Nacelle heat sink oil tank integration for an aeroengine

Abstract

This invention belongs to the field of aero-engine design and manufacturing technology, and discloses an integrated device for an aero-engine casing radiator oil tank. It includes an annular front end cover and a rear end cover, which are axially opposite each other and fixed to a cylindrical outer wall, forming a cylindrical shell. An inner wall is coaxially arranged inside the shell, with both ends fixed to the front and rear end covers to form a casing. An annular sealed oil reservoir is formed between the inner and outer wall surfaces. An air-lubricating oil radiator and a fuel-lubricating oil radiator are fixed inside the oil reservoir. Their outward-facing arc-shaped sides are fixed to the inner side of the outer wall, while their inward-facing sides are fixed to the inner wall via a support plate. One end of the support plate is connected to the inner wall, and the other end is connected to both radiators. The outer wall surface has an oil outlet, an oil return port, a fuel inlet, and a fuel outlet. This invention solves the technical problems of existing aero-engine casing accessories being complex in structure, having numerous oil circuit interfaces, and externally mounted radiators, leading to excessive weight and low reliability in aero-engines.

Description

Technical Field

[0001] This invention belongs to the field of aero-engine design and manufacturing technology, and relates to an integrated device for a casing radiator and lubricating oil tank for aero-engines. Background Technology

[0002] Aircraft engines have an internal lubrication system (device) for lubricating engine components. As the engine runs, the lubricating oil temperature rises rapidly, necessitating a cooling system to lower the oil temperature. There are typically two types of radiators used for lubrication system cooling: one type guides external airflow into the air-oil radiator, where heat exchange occurs between the radiator and the high-temperature lubricating oil through a finned structure; the other type utilizes engine fuel as a cooling medium for heat exchange with the lubricating oil, known as a fuel-oil radiator.

[0003] Existing oil cooling systems employ a circumferentially integrated layout around the engine casing, where the oil tank and dual air / fuel oil radiators are arranged in a ring around the engine casing, forming a compact thermal management module. The oil chamber of the fuel oil radiator is connected to the oil tank via a dedicated pipeline, ultimately delivering the cooled oil to the bearing chamber. Its fuel chamber is connected to the engine fuel line, where the heated fuel is injected into the combustion chamber for combustion. Furthermore, existing oil cooling systems also provide mounting interfaces for auxiliary components such as oil pumps and valves, effectively improving system stability and maintenance convenience. However, the aforementioned oil cooling system structure has the following technical problems: First, the complex and numerous mounting structures for accessories on the engine casing surface significantly increase the overall system weight. Second, the excessive number of oil system interfaces not only increases the probability of leakage but also reduces the overall system reliability. Additionally, the externally mounted radiator requires excessively long piping, occupying too much engine space and further complicating the layout. Summary of the Invention

[0004] This invention provides an integrated device for the casing radiator and oil tank of an aero-engine, which solves the technical problems of existing aero-engine casing accessories having complex structures, numerous oil circuit interfaces, and external radiators, resulting in excessive weight, low reliability, and excessive space occupation of the aero-engine.

[0005] To solve the above-mentioned technical problems, the technical solution adopted by the present invention is an integrated device for the oil tank of the casing radiator of an aero-engine, including a front end cover and a rear end cover in an annular shape, the front end cover and the rear end cover are axially opposite to each other, and a cylindrical outer wall surface is sandwiched between the two and fixedly connected to the two, together forming a cylindrical shell.

[0006] The housing has an inner wall surface coaxially fitted inside, and the two ends of the inner wall surface are fixed to the front cover and the rear cover respectively to form a casing. An annular sealed oil storage cavity is formed between the inner wall surface and the outer wall surface.

[0007] An air-oil radiator and a fuel-oil radiator are fixedly connected inside the oil storage chamber. Both the air-oil radiator and the fuel-oil radiator have internal channel structures for heat exchange.

[0008] The side of the air-oil radiator and the fuel-oil radiator facing the outer wall is curved and fixedly connected to the inner side of the outer wall. The side of the air-oil radiator and the fuel-oil radiator facing the inner wall is fixedly connected to the inner wall through a support plate. One end of the support plate is fixedly connected to the inner wall, and the other end is fixedly connected to one of the air-oil radiator or the fuel-oil radiator.

[0009] The outer wall surface is provided with a lubricating oil outlet, a lubricating oil return port, a fuel inlet, and a fuel outlet. The lubricating oil outlet and the lubricating oil return port are connected to the oil storage chamber, and the fuel inlet and the fuel outlet are connected to the fuel and lubricating oil radiator.

