembly (4) through a hoop (5) and a transition cover (6), and the impeller (8) is arranged inside the air guide barrel assembly 4;
the blades on the impeller (8) are distributed at unequal intervals.
2. A lubricant cooling fan for an unmanned helicopter according to claim 1, characterized in that each blade on the impeller (8) adopts a plate type twisted structure.
3. The oil cooling fan for unmanned helicopters according to claim 1, characterized in that the allowable unbalance amount of the impeller (8) is less than a preset value.
4. The lubricant cooling fan for an unmanned helicopter of claim 3, wherein when the dynamic balance accuracy of the impeller is controlled in class G5.6, said predetermined value is designed to be 0.0995g.cm, g.cm representing g.cm.
5. A lubricant cooling fan for an unmanned helicopter according to claim 1, characterized in that n adjacent blades on the impeller (8) are taken as a set of blades, and the distance between the first set of blades and the second set of blades is 50mm to 55 mm; the distance between adjacent blades in a certain group of blades is about 35 mm-38 mm; the first group of blades and the second group of blades are any group of blades.
6. A lubricant cooling fan for unmanned helicopters according to claim 1, characterized in that the transition hood (6) is a flexible device.
7. A lubricant cooling fan for an unmanned helicopter according to claim 1, characterized in that a plurality of screws (1) connect the lubricant cooling fan with the final drive housing.
8. The oil cooling fan for an unmanned helicopter of claim 5 wherein the clearance between the outer edges of the blades and the inner wall of the air guide barrel assembly is 3mm and the cylindricity of the inner wall of the air guide barrel assembly is not more than 0.3 mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011028748.4A CN112196813A (en) | 2020-09-25 | 2020-09-25 | Lubricating oil cooling fan for unmanned helicopter |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011028748.4A CN112196813A (en) | 2020-09-25 | 2020-09-25 | Lubricating oil cooling fan for unmanned helicopter |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN112196813A true CN112196813A (en) | 2021-01-08 |
Family
ID=74006974
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202011028748.4A Pending CN112196813A (en) | 2020-09-25 | 2020-09-25 | Lubricating oil cooling fan for unmanned helicopter |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN112196813A (en) |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| KR20130074511A (en) * | 2011-12-26 | 2013-07-04 | 엘지전자 주식회사 | An axial fan and outdoor unit of air conditioner having the same |
| CN104421986A (en) * | 2013-08-26 | 2015-03-18 | 广东美的厨房电器制造有限公司 | Range hood |
| CN105782090A (en) * | 2016-04-26 | 2016-07-20 | 浙江理工大学 | Noise-lowering and vortex-reducing axial flow fan |
| CN106468289A (en) * | 2016-06-28 | 2017-03-01 | 徐工集团工程机械有限公司 | Wind scooper, electromotor and engineering truck |
| EP3306101A1 (en) * | 2016-10-07 | 2018-04-11 | Anthony Wood | High efficiency fan |
| CN210949262U (en) * | 2019-07-15 | 2020-07-07 | 浙江上风高科专风实业股份有限公司 | Novel plate type axial flow fan impeller |
-
2020
- 2020-09-25 CN CN202011028748.4A patent/CN112196813A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| KR20130074511A (en) * | 2011-12-26 | 2013-07-04 | 엘지전자 주식회사 | An axial fan and outdoor unit of air conditioner having the same |
| CN104421986A (en) * | 2013-08-26 | 2015-03-18 | 广东美的厨房电器制造有限公司 | Range hood |
| CN105782090A (en) * | 2016-04-26 | 2016-07-20 | 浙江理工大学 | Noise-lowering and vortex-reducing axial flow fan |
| CN106468289A (en) * | 2016-06-28 | 2017-03-01 | 徐工集团工程机械有限公司 | Wind scooper, electromotor and engineering truck |
| EP3306101A1 (en) * | 2016-10-07 | 2018-04-11 | Anthony Wood | High efficiency fan |
| CN210949262U (en) * | 2019-07-15 | 2020-07-07 | 浙江上风高科专风实业股份有限公司 | Novel plate type axial flow fan impeller |
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| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20210108 |
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| RJ01 | Rejection of invention patent application after publication |