Propeller aircraft lubricating oil heat dissipation system and heat dissipation method

Abstract

According to the propeller aircraft lubricating oil cooling system and cooling method, 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 channel and an exhaust channel to form the lubricating oil cooling system, and the lubricating oil cooling system is installed on the lower portion of an aircraft nacelle. The air inlet channel, the integrated lubricating oil radiator and the exhaust channel form an air circulation channel; the two ends of an aircraft generator lubricating oil cooling pipeline are connected with a generator lubricating oil inlet connector and a generator lubricating oil outlet connector of the integrated lubricating oil radiator respectively; the two ends of the aircraft engine lubricating oil cooling pipeline are connected with the engine lubricating oil inlet connector and the engine lubricating oil outlet connector of the integrated lubricating oil radiator respectively.

Description

Technical Field

[0001] The present application relates to the technical field of propeller aircraft design, and in particular to a propeller aircraft engine and generator lubricating oil cooling system and a cooling method. Background Art

[0002] At present, more and more aircraft engines and generators tend to be equipped with their own independent lubricating oil systems. For aircraft engines and generators, lubricating oil can lubricate and cool their bearings, gears and other parts. In the process of lubricating the engine and generator, the lubricating oil will take away the heat generated by the friction of the bearings, gears and other parts, and will also increase the temperature of the lubricating oil itself. Therefore, both the engine and the generator need to be equipped with a lubricating oil cooling system.

[0003] For propeller aircraft, the engine and generator are generally installed in the nacelle, and the supporting lubricating oil cooling system also needs to be installed in the nacelle. The space in the aircraft nacelle is small and the weight requirements are strict, which makes the design of the lubricating oil cooling system of the engine and generator difficult. At present, the lubricating oil cooling of engines and generators at home and abroad usually adopts air cooling or oil cooling. The engine and generator have independent lubricating oil cooling systems, which occupy a large space and have a large weight, which is not conducive to the aircraft appearance design and weight reduction requirements. Summary of the invention

[0004] In order to solve the above problems, the present invention provides a propeller aircraft oil cooling system and a heat dissipation method, which solves the oil cooling problem of the engine and the AC generator, saves space and weight, and optimizes the design.

[0005] A propeller aircraft oil cooling system, the oil cooling system contains an engine oil radiator and a generator oil radiator, characterized in that the engine oil radiator and the generator oil radiator are integrated into an integrated oil radiator, the integrated oil radiator is located between an air inlet and an exhaust duct to form an oil cooling system, the air inlet of the air inlet is consistent with the heading, the exhaust port of the exhaust duct is opposite to the heading, the integrated oil radiator contains a physically isolated generator oil cooling core and an engine oil cooling core, the generator oil cooling core is connected to a generator oil inlet joint and a generator oil outlet joint, and the engine oil cooling core is connected to an engine oil inlet joint and an engine oil outlet joint.

[0006] The propeller aircraft oil cooling system is characterized in that the integrated oil radiator contains a fixed frame, the generator oil cooling core and the engine oil cooling core are integrated in the fixed frame, the front side frame of the fixed frame is connected to the air inlet duct, and the rear side frame of the fixed frame is connected to the exhaust duct.

[0007] The propeller aircraft oil cooling system is characterized in that the generator oil inlet joint and the generator oil outlet joint are arranged on a connecting plate at one end of the fixed frame and are connected to the generator oil cooling core, and the engine oil inlet joint and the engine oil outlet joint are arranged on a connecting plate at the other end of the fixed frame and are connected to the engine oil cooling core.

[0008] A propeller aircraft oil cooling method, characterized in that it comprises the following contents: 1) using a propeller aircraft oil cooling system according to any one of claims 1 to 3; 2) installing the oil cooling system at the lower part of the aircraft nacelle so that the air inlet, the integrated oil radiator and the exhaust duct form an air circulation channel; 3) connecting the two ends of the aircraft generator oil cooling pipeline to the generator oil inlet joint and the generator oil outlet joint of the integrated oil radiator respectively; 4) connecting the two ends of the aircraft engine oil cooling pipeline to the engine oil inlet joint and the engine oil outlet joint of the integrated oil radiator respectively; 5) when the aircraft is flying at high altitude, high-speed low-temperature air flows into the integrated oil radiator from the air inlet, cools the high-temperature oil of the engine and the generator, and then discharges it from the exhaust duct; 6) when the aircraft is stationary on the ground, air driven by the propeller enters the integrated oil radiator from the air inlet, cools the high-temperature oil of the engine and the generator, and then discharges it from the exhaust duct.

