CN213510887U - Lubricating oil radiator of aircraft engine - Google Patents
Lubricating oil radiator of aircraft engine Download PDFInfo
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- CN213510887U CN213510887U CN202022474844.3U CN202022474844U CN213510887U CN 213510887 U CN213510887 U CN 213510887U CN 202022474844 U CN202022474844 U CN 202022474844U CN 213510887 U CN213510887 U CN 213510887U
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- heat dissipation
- fixedly connected
- radiating
- cavity
- filter screen
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Abstract
The utility model discloses a lubricating oil radiator of an aircraft engine, which comprises a shell, a first radiating cavity, a first radiating fin, a lubricating oil pipe, a first filter screen, an input joint, an annular pipe, an output joint, a second radiating cavity, a second filter screen, a intercommunicating pore and the like; the first filter screen and the second filter screen which are arranged in the utility model can ensure that dust and sundries can not enter the first heat dissipation cavity and the second heat dissipation cavity, thereby ensuring the long-time heat dissipation effect of the first heat dissipation fin and the second heat dissipation fin; the motor is a positive and negative rotation motor and the fan blades are positive and negative rotation fan blades, so that the flow direction of air in the first heat dissipation cavity and the second heat dissipation cavity can be controlled as required, and the blockage of the first filter screen or the second filter screen caused by the fixed flow direction of the air is avoided; the utility model discloses in with during cooling water passes through water supply connector transport ring pipe, then the cooling water then sprays the heat dissipation chamber through the shower nozzle to radiating effect of improvement that can be quick has just also satisfied aeroengine high strength work's needs.
Description
Technical Field
The utility model relates to an aeroengine field, specific lubricating oil radiator of aeroengine that says so.
Background
The basic function of an aircraft engine lubricating oil system is to continuously supply lubricating oil to engine bearings and gears to reduce friction and wear of the moving mating surfaces, prevent them from corrosion and surface hardening, and remove heat generated by friction and heat transferred to the lubricating oil by high temperature parts. The lubricating oil system of modern advanced aircraft engine mostly adopts closed circulation system, and the system mainly contains the lubricating oil tank of storing lubricating oil, the lubricating oil pump that provides power, uses the radiator and the lubricating oil filter equipment of fuel cooling lubricating oil (or other lubricating oil cooling methods), and the continuous cyclic utilization of lubricating oil in the system, and the lubricating oil radiator function of current aircraft engine is fairly simple to the effect that the lubricating oil lasts the heat dissipation has been influenced.
SUMMERY OF THE UTILITY MODEL
To the above-mentioned weak point that exists among the prior art, the utility model aims at providing an aeroengine's lubricating oil radiator has solved current aeroengine's lubricating oil radiator function fairly simple to influenced the problem that the lubricating oil lasts the radiating effect.
The utility model discloses a realize that the technical scheme that above-mentioned purpose adopted is: the lubricating oil radiator of the aircraft engine is characterized by comprising a shell, a first radiating cavity, a first radiating fin, a lubricating oil pipe, a first filter screen, an input joint, an annular pipe, a spray head, a water inlet joint, a protective cover, a motor, fan blades, a transmission shaft, a driving gear, a driven gear, a connecting shaft, a second radiating fin, an output joint, a second radiating cavity, a second filter screen and a communicating hole; a first heat dissipation cavity is formed in the left side of the shell, and a second heat dissipation cavity is formed in the right side of the shell; a first filter screen is fixedly connected in the opening at the left side of the first heat dissipation cavity, and the right side of the first heat dissipation cavity is communicated with the left side of the second heat dissipation cavity through a plurality of communicating holes; a second filter screen is fixedly connected in the opening at the right side of the second heat dissipation cavity; the radiating fins I are vertically arranged and fixedly connected to the inner side of the radiating cavity; the plurality of second radiating fins are vertically arranged and fixedly connected to the inner side of the second radiating cavity; the left side of the lubricating oil pipe is fixedly connected in the first radiating fin in a snake shape, the right side of the lubricating oil pipe is fixedly connected in the second radiating fin in a snake shape, an input connector is arranged at an inlet on the left upper side of the lubricating oil pipe and is fixedly connected to the outer portion of the left upper side of the shell, an output connector is arranged at an outlet on the right upper side of the lubricating oil pipe and is fixedly connected to the outer portion of the right upper side of the shell; the motor is fixedly connected to the center of the outer part of the upper side of the shell, and a protective cover is fixedly connected to the outer part of the motor; the transmission shaft is movably connected in a vertical hole arranged at the upper side of the center of the shell, the shaft end at the upper side of the transmission shaft is fixedly connected with an output shaft at the lower side of the motor, and the shaft end at the lower side of the transmission shaft is fixedly connected with the center of the driving gear; the connecting shaft is movably connected in a transverse hole arranged in the center of the shell, fan blades are fixedly connected to the end parts of the left side and the right side of the connecting shaft, a driven gear is fixedly connected to the right side outside the connecting shaft, and the driven gear is connected with the driving gear; the annular pipe is two, two annular pipe fixed connection is in two left sides in heat dissipation chamber one right sides and heat dissipation chamber respectively, the annular pipe inboard evenly is equipped with a plurality of shower nozzle, annular pipe upside entrance all is equipped with water supply connector, and the equal fixed connection of water supply connector upside is outside at the casing upside.