[0010] Furthermore, the outer wall surface is provided with an oil outlet and an oil return port, and the oil outlet and the oil return port are spaced apart in the circumferential direction of the outer wall surface.

[0011] Furthermore, the air-oil radiator is fixed to the inner side of the outer wall of the casing. An air chamber and a first oil chamber are separated inside the air-oil radiator by a first partition. The air chamber is close to the outer wall, and the first oil chamber is close to the inner wall. The first partition is connected to the housing of the air-oil radiator. The inlet and outlet of the air chamber are opened on the outer wall. The air chamber is provided with heat dissipation fins. The thickness of the heat dissipation fins is 0.3mm to 0.5mm, the height is 1mm to 5mm, and the structure is any one of straight fins, serrated fins, corrugated fins, or perforated fins. The extension direction of the heat dissipation fins is parallel to the axial direction of the casing.

[0012] Furthermore, the first lubricating oil chamber is directly connected to the oil storage chamber, and the first lubricating oil chamber is provided with a first forked rib, which is fixedly connected to the first partition plate.

[0013] Furthermore, the lubricating oil radiator is fixed to the inner side of the outer wall of the casing. The lubricating oil radiator has a lubricating oil radiator core inside. The lubricating oil radiator core is composed of multiple stacked second partitions. The space between two adjacent second partitions is constructed as a heat exchange channel. The fuel channel and the lubricating oil channel are arranged alternately in the stacking direction. One end of the lubricating oil channel is connected to the oil storage chamber, and the other end is connected to the lubricating oil outlet. One end of the lubricating oil radiator is provided with a fuel inlet chamber and a fuel outlet chamber. The inlet end of the fuel channel is connected to one end of the fuel inlet chamber, and the outlet end of the fuel channel is connected to one end of the fuel outlet chamber. The other end of the fuel inlet chamber is connected to the fuel inlet, and the other end of the fuel outlet chamber is connected to the fuel outlet. The other end of the lubricating oil radiator is provided with a second lubricating oil chamber inlet chamber and a second lubricating oil chamber outlet chamber. The second lubricating oil chamber inlet chamber is connected to the oil storage chamber, and the second lubricating oil chamber outlet chamber is connected to the lubricating oil outlet.

[0014] A second fork rib is fixedly connected to the fuel passage and the lubricating oil passage. The diameter of the second fork rib is 0.5mm to 0.6mm and the height is 1mm to 1.2mm.

[0015] Furthermore, the front end cover is provided with multiple mounting holes and an oil filling port. The multiple mounting holes are evenly spaced along the circumference of the front end cover, and the oil filling port is located at the top of the front end cover.

[0016] Furthermore, it also includes an inner ring coaxially sleeved on the inner side of the inner wall surface and multiple guide plates evenly spaced along the circumference. Each guide plate extends radially, with one end fixed to the outer wall of the inner ring and the other end fixed to the inner wall of the inner wall surface.

[0017] Furthermore, the rear end cover is provided with mounting holes, which are evenly spaced along the circumference of the rear end cover.

[0018] The beneficial effects of this invention are: by highly integrating the oil tank, casing, and radiator, this invention significantly reduces the original external piping and mounting components, effectively reducing the weight and overall size of the aircraft engine, while improving heat dissipation efficiency and operational reliability. Attached Figure Description

[0019] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0020] Figure 1 This is a schematic diagram of the structure of the integrated device for the casing radiator and lubricating oil tank of an aero engine according to an embodiment of the present invention;

[0021] Figure 2 This is an exploded view of an integrated device for a casing radiator and lubricating oil tank in an aero engine, according to an embodiment of the present invention.

[0022] Figure 3 This is a front view of an embodiment of the present invention for an integrated device of a casing radiator and lubricating oil tank for an aero engine;

[0023] Figure 4 This is a right view of an embodiment of the present invention for an integrated device of a casing radiator and lubricating oil tank for an aircraft engine;

[0024] Figure 5 This is a left view of an integrated device for a casing radiator and lubricating oil tank of an aircraft engine according to an embodiment of the present invention;

[0025] Figure 6 yes Figure 3 AA section view;

[0026] Figure 7 yes Figure 3 A close-up view of the air-cooled lubricating oil radiator;

[0027] Figure 8 yes Figure 3 A partial enlarged view of the Zhongran lubricating oil radiator;

[0028] Figure 9 yes Figure 3 A partial enlarged view of the fuel flow path in the Zhongran lubricating oil radiator;

[0029] Figure 10 yes Figure 3 A partial enlarged view of the fuel flow path in the Zhongran lubricating oil radiator;

[0030] Figure 11 yes Figure 3 A schematic diagram showing the connection relationship between the oil radiator, oil reservoir, second oil chamber, and second lubricating chamber.

