CN207554198U - A kind of oil cooler - Google Patents
A kind of oil cooler Download PDFInfo
- Publication number
- CN207554198U CN207554198U CN201721439625.3U CN201721439625U CN207554198U CN 207554198 U CN207554198 U CN 207554198U CN 201721439625 U CN201721439625 U CN 201721439625U CN 207554198 U CN207554198 U CN 207554198U
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- connector
- radiator
- pedestal
- oil cooler
- connecting hole
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Abstract
The utility model discloses a kind of oil cooler, before being installed on aircraft engine turbofan, for the heat dissipation of aircraft engine lubricating oil, including multiple radiator subelements；The radiator subelement includes upper cover and pedestal；The upper cover includes cover board and fin group；The pedestal is equipped with inner flow passage；The two side in the pedestal along arc length direction is Mosaic face, and the first connecting hole and the second connecting hole are offered, and be installed with the first connector and the second connector on the Mosaic face；First connector and the second connector splice each radiator subelement, each radiator subelement inner flow passage is interconnected by first connector, lubricating oil is flowed by the first connector of radiator subelement originated, is flowed out after flowing through inner flow passage by the first connector of end radiator subelement.The utility model is linked into an integrated entity by several radiator subelements, and incoming air is made full use of to carry out the cooling of lubricating oil, has many advantages, such as that big heat dissipation capacity, small, simple structure, space availability ratio are high.
Description
Technical field
The utility model is related to a kind of oil coolers.
Background technology
Radiator is widely used in the engineerings field of radiating such as aerospace.Fortune of the design of radiator concerning engineering machinery
Row stability and service life.Therefore the innovative design of radiator is the key point for improving heat dissipation performance.
When aircraft is near the ground slide, engine system will generate huge heat.In order to ensure that aircraft system is run
Stability and dependability, it is necessary to timely to engine system radiating and cooling.Lubricating system can be by aircraft gear-box and each axis
The heat of the heat held is timely taken away, and reduces the running temperature of oil system, usually using usual heat exchanger.It is existing to dissipate
Hot device heat-sinking capability in aircraft low speed slide near the ground is insufficient, and conventional diffusers, which exist, often induces incoming air turbulent flow, mistake
The problems such as big air-pressure drop, and traditional heat exchange radiator is installed on inside aircraft engine, it usually needs specific peace
Fill space, while connect it is long and complex into fuel-displaced header tube road, some for increase cooling effect also add refrigerant pipe, drop significantly
Low spatial utilization rate, design thus it is a can make full use of incoming air, fully the limited space of profit very it is necessary to.
Utility model content
The purpose of the utility model is to overcome usual heat exchanger air in the prior art, space utilization is insufficient, radiates
The shortcomings such as ability is low, provide a kind of oil cooler, solve the problems in above-mentioned background technology.
Technical solution is used by the utility model solves its technical problem：A kind of oil cooler, is installed on aircraft
Before engine turbofan, for the heat dissipation of aircraft engine lubricating oil, including multiple radiator subelements；
The radiator subelement includes upper cover and pedestal；
The upper cover includes cover board and fin group, and the cover board is arc panel, and the fin group is set to cover board towards circle
The side of the heart, and including multiple fins, the fin is alternatively arranged perpendicular to cover board upper surface and along cover board arc length direction, described
Two neighboring fin between form air duct；
The pedestal is the arc-shaped base being adapted with cover board shape, and the base upper surface is fitted closely with cover board；Institute
Pedestal is stated equipped with inner flow passage；The two side in the pedestal along arc length direction is joint face, and the first company is offered on the joint face
Hole and the second connecting hole are connect, first connecting hole is connected with inner flow passage, and is installed with the first connector, first connector
For hollow structure；Second connecting hole is installed with the second connector；First connector and the second connector are by each heat dissipation
Device subelement splices, and each radiator subelement inner flow passage is interconnected by first connector, and lubricating oil is by the radiator that originates
First connector of subelement flows into, and is flowed out after flowing through inner flow passage by the first connector of end radiator subelement.
A kind of oil cooler in one preferred embodiment of the utility model is by multiple radiator subelements along arc
Length direction is spliced to form.The crooked radian of the cover board and pedestal is adapted with aircraft engine turbofan radian.
In one preferred embodiment of the utility model, the inner flow passage is opened in base upper surface.
In one preferred embodiment of the utility model, first connecting hole and the second connecting hole are stepped hole.
In one preferred embodiment of the utility model, first connector be hollow connection plug, the hollow connection plug
It is formed by a hollow cylinder and in the middle part of cylinder and along the coaxial circumferentially disposed boss of cylinder, the hollow connection plug
Shape is adapted with stepped hole.