Preferably, an opening of a left side of the heat dissipation cavity is in a bell mouth shape.
Preferably, the opening on the right side of the second heat dissipation cavity is in a bell mouth shape.
Preferably, the fan blades are forward and reverse rotating fan blades.
Preferably, the motor is a forward and reverse rotation motor.
The utility model has the advantages that:
(1) the utility model discloses in the filter screen one and the filter screen two that set up, can ensure that dust debris can not enter into heat dissipation chamber one and heat dissipation chamber two to the long-time radiating effect of fin one and fin two has been ensured.
(2) The utility model discloses well motor is just reversing motor and flabellum is just reversing the flabellum to can control the flow direction of air in heat dissipation chamber one and heat dissipation chamber two as required, just also avoided because the fixed jam that causes filter screen one or filter screen two of air current to.
(3) The utility model discloses in with during cooling water passes through water supply connector transport ring pipe, then the cooling water then sprays the heat dissipation chamber through the shower nozzle to radiating effect of improvement that can be quick has just also satisfied aeroengine high strength work's needs.
Drawings
Fig. 1 is a schematic structural view of the present invention;
fig. 2 is a partial enlarged view of the present invention.
In the figure: 1-a shell; 2-a first heat dissipation cavity; 3-a first heat sink; 4-a slide oil pipe; 5, a first filter screen; 6-input joint; 7-a ring-shaped pipe; 8-a spray head; 9-water inlet joint; 10-a protective cover; 11-a motor; 12-fan blades; 13-a drive shaft; 14-a drive gear; 15-a driven gear; 16-a connecting shaft; 17-a second heat sink; 18-an output connector; 19-a second heat dissipation cavity; 20-filter screen II; 21-communicating hole.
Detailed Description
The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments.
As shown in fig. 1-2, a lubricating oil radiator of an aircraft engine comprises a shell 1, a first heat dissipation cavity 2, a first heat dissipation fin 3, a lubricating oil pipe 4, a first filter screen 5, an input joint 6, an annular pipe 7, a spray head 8, a water inlet joint 9, a protective cover 10, a motor 11, fan blades 12, a transmission shaft 13, a driving gear 14, a driven gear 15, a connecting shaft 16, a second heat dissipation fin 17, an output joint 18, a second heat dissipation cavity 19, a second filter screen 20 and a communication hole 21; a first heat dissipation cavity 2 is formed in the left side of the shell 1, and a second heat dissipation cavity 19 is formed in the right side of the shell 1; a first filter screen 5 is fixedly connected in an opening at the left side of the first heat dissipation cavity 2, and the right side of the first heat dissipation cavity 2 is communicated with the left side of a second heat dissipation cavity 19 through a plurality of communicating holes 21; a second filter screen 20 is fixedly connected in the opening at the right side of the second heat dissipation cavity 19; the number of the radiating fins I3 is multiple, and the radiating fins I3 are vertically arranged and fixedly connected to the inner side of the radiating cavity I2; the number of the second cooling fins 17 is multiple, and the second cooling fins 17 are vertically arranged and fixedly connected to the inner side of the second cooling cavity 19; the left side of the oil sliding pipe 4 is fixedly connected in the first radiating fin 3 in a snake shape, the right side of the oil sliding pipe 4 is fixedly connected in the second radiating fin 17 in a snake shape, an input connector 6 is arranged at an inlet at the left upper side of the oil sliding pipe 4, the input connector 6 is fixedly connected to the outer portion of the left upper side of the shell 1, an output connector 18 is arranged at an outlet at the right upper side of the oil sliding pipe 4, and the output connector 18 is fixedly connected to the outer portion of the right upper side of; the motor 11 is fixedly connected to the center of the outer part of the upper side of the shell 1, and the outer part of the motor 11 is fixedly connected with a protective cover 10; the transmission shaft 13 is movably connected in a vertical hole arranged at the upper side of the center of the shell 1, the shaft end at the upper side of the transmission shaft 13 is fixedly connected with the output shaft at the lower side of the motor 11, and the shaft end at the lower side of the transmission shaft 13 is fixedly connected with the center of the driving gear 14; the connecting shaft 16 is movably connected in a transverse hole formed in the center of the