CN119429130A - A propeller aircraft lubricating oil cooling system and cooling method - Google Patents
A propeller aircraft lubricating oil cooling system and cooling method Download PDFInfo
- Publication number
- CN119429130A CN119429130A CN202310938380.2A CN202310938380A CN119429130A CN 119429130 A CN119429130 A CN 119429130A CN 202310938380 A CN202310938380 A CN 202310938380A CN 119429130 A CN119429130 A CN 119429130A
- Authority
- CN
- China
- Prior art keywords
- lubricating oil
- oil
- generator
- engine
- radiator
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- Pending
Links
- 238000001816 cooling Methods 0.000 title claims abstract description 52
- 239000010687 lubricating oil Substances 0.000 title abstract description 171
- 239000003921 oil Substances 0.000 claims 32
- 239000010705 motor oil Substances 0.000 claims 13
- 230000017525 heat dissipation Effects 0.000 abstract description 26
- 238000000034 method Methods 0.000 abstract description 6
- 238000010586 diagram Methods 0.000 description 5
- 210000001015 abdomen Anatomy 0.000 description 2
- 238000007599 discharging Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000004519 grease Substances 0.000 description 1
- 230000010354 integration Effects 0.000 description 1
- 238000002955 isolation Methods 0.000 description 1
- 230000001050 lubricating effect Effects 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
- 239000013585 weight reducing agent Substances 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D33/00—Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for
- B64D33/08—Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of power plant cooling systems
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Lubrication Of Internal Combustion Engines (AREA)
Abstract
一种螺旋桨飞机滑油散热系统及散热方法，将发动机滑油散热器和发电机滑油散热器集成为一个集成滑油散热器，该集成滑油散热器位于进气道和排气道之间，形成滑油散热系统，该滑油散热系统安装在飞机短舱下部，使进气道、集成滑油散热器和排气道形成一个空气流通通道；将飞机发电机滑油冷却管路的两端分别与集成滑油散热器的发电机滑油入口接头和发电机滑油出口接头连接；将飞机发动机滑油冷却管路的两端分别与集成滑油散热器的发动机滑油入口接头和发动机滑油出口接头连接。
A propeller aircraft lubricating oil cooling system and a heat dissipation method, wherein an engine lubricating oil radiator and a generator lubricating oil radiator are integrated into an integrated lubricating oil radiator, the integrated lubricating oil radiator is located between an air inlet and an exhaust duct to form an lubricating oil cooling system, the lubricating oil cooling system is installed at the lower part of the aircraft nacelle, so that the air inlet, the integrated lubricating oil radiator and the exhaust duct form an air circulation channel; the two ends of the aircraft generator lubricating oil cooling pipeline are respectively connected to the generator lubricating oil inlet joint and the generator lubricating oil outlet joint of the integrated lubricating oil radiator; the two ends of the aircraft engine lubricating oil cooling pipeline are respectively connected to the engine lubricating oil inlet joint and the engine lubricating oil outlet joint of the integrated lubricating oil radiator.
Description
Technical Field
The application relates to the technical field of propeller aircraft design, in particular to a lubricating oil heat dissipation system and a heat dissipation method for a propeller aircraft engine and a generator.
Background
Currently more and more aircraft engines and generators tend to be configured with separate lubricating oil systems. For aero-engine and generator, lubricating oil can lubricate and cool the parts such as bearing, gear, etc. and in the process of lubricating the engine and generator, the lubricating oil can take away the heat generated by friction operation of parts such as bearing gear, etc. and can raise the temperature of the lubricating oil, so that lubricating oil heat dissipation systems are needed for the engine and generator.
For a propeller aircraft, an engine and a generator are generally arranged in a short cabin, a matched lubricating oil heat dissipation system of the engine and the generator is also required to be arranged in the short cabin, the space in the short cabin of the aircraft is narrow, the weight requirement is severe, and the design difficulty of the lubricating oil heat dissipation system of the engine and the generator is high. At present, the lubricating oil heat dissipation of engines and generators at home and abroad is generally realized by adopting an air-cooled or oil-cooled lubricating oil heat dissipation mode, and the engines and the generators are provided with independent lubricating oil heat dissipation systems, so that the space occupation is large, the self weight is large, and the design of the appearance and the weight reduction requirements of an airplane are not facilitated.
Disclosure of Invention
In order to solve the problems, the invention provides a lubricating oil heat dissipation system and a heat dissipation method for a propeller plane. The lubricating oil heat dissipation problem of the engine and the alternating current generator is solved, space and weight are saved, and design is optimized.