[0031] In the diagram, 1. Casing, 2. Oil reservoir, 3. Air-oil radiator, 4. Fuel-oil radiator, 101. Front end cover, 102. Rear end cover, 103. Outer wall surface, 104. Inner wall surface, 105. Guide plate, 106. Inner ring, 107. Mounting hole, 201. Oil inlet, 202. Oil outlet, 203. Oil return port, 204. Fuel outlet, 205. Fuel inlet, 206. Support plate, 301. Air cavity, 302. Heat dissipation fins, 303. First oil cavity, 304. First forked rib, 305. First partition, 401A. Fuel inlet chamber, 401B. Fuel outlet chamber, 402A. Second oil cavity inlet chamber, 402B. Second oil cavity outlet chamber, 403. Second forked rib, 404. Fuel-oil radiator core, 405. Second partition. Detailed Implementation

[0032] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0033] Reference Figure 1 , Figure 2 The present invention provides an integrated device for a casing radiator oil tank for an aircraft engine, including a front end cover 101 and a rear end cover 102 in an annular shape. The front end cover 101 and the rear end cover 102 are axially opposite to each other. A cylindrical outer wall surface 103 is sandwiched between the two and fixedly connected to them, forming a cylindrical shell together.

[0034] An inner wall surface 104 is coaxially fitted inside the cylindrical housing. The two ends of the inner wall surface 104 are fixedly connected to the front cover 101 and the rear cover 102 respectively to form a casing 1. An annular sealed oil storage cavity 2 is formed between the inner wall surface 104 and the outer wall surface 103.

[0035] In this embodiment, the casing 1 serves as a structural support, an airflow guide for the outer bypass duct, and an accessory mounting area.

[0036] In this embodiment, the internal cavity space of the casing 1 is set as the oil storage cavity 2. Therefore, the outer wall surface 103 and the inner wall surface 104 are not only components of the casing 1, but also the inner and outer walls of the oil storage cavity 2.

[0037] In this embodiment, the front cover 101 and the rear cover 102 are integrally formed with the outer wall surface 103 and the inner wall surface 104 through 3D printing. Integral forming can also be achieved through other processes known in the art, such as casting and welding.

[0038] An air-oil radiator 3 and a fuel-oil radiator 4 are fixedly connected inside the oil storage chamber 2. Both the air-oil radiator 3 and the fuel-oil radiator 4 have internal channel structures for heat exchange.

[0039] The side of the air-oil radiator 3 and the fuel-oil radiator 4 facing the outer wall 103 is an arc-shaped surface and is fixedly connected to the inner side of the outer wall 103. The side of the air-oil radiator 3 and the fuel-oil radiator 4 facing the inner wall 104 is fixedly connected to the inner wall 104 through a support plate 206. One end of the support plate 206 is fixedly connected to the inner wall 104, and the other end is fixedly connected to one of the air-oil radiator 3 or the fuel-oil radiator 4.

[0040] In this embodiment, the support plate 206 is a support structure inside the oil storage cavity 2, which is used to improve the overall structural strength of the oil storage cavity 2 and prevent deformation.

[0041] The outer wall surface 103 is provided with a lubricating oil outlet 202, a lubricating oil return port 203, a fuel outlet 204, and a fuel inlet 205. The lubricating oil outlet 202 and the lubricating oil return port 203 are connected to the oil storage chamber 2, and the fuel outlet 204 and the fuel inlet 205 are connected to the fuel oil radiator 4. This is the result of the integrated design of the oil storage chamber 2 and the casing 1. This integrated opening layout is the result of the integrated design of the oil storage chamber 2 and the casing 1.

[0042] Reference Figure 1 , Figure 2 , Figure 4 An oil outlet 202 and an oil return port 203 are provided on the outer wall surface 103. The oil outlet 202 and the oil return port 203 are arranged in the circumferential direction of the outer wall surface 103. The height of the oil outlet 202 is lower than the position of the oil return port 203. In this embodiment, the oil outlet 202 is located on the outer wall surface 103 near the bottom of the oil storage chamber 2, which facilitates oil discharge and avoids the introduction of impurities from the bottom of the oil tank, and facilitates the extraction of cold oil from the bottom of the oil storage chamber 2. The oil return port 203 is located on the outer wall surface 103 near the top of the oil storage chamber 2. At the same time, the high temperature return oil has a low density. After entering from the upper oil return port 203, it tends to float naturally and stay at the top of the oil storage chamber.