shell 1, fan blades 12 are fixedly connected to the end portions of the left side and the right side of the connecting shaft 16, a driven gear 15 is fixedly connected to the right side of the outer portion of the connecting shaft 16, and the driven gear 15 is connected with a driving gear 14; annular pipe 7 is two, two annular pipe 7 fixed connection is in heat dissipation chamber 2 right sides and two 19 left sides in heat dissipation chamber respectively, 7 inboard sides of annular pipe evenly are equipped with a plurality of shower nozzle 8, 7 upside entrances of annular pipe all are equipped with water supply connector 9, and the equal fixed connection of water supply connector 9 upside is outside at 1 upside of casing.
The opening on the left side of the first heat dissipation cavity 2 is in a bell mouth shape; the opening on the right side of the second heat dissipation cavity 19 is in a horn mouth shape; the fan blades 12 are forward and reverse rotating fan blades; the motor 11 is a forward and reverse rotating motor.
The utility model has the use state that, when in use, firstly, the starting motor 11 drives the driving gear 14 to rotate through the transmission shaft 13, the driving gear 14 rotates through the driven gear 15 and the connecting shaft 16 to drive the fan blade 12 to rotate, the fan blade 12 rotates to enable the external air to flow in the first radiating fin 3 and the second radiating fin 17 for radiating, thereby effectively radiating the lubricating oil flowing in the lubricating oil pipe 4, and improving the radiating effect, in addition, the first filtering net 5 and the second filtering net 20 are arranged to ensure that the dust sundries can not enter the first radiating cavity 2 and the second radiating cavity 19, thereby ensuring the long-time radiating effect of the first radiating fin 3 and the second radiating fin 17, in addition, the motor 11 is a positive and negative rotating motor and the fan blade 12 is a positive and negative rotating fan blade, thereby controlling the flow direction of the air in the first radiating cavity 2 and the second radiating cavity 19 according to requirements, the blockage of the first filter screen 5 or the second filter screen 20 caused by the fixed air flow direction is avoided, cooling water is conveyed into the annular pipe 7 through the water inlet joint 9, and then the cooling water is sprayed into the heat dissipation cavity through the spray head 8, so that the heat dissipation effect can be quickly improved, and the requirement of high-strength work of an aero-engine is met.
The control mode of the present invention is controlled by manual starting or by the existing automation technology, the connection diagram of the power element and the supply of the power source belong to the common knowledge in the field, and the present invention is mainly used for protecting the mechanical device, so the present invention does not explain the control mode and the wiring arrangement in detail.
In the description of the present invention, it is to be understood that the terms "coaxial", "bottom", "one end", "top", "middle", "other end", "upper", "one side", "top", "inner", "front", "center", "both ends", and the like, indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience of description and simplicity of description, and do not indicate or imply that the device or element referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore, should not be construed as limiting the present invention.
In the present invention, unless otherwise expressly stated or limited, the terms "mounted," "disposed," "connected," "fixed," "screwed" and the like are to be construed broadly, e.g., as meaning fixedly connected, detachably connected, or integrally formed; can be mechanically or electrically connected; they may be directly connected or indirectly connected through an intermediate medium, and may be connected through the inside of two elements or in an interaction relationship between two elements, unless otherwise specifically defined, and the specific meaning of the above terms in the present invention will be understood by those skilled in the art according to specific situations.
The basic principles and main features of the present invention and the advantages of the present invention have been shown and described above, and it should be understood by those skilled in the art that the present invention is not limited by the above embodiments, which are only illustrative, but also various changes and modifications may be made without departing from the spirit and scope of the present invention, which fall within the scope of the present invention as claimed, which is defined by the appended claims and their equivalents.