In one preferred embodiment of the utility model, second connector be solid connection plug, the solid connection plug
It is formed by a solid cylinder and in the middle part of cylinder and along the coaxial circumferentially disposed boss of cylinder, the solid connection plug
Shape is adapted with stepped hole.
In one preferred embodiment of the utility model, there are two joint face, two the first connecting holes and two for the pedestal tool
A second connecting hole, two the first connecting holes are divided on two joint faces and are distributed in diagonal, two second connections
Hole is divided on two joint faces and is distributed in diagonal.
In one preferred embodiment of the utility model, the inner flow passage, which is diagonally bent, is set to pedestal upper table
Face, entrance are the first connecting hole of side joint face, export the first connecting hole for opposite side joint face.
In one preferred embodiment of the utility model, the upper cover passes through soldering connection with pedestal.
Compared with background technology, it has the following advantages that the technical program：
1. the radiator subelement of multiple arcs be spliced into radiator entirety, be conducive to adjust heat sink size, radian with
The adaptation degree of engine turbofan has good suitability.
2. before being installed on aircraft engine turbofan, making full use of incoming air, nature refrigerant is formed, heat dissipation capacity is big, convenient
And save the energy.
3. simple structure, manufacture, dismounting, repair are easy, can be mass, are not take up sky limited in a large amount of aircraft components
Between, utilization rate is high.
Description of the drawings
Fig. 1 is the utility model radiator sub-unit structure schematic diagram.
Fig. 2 is the utility model radiator subelement explosive view.
Fig. 3 is the utility model radiator subelement connecting method schematic diagram.
Specific embodiment
The content of the utility model is illustrated with reference to the accompanying drawings and examples：
Please refer to Fig. 1-3, a kind of oil cooler of the present embodiment, before being installed on aircraft engine turbofan, for aircraft
The heat dissipation of motor oil, including multiple radiator subelements 1；
The radiator subelement 1 includes upper cover 2 and pedestal 3；
The upper cover 2 includes cover board 21 and fin group, and the cover board 21 is arc panel, and the fin group is set to cover board 21
Towards the side in the center of circle, and including multiple fins 23, the fin 23 is perpendicular to cover board upper surface and along between cover board arc length direction
Air duct is formed between arrangement, the two neighboring fin 23；For aircraft near the ground slide, outside air flows through air duct shape
Into natural refrigerant, for cooling lubricating oil.
The pedestal 3 is the arc-shaped base 3 being adapted with 21 shape of cover board, and 3 upper surface of pedestal is close with cover board 21
Fitting；The pedestal 3 is equipped with inner flow passage 31；For the inner flow passage 31 of lubricating oil flowing to offer 3 upper table of pedestal in the present embodiment
Face and the gully of bending arrangement, cover board 21 are closely connect with 3 upper surface of pedestal by soldering, and cover board 21 is covered on above gully will
It is closed as inner flow passage 31.
The two side in the pedestal 3 along arc length direction is Mosaic face, and 35 He of the first connecting hole is offered on the Mosaic face
Second connecting hole 37,35 and second connecting hole 37 of the first connecting hole is stepped hole；First connecting hole 35 and interior stream
Road 31 connects, and is installed with the first connector 5, and first connector 5 is the multi-diameter shaft with hollow structure；Described second connects
It connects hole 37 and is installed with the second connector 7, second connector 7 is multi-diameter shaft；
The hollow connection plug that first connector 5 is adapted for shape with the first connecting hole 35, the hollow connection plug
It is formed by a hollow cylinder and in the middle part of cylinder and along the coaxial circumferentially disposed boss of cylinder.Second connector
The 7 solid connection plugs being adapted for shape with the second connecting hole 37, the solid connection plug is by a solid cylinder and positioned at circle
It is formed in the middle part of cylinder and along the coaxial circumferentially disposed boss of cylinder.The convex edge of table forms the shaft shoulder, corresponding with stepped hole
The mutual contact in position.
First connector, 5 and second connector 7 splices each radiator subelement 1, and first connector 5 will be each
1 inner flow passage 31 of radiator subelement, which is interconnected, concatenates internal lubricating oil, and lubricating oil is connected by originate the first of radiator subelement 1
Fitting 5 flows into, and is flowed out after flowing through inner flow passage 31 by the first connector 5 of end radiator subelement 1.
Utmostly to utilize space in pedestal 3, increasing lubricating oil flow path, there are two Mosaic face, two for the tool of pedestal 3
A first connecting hole 35 and two the second connecting holes 37, two the first connecting holes 35 are divided on two Mosaic faces and in diagonal
Directional spreding, two the second connecting holes 37 are divided on two Mosaic faces and are distributed in diagonal.31 edge of inner flow passage
Diagonal bending is set to 3 upper surface of pedestal, and entrance is the first connecting hole 35 of side Mosaic face, is exported as opposite side
First connecting hole 35 of Mosaic face.