[0009] The beneficial effects of the present application are as follows: 1) The present application proposes an integrated oil radiator, so that the engine air oil radiator and the generator air oil radiator share the air inlet and exhaust duct, but they still have independent oil flow paths. The oil radiator and its air inlet and exhaust ducts are installed on the lower hull of the nacelle, which solves the problem of cooling the engine oil and generator oil, saves space in the nacelle, reduces the weight of the aircraft, and optimizes the nacelle shape design. 2) When the aircraft is at high speed, the external flow is used to enter the air cooling radiator to cool the oil. When the aircraft speed is low and the external flow is insufficient, the propeller slipstream is used to enter the air cooling oil radiator to dissipate the oil. When the aircraft is flying at high altitude, the cooling airflow enters the oil radiator from the air inlet, cools the high-temperature oil of the engine and generator, and then discharges it from the exhaust duct; when the aircraft is stationary on the ground, the propeller slipstream enters the oil radiator from the air inlet, cools the high-temperature oil of the engine and generator, and then discharges it from the exhaust duct.

[0010] The present application is further described in detail below in conjunction with the accompanying drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0011] Figure 1 This is a principle block diagram of the lubricating oil cooling system of this application.

[0012] Figure 2 This is a schematic diagram of the structure of the lubricating oil cooling system of this application.

[0013] Figure 3 This is a schematic diagram of the integrated oil radiator structure of the present application.

[0014] Figure 4 This is a schematic diagram of the connection relationship between the integrated oil radiator of the present application and the nacelle of a propeller aircraft.

[0015] Figure 5 This is a schematic diagram of the connection relationship between the lubricating oil cooling system of the present application and the nacelle of a propeller aircraft.

[0016] Explanation of numbers in the figure: 1 air inlet, 2 integrated oil radiator, 3 exhaust duct, 4 engine oil cooling core, 5 generator oil cooling core, 6 fixing frame, 7 connecting hole, 8 engine oil inlet joint, 9 engine oil outlet joint, 10 engine oil bypass valve, 11 generator oil inlet joint, 12 generator oil outlet joint, 13 generator oil bypass valve, 14 connecting plate, 15 nacelle, 16 propeller aircraft. DETAILED DESCRIPTION

[0017] Referring to the accompanying drawings, the propeller aircraft oil cooling system of the present application is installed on the lower hull of the belly nacelle 15 of the propeller aircraft 16, as shown in FIG. Figure 5 The lubricating oil cooling system integrates the engine lubricating oil radiator and the generator lubricating oil radiator into an integrated lubricating oil radiator 2, and the integrated lubricating oil radiator 2 is located between the air inlet 1 and the exhaust duct 3. The air inlet of the air inlet 1 is consistent with the heading of the aircraft, and the exhaust port of the exhaust duct 3 is opposite to the heading of the aircraft. The integrated lubricating oil radiator 2 contains a physically isolated generator lubricating oil cooling core 5 and an engine lubricating oil cooling core 4. The generator lubricating oil cooling core 5 is connected to a generator lubricating oil inlet joint 11 and a generator lubricating oil outlet joint 12, and the engine lubricating oil cooling core 4 is connected to an engine lubricating oil inlet joint 8 and an engine lubricating oil outlet joint 9.

[0018] In practice, the integrated oil radiator 2 integrates the generator oil cooling core 5 and the engine oil cooling core 4 through the fixed frame 6. The front side frame of the fixed frame 6 is connected to the air inlet 1 through the connecting hole 7 thereon, and the rear side frame of the fixed frame 6 is connected to the exhaust duct through the connecting hole 7 thereon. The front and rear sides of the fixed frame 6 are an open structure. The generator oil inlet joint 11, the generator oil outlet joint 12 and the generator oil bypass valve 13 are arranged on the connecting plate 13 at one end of the fixed frame 6, and are connected to the generator oil cooling core 5. The engine oil inlet joint 8, the engine oil outlet joint 9 and the engine oil bypass valve 10 are arranged on the connecting plate 13 at the other end of the fixed frame 6, and are connected to the engine oil cooling core 4.