Claims (5)
1. The lubricating oil radiator of the aircraft engine is characterized by comprising a shell (1), a first radiating cavity (2), a first radiating fin (3), a lubricating oil pipe (4), a first filter screen (5), an input joint (6), an annular pipe (7), a sprayer (8), a water inlet joint (9), a protective cover (10), a motor (11), fan blades (12), a transmission shaft (13), a driving gear (14), a driven gear (15), a connecting shaft (16), a second radiating fin (17), an output joint (18), a second radiating cavity (19), a second filter screen (20) and a communicating hole (21);
a first heat dissipation cavity (2) is arranged inside the left side of the shell (1), and a second heat dissipation cavity (19) is arranged inside the right side of the shell (1);
a first filter screen (5) is fixedly connected in an opening at the left side of the first heat dissipation cavity (2), and the right side of the first heat dissipation cavity (2) is communicated with the left side of the second heat dissipation cavity (19) through a plurality of communicating holes (21);
a second filter screen (20) is fixedly connected in the opening at the right side of the second heat dissipation cavity (19);
the number of the first radiating fins (3) is multiple, and the plurality of the first radiating fins (3) are vertically arranged and fixedly connected to the inner side of the first radiating cavity (2);
the number of the second radiating fins (17) is multiple, and the second radiating fins (17) are vertically arranged and fixedly connected to the inner side of the second radiating cavity (19);
the left side of the oil sliding pipe (4) is fixedly connected in the first radiating fin (3) in a snake shape, the right side of the oil sliding pipe (4) is fixedly connected in the second radiating fin (17) in a snake shape, an input connector (6) is arranged at an inlet at the upper left side of the oil sliding pipe (4), the input connector (6) is fixedly connected to the outer portion of the upper left side of the shell (1), an output connector (18) is arranged at an outlet at the upper right side of the oil sliding pipe (4), and the output connector (18) is fixedly connected to the outer portion of the upper right side of the shell (;
the motor (11) is fixedly connected to the center of the outer side of the upper side of the shell (1), and the outer part of the motor (11) is fixedly connected with a protective cover (10);
the transmission shaft (13) is movably connected in a vertical hole formed in the upper side of the center of the shell (1), the shaft end of the upper side of the transmission shaft (13) is fixedly connected with an output shaft of the lower side of the motor (11), and the shaft end of the lower side of the transmission shaft (13) is fixedly connected with the center of the driving gear (14);
the fan blade type fan is characterized in that the connecting shaft (16) is movably connected in a transverse hole formed in the center of the shell (1), fan blades (12) are fixedly connected to the end portions of the left side and the right side of the connecting shaft (16), a driven gear (15) is fixedly connected to the right side of the outer portion of the connecting shaft (16), and the driven gear (15) is connected with the driving gear (14);
annular pipe (7) are two, two annular pipe (7) fixed connection is in heat dissipation chamber (2) right side and heat dissipation chamber two (19) left sides respectively, annular pipe (7) inboard evenly is equipped with a plurality of shower nozzle (8), annular pipe (7) upside entrance all is equipped with water supply connector (9), and the equal fixed connection of water supply connector (9) upside is outside at casing (1).
2. The lubricating oil radiator of an aircraft engine as claimed in claim 1, wherein the left opening of the first radiating cavity (2) is in the shape of a bell mouth.
3. The lubricating oil radiator of an aircraft engine as claimed in claim 1, wherein the right opening of the second heat dissipation cavity (19) is in a bell mouth shape.
4. The lubricating oil radiator of an aircraft engine according to claim 1, characterized in that the fan blades (12) are counter-rotating fan blades.
5. The lubricating oil radiator of an aircraft engine according to claim 1, characterized in that the electric machine (11) is a counter-rotating electric machine.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202022474844.3U CN213510887U (en) | 2020-10-31 | 2020-10-31 | Lubricating oil radiator of aircraft engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202022474844.3U CN213510887U (en) | 2020-10-31 | 2020-10-31 | Lubricating oil radiator of aircraft engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN213510887U true CN213510887U (en) | 2021-06-22 |
Family
ID=76414017
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202022474844.3U Active CN213510887U (en) | 2020-10-31 | 2020-10-31 | Lubricating oil radiator of aircraft engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN213510887U (en) |
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2020
- 2020-10-31 CN CN202022474844.3U patent/CN213510887U/en active Active
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