The utility model provides a screw aircraft lubricating oil cooling system, this lubricating oil cooling system contains engine lubricating oil radiator and generator lubricating oil radiator, its characterized in that, with engine lubricating oil radiator and generator lubricating oil radiator integration into an integrated lubricating oil radiator, this integrated lubricating oil radiator is located between intake duct and the exhaust duct, forms the lubricating oil cooling system, the air inlet and the course of intake duct are unanimous, the gas vent and the course of exhaust duct are opposite, integrated lubricating oil radiator contain the engine lubricating oil cooling core and the engine lubricating oil cooling core of physical isolation, engine lubricating oil cooling core intercommunication has generator lubricating oil inlet connection and generator lubricating oil outlet connection, engine lubricating oil cooling core intercommunication has engine lubricating oil inlet connection and engine lubricating oil outlet connection.
The lubricating oil heat dissipation system of the propeller aircraft is characterized in that the integrated lubricating oil heat radiator comprises a fixed frame, a generator lubricating oil heat dissipation core body and an engine lubricating oil heat dissipation core body are integrated in the fixed frame, a front side frame of the fixed frame is connected with an air inlet channel, and a rear side frame of the fixed frame is connected with an exhaust channel.
The propeller plane lubricating oil heat dissipation system is characterized in that the generator lubricating oil inlet connector and the generator lubricating oil outlet connector are arranged on a connecting plate at one end of the fixed frame and are communicated with the generator lubricating oil heat dissipation core, and the engine lubricating oil inlet connector and the engine lubricating oil outlet connector are arranged on a connecting plate at the other end of the fixed frame and are communicated with the engine lubricating oil heat dissipation core.
A method for cooling the lubricating oil of a propeller aircraft is characterized by comprising the following steps of 1) using the lubricating oil cooling system of the propeller aircraft according to any one of claims 1-3, 2) installing the lubricating oil cooling system at the lower part of a nacelle of the aircraft to enable an air inlet channel, an integrated lubricating oil radiator and an exhaust channel to form an air circulation channel, 3) connecting two ends of a lubricating oil cooling pipeline of a generator of the aircraft with a generator lubricating oil inlet joint and a generator lubricating oil outlet joint of the integrated lubricating oil radiator respectively, 4) connecting two ends of a lubricating oil cooling pipeline of an engine of the aircraft with an engine lubricating oil inlet joint and an engine lubricating oil outlet joint of the integrated lubricating oil radiator respectively, 5) enabling high-speed low-temperature air to flow into the integrated lubricating oil radiator from the air inlet channel when the aircraft flies at high altitude, cooling high-temperature lubricating oil of the engine and the generator and then discharging the lubricating oil from the exhaust channel, 6) enabling air driven by the propeller to enter the integrated lubricating oil radiator from the air inlet channel when the aircraft is stationary on the ground and cooling high-temperature lubricating oil of the engine and the generator and then discharging the lubricating oil from the exhaust channel.
The application has the beneficial effects that 1) the application provides the integrated lubricating oil radiator, so that the engine air lubricating oil radiator and the generator air lubricating oil radiator share the air inlet passage and the air outlet passage, but the engine air lubricating oil radiator and the generator air lubricating oil radiator still have independent lubricating oil flow passages, the lubricating oil radiator and the air inlet passage are arranged on the lower hull of the nacelle, the problem of cooling engine lubricating oil and generator lubricating oil is solved, the space in the nacelle is saved, the weight of an airplane can be reduced, and the appearance design of the nacelle is optimized. 2) When the aircraft is at high speed, external inflow is utilized to enter the air cooling radiator to cool the lubricating oil, and when the aircraft is at low speed and external inflow is insufficient, the propeller inflow is utilized to enter the air cooling lubricating oil radiator to cool the lubricating oil. When the aircraft is at rest on the ground, the propeller slipstream enters the lubricating oil radiator from the air inlet channel, cools the high-temperature lubricating oil of the engine and the generator and then is discharged from the exhaust channel.
The present application is described in further detail below with reference to the accompanying drawings.
Drawings
FIG. 1 is a schematic block diagram of a lubricating oil heat dissipation system of the present application.
Fig. 2 is a schematic diagram of a lubricating oil heat dissipation system according to the present application.
Fig. 3 is a schematic structural diagram of an integrated lubricating oil radiator according to the present application.
FIG. 4 is a schematic diagram of the connection of an integrated lubricating oil radiator to a nacelle of a propeller aircraft of the present application.
FIG. 5 is a schematic diagram of the connection between the grease cooling system of the present application and the nacelle of a propeller aircraft.
The number of the figures shows that the engine comprises an air inlet channel 1, an integrated lubricating oil radiator 2, an air outlet channel 3, an engine lubricating oil cooling core 4, a generator lubricating oil cooling core 5, a fixed frame 6, a connecting hole 7, an engine lubricating oil inlet joint 8, an engine lubricating oil outlet joint 9, an engine lubricating oil bypass valve 10, a generator lubricating oil inlet joint 11, a generator lubricating oil outlet joint 12, a generator lubricating oil bypass valve 13, a connecting plate 14, a nacelle 15 and a propeller aircraft 16.