[0019] The above-mentioned engine oil cooling system is installed on the lower hull of the belly nacelle 15 of the propeller aircraft 16, so that the air inlet duct 1, the integrated oil radiator 2 and the exhaust duct 3 form an air circulation channel; then the two ends of the aircraft generator oil cooling pipeline are respectively connected to the generator oil inlet joint 11 and the generator oil outlet joint 12 of the integrated oil radiator 2; the two ends of the aircraft engine oil cooling pipeline are respectively connected to the engine oil inlet joint 8 and the engine oil outlet joint 9 of the integrated oil radiator 2; after the high-temperature oil of the generator enters the generator oil cooling core 4 through the generator oil inlet joint 11 for heat dissipation, the cooled oil flows back to the generator oil system through the generator oil outlet joint 12, and is circulated in this way; similarly, after the high-temperature oil of the engine enters the engine oil cooling core 5 through the engine oil inlet joint 8 for heat dissipation, the cooled oil flows back to the engine oil system through the engine oil outlet joint 9, and is circulated in this way. When the aircraft is flying at high altitude, high-speed and low-temperature air flows into the integrated oil radiator 2 from the air inlet 1, cools the high-temperature oil of the engine and generator, and is then discharged from the exhaust duct 3; when the aircraft is stationary on the ground, air driven by the propeller enters the integrated oil radiator 2 from the air inlet 1, cools the high-temperature oil of the engine and generator, and is then discharged from the exhaust duct 3, thereby cooling the aircraft generator oil and engine oil.

[0020] The cooling air enters the integrated oil radiator 2 from the air intake 1 to cool the high-temperature oil. The engine oil and the generator oil have separate oil flow paths in the radiator, but share the air intake 1 and exhaust 2 of the oil cooling system.

[0021] When the engine oil inlet temperature is lower than (70±5)℃, the oil does not need to be cooled. At this time, the engine oil bypass valve is opened and the oil does not pass through the radiator. When the engine oil inlet and outlet pressure difference is higher than 158.585kPa, the engine oil bypass valve 10 is opened to reduce the system pressure and protect the radiator. When the generator oil inlet temperature is lower than (70±5)℃, the oil does not need to be cooled. At this time, the generator oil bypass valve 13 is opened and the generator oil does not pass through the radiator.

Claims

1. A propeller aircraft oil cooling system, the oil cooling system comprising an engine oil radiator and a generator oil radiator, characterized in that: The engine oil radiator and the generator oil radiator are integrated into an integrated oil radiator, which is located between the air inlet and the exhaust to form an oil cooling system. The air inlet of the air inlet is consistent with the heading, and the exhaust of the exhaust is opposite to the heading. The integrated oil radiator contains a physically isolated generator oil cooling core and an engine oil cooling core. The generator oil cooling core is connected to a generator oil inlet joint and a generator oil outlet joint, and the engine oil cooling core is connected to an engine oil inlet joint and an engine oil outlet joint.

2. The propeller aircraft oil cooling system according to claim 1, characterized in that: The integrated oil radiator comprises a fixed frame, in which the generator oil radiator core and the engine oil radiator core are integrated, the front side frame of the fixed frame is connected to the air inlet, and the rear side frame of the fixed frame is connected to the exhaust duct.

3. The propeller aircraft oil cooling system according to claim 1, characterized in that: The generator oil inlet joint and the generator oil outlet joint are arranged on a connecting plate at one end of the fixed frame and are connected to the generator oil cooling core. The engine oil inlet joint and the engine oil outlet joint are arranged on a connecting plate at the other end of the fixed frame and are connected to the engine oil cooling core.

4. A propeller aircraft lubricating oil heat dissipation method, characterized in that The invention comprises the following contents: 1) using the propeller aircraft oil cooling system according to any one of claims 1 to 3; 2) installing the oil cooling system at the lower part of the aircraft nacelle so that the air inlet, the integrated oil radiator and the exhaust duct form an air circulation channel; 3) connecting the two ends of the aircraft generator oil cooling pipeline to the generator oil inlet joint and the generator oil outlet joint of the integrated oil radiator respectively; 4) connecting the two ends of the aircraft engine oil cooling pipeline to the engine oil inlet joint and the engine oil outlet joint of the integrated oil radiator respectively; 5) when the aircraft is flying at high altitude, the high-speed low-temperature air flow enters the integrated oil radiator from the air inlet, cools the high-temperature oil of the engine and the generator, and then is discharged from the exhaust duct; 6) When the aircraft is stationary on the ground, the propeller drives air from the air inlet into the integrated oil radiator, cools the high-temperature oil of the engine and generator, and then discharges it from the exhaust duct.

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