Fig. 3 is please referred to, the radiator of the present embodiment is whole to splice shape by multiple radiator subelements 1 along arc length direction
Into the crooked radian of the cover board 21 and pedestal 3 is adapted with aircraft engine turbofan radian, can be mass, and is installed, dimension
It repaiies conveniently, adaptation degree is high.
The above, only the utility model preferred embodiment, therefore the utility model implementation cannot be limited according to this
It is new all should still to belong to this practicality for range, i.e., the equivalent changes and modifications made according to the utility model patent range and description
In the range of type covers.
Claims (10)
1. a kind of oil cooler, before being installed on aircraft engine turbofan, for the heat dissipation of aircraft engine lubricating oil, feature exists
In：Including multiple radiator subelements；
The radiator subelement includes upper cover and pedestal；
The upper cover includes cover board and fin group, and the cover board is arc panel, and the fin group is set to cover board towards the center of circle
Side, and including multiple fins, the fin is alternatively arranged perpendicular to cover board upper surface and along cover board arc length direction, two neighboring
Air duct is formed between the fin；
The pedestal is the arc-shaped base being adapted with cover board shape, and the base upper surface is fitted closely with cover board；The bottom
Seat is equipped with inner flow passage；The two side in the pedestal along arc length direction is joint face, and the first connecting hole is offered on the joint face
With the second connecting hole, first connecting hole is connected with inner flow passage, and is installed with the first connector, during first connector is
Hollow structure；Second connecting hole is installed with the second connector；First connector and the second connector are sub by each radiator
Each radiator subelement inner flow passage is interconnected by unit spliced, first connector, and lubricating oil is single by radiator originated
First connector of member flows into, and is flowed out after flowing through inner flow passage by the first connector of end radiator subelement.
2. a kind of oil cooler according to claim 1, it is characterised in that：The crooked radian of the cover board and pedestal with
Aircraft engine turbofan radian is adapted.
3. a kind of oil cooler according to claim 1, it is characterised in that：By multiple radiator subelements along arc
Length direction is spliced to form.
4. a kind of oil cooler according to claim 1, it is characterised in that：The inner flow passage is opened in pedestal upper table
Face.
5. a kind of oil cooler according to claim 1, it is characterised in that：First connecting hole and the second connecting hole
It is stepped hole.
6. a kind of oil cooler according to claim 5, it is characterised in that：First connector is hollow connection
Plug, the hollow connection plug is by a hollow cylinder and in the middle part of the cylinder and along the coaxial circumferentially disposed boss group of cylinder
Into the hollow connection plug shape is adapted with stepped hole.
7. a kind of oil cooler according to claim 6, it is characterised in that：Second connector is solid connection
Plug, the solid connection plug is by a solid cylinder and in the middle part of the cylinder and along the coaxial circumferentially disposed boss group of cylinder
Into the solid connection plug shape is adapted with stepped hole.
8. a kind of oil cooler according to claim 7, it is characterised in that：There are two joint face, two for the pedestal tool
A first connecting hole and two the second connecting holes, two the first connecting holes are divided on two joint faces and in diagonals point
Cloth, two the second connecting holes are divided on two joint faces and are distributed in diagonal.
9. a kind of oil cooler according to claim 8, it is characterised in that：The inner flow passage is diagonally bent
Base upper surface is set to, entrance is the first connecting hole of side joint face, exports the first connection for opposite side joint face
Hole.
10. a kind of oil cooler according to claim 1, it is characterised in that：The upper cover passes through the company of soldering with pedestal
It connects.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721439625.3U CN207554198U (en) | 2017-11-01 | 2017-11-01 | A kind of oil cooler |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721439625.3U CN207554198U (en) | 2017-11-01 | 2017-11-01 | A kind of oil cooler |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN207554198U true CN207554198U (en) | 2018-06-29 |
Family
ID=62681595
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201721439625.3U Active CN207554198U (en) | 2017-11-01 | 2017-11-01 | A kind of oil cooler |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN207554198U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107859564A (en) * | 2017-11-01 | 2018-03-30 | 厦门大学 | A kind of oil cooler being installed on before aircraft engine turbofan |
-
2017
- 2017-11-01 CN CN201721439625.3U patent/CN207554198U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107859564A (en) * | 2017-11-01 | 2018-03-30 | 厦门大学 | A kind of oil cooler being installed on before aircraft engine turbofan |
| CN107859564B (en) * | 2017-11-01 | 2024-04-09 | 厦门大学 | Lubricating oil radiator mounted in front of turbofan of aircraft engine |
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