Detailed Description
Referring to the drawings, the lubricating oil heat dissipation system of the propeller aircraft of the present application is mounted on the lower hull of the belly nacelle 15 of the propeller aircraft 16 as shown in fig. 5. The engine lubricating oil radiator and the generator lubricating oil radiator are integrated into an integrated lubricating oil radiator 2, the integrated lubricating oil radiator 2 is positioned between an air inlet channel 1 and an air outlet channel 3, the air inlet of the air inlet channel 1 is consistent with the aircraft heading, the air outlet of the air outlet channel 3 is opposite to the aircraft heading, the integrated lubricating oil radiator 2 comprises a physically isolated generator lubricating oil radiating core 5 and an engine lubricating oil radiating core 4, the generator lubricating oil radiating core 5 is communicated with a generator lubricating oil inlet joint 11 and a generator lubricating oil outlet joint 12, and the engine lubricating oil radiating core 4 is communicated with an engine lubricating oil inlet joint 8 and an engine lubricating oil outlet joint 9.
In implementation, the integrated lubricating oil radiator 2 integrates the generator lubricating oil radiating core 5 and the engine lubricating oil radiating core 4 together through the fixing frame 6, the front side frame of the fixing frame 6 is connected with the air inlet channel 1 through the connecting hole 7 thereon, and the rear side frame of the fixing frame 6 is connected with the air outlet channel through the connecting hole 7 thereon. The front and rear sides of the fixing frame 6 are an open structure. The generator lubricating oil inlet joint 11, the generator lubricating oil outlet joint 12 and the generator lubricating oil bypass valve 13 are arranged on a connecting plate 13 at one end of the fixed frame 6 and are communicated with the generator lubricating oil heat dissipation core 5, and the engine lubricating oil inlet joint 8, the engine lubricating oil outlet joint 9 and the engine lubricating oil bypass valve 10 are arranged on a connecting plate 13 at the other end of the fixed frame 6 and are communicated with the engine lubricating oil heat dissipation core 4.
The engine lubricating oil cooling system is arranged on the lower hull of an belly nacelle 15 of a propeller aircraft 16, an air circulation channel is formed by the air inlet channel 1, the integrated lubricating oil radiator 2 and the air exhaust channel 3, two ends of an aircraft engine lubricating oil cooling pipeline are respectively connected with a generator lubricating oil inlet joint 11 and a generator lubricating oil outlet joint 12 of the integrated lubricating oil radiator 2, two ends of the aircraft engine lubricating oil cooling pipeline are respectively connected with an engine lubricating oil inlet joint 8 and an engine lubricating oil outlet joint 9 of the integrated lubricating oil radiator 2, high-temperature lubricating oil of the generator enters the generator lubricating oil cooling core 4 through the generator lubricating oil inlet joint 11 to dissipate heat, cooled lubricating oil flows back to the engine lubricating oil system through the generator lubricating oil outlet joint 12 to be recycled, and the cooled lubricating oil flows back to the engine lubricating oil system through the engine lubricating oil outlet joint 9 after entering the engine lubricating oil cooling core 5 through the engine lubricating oil inlet joint 8 to dissipate heat. When the aircraft is in static ground, air driven by the propeller enters the integrated lubricating oil radiator 2 from the air inlet channel 1, the high-temperature lubricating oil of the engine and the generator is cooled and then is discharged from the exhaust channel 3, and the cooling of the lubricating oil of the generator and the lubricating oil of the engine of the aircraft is realized.
Cooling air enters the integrated lubricating oil radiator 2 from the air inlet channel 1 to cool high-temperature lubricating oil. The engine lubricating oil and the generator lubricating oil are separate lubricating oil flow paths in the radiator, but share the air inlet channel 1 and the air outlet channel 2 of the lubricating oil heat dissipation system.
When the temperature of the engine lubricating oil inlet is lower than (70+/-5) DEGC, the lubricating oil does not need to dissipate heat, at the moment, the engine lubricating oil bypass valve is opened, the lubricating oil does not pass through the radiator, when the pressure difference of the engine lubricating oil inlet and outlet is higher than 158.585kPa, the engine lubricating oil bypass valve 10 is opened, the system pressure is reduced, the radiator is protected, and when the temperature of the generator lubricating oil inlet is lower than (70+/-5) DEGC, the lubricating oil does not need to dissipate heat, at the moment, the generator lubricating oil bypass valve 13 is opened, and the generator lubricating oil does not pass through the radiator.
Claims (4)
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310938380.2A CN119429130A (en) | 2023-07-28 | 2023-07-28 | A propeller aircraft lubricating oil cooling system and cooling method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310938380.2A CN119429130A (en) | 2023-07-28 | 2023-07-28 | A propeller aircraft lubricating oil cooling system and cooling method |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN119429130A true CN119429130A (en) | 2025-02-14 |
Family
ID=94529523
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202310938380.2A Pending CN119429130A (en) | 2023-07-28 | 2023-07-28 | A propeller aircraft lubricating oil cooling system and cooling method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN119429130A (en) |
-
2023
- 2023-07-28 CN CN202310938380.2A patent/CN119429130A/en active Pending
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