[0043] Reference Figure 1 , Figure 2 , Figure 4 , Figure 5 The lubricating oil outlet 202, lubricating oil return outlet 203, fuel outlet 204, and fuel inlet 205 are all nozzles that extend out of the outer wall surface 103 and are integrally formed with the outer wall surface 103 by 3D printing.

[0044] Reference Figure 6 , Figure 7 The air-oil radiator 3 is fixed to the inner side of the outer wall 103 of the casing 1. An air chamber 301 and a first oil chamber 303 are separated within the air-oil radiator 3 by a first partition 305. The air chamber 301 is near the outer wall 103, and the first oil chamber 303 is near the inner wall 104. The first partition 305 is connected to the housing of the air-oil radiator 3. The inlet and outlet of the air chamber 301 are located on the outer wall 103, and heat dissipation fins are provided inside the air chamber 301. 302, the thickness of the heat dissipation fin 302 is 0.3mm to 0.5mm, the height is 1mm to 5mm, and the structure is any one of straight fins, serrated fins, corrugated fins or perforated fins. The extension direction of the heat dissipation fin 302 is parallel to the axial direction of the casing 1. Both ends of the first lubricating oil cavity 303 are directly connected to the oil storage cavity 2. The first lubricating oil cavity 303 is provided with a first forked rib 304, and the first forked rib 304 is fixedly connected to the first partition 305.

[0045] Reference Figure 2 , Figure 8 , Figure 9 , Figure 10 , Figure 11 The lubricating oil radiator 4 is fixed (optionally using 3D printing technology) to the inner side of the outer wall 103 of the casing 1. The lubricating oil radiator 4 contains a lubricating oil radiator core 404, which is formed by stacking multiple second partitions 405. Fuel passages and lubricating oil passages are alternately formed between adjacent second partitions 405. One end of the lubricating oil passage is connected to the oil reservoir 2, and the other end is connected to the lubricating oil outlet 202. At the end of the lubricating oil radiator 4 furthest from the lubricating oil outlet 202, there are a fuel inlet 401A and a fuel outlet 401B. The fuel inlet 401A and the fuel outlet 401B are connected to each other through a non-linear, angled channel. The inlet end of the fuel passage is connected to the fuel inlet chamber 401A, and the outlet end of the fuel passage is connected to the fuel outlet chamber 401B. The fuel inlet chamber 401A is connected to the fuel inlet 205, and the fuel outlet chamber 401B is connected to the fuel outlet 204. The lubricating oil radiator 4 has a second lubricating oil chamber inlet chamber 402A and a second lubricating oil chamber outlet chamber 402B at one end near the lubricating oil outlet 202. The second lubricating oil chamber inlet chamber 402A and the second lubricating oil chamber outlet chamber 402B are connected to each other through a non-linear, angled channel. The second lubricating oil chamber inlet chamber 402A is connected to the oil storage chamber 2, and the second lubricating oil chamber outlet chamber 402B is connected to the lubricating oil outlet 202.

[0046] The fuel passage and the lubricating oil passage are fixed with a second forked rib 403, which can enhance heat transfer and improve the structural strength of the oil tank. The diameter of the second forked rib 403 is 0.5mm to 0.6mm, the height is 1mm to 1.2mm, and the distance between the nearest surfaces of two adjacent ribs is 1mm to 2mm.

[0047] Reference Figure 1 , Figure 3 The front cover 101 is provided with multiple mounting holes 107 and an oil filling port 201. The multiple mounting holes 107 are evenly spaced along the circumference of the front cover 101. The oil filling port 201 is located at the top of the front cover 101. The oil filling port 201 must be located at the top of the oil tank structure so that it is easy to add oil by relying on gravity.

[0048] refer to Figure 1 , Figure 2 It also includes an inner ring 106 coaxially sleeved on the inner side of the inner wall surface 104 and a plurality of guide plates 105 evenly spaced along the circumference. Each guide plate 105 extends radially, with one end fixed to the outer wall of the inner ring 106 and the other end fixed to the inner wall of the inner wall surface 104.

[0049] In this embodiment, the function of the deflector 105 is to guide the air flowing through the casing 1 and to enhance the structural connection strength.

[0050] In this embodiment, the inner ring 106 serves to support the guide plate 105.

[0051] In this embodiment, the mounting hole 107 is used for mounting and fixing the casing 1.

[0052] The rear end cover 102 is provided with mounting holes 107, which are evenly spaced along the circumference of the rear end cover 102.

[0053] Working principle: Under the drive of the lubricating oil pump, the high-temperature lubricating oil enters the oil storage chamber 2 through the lubricating oil return port 203 on the outer wall surface 103. The oil storage chamber 2 serves as the oil collection pool for the entire lubricating oil system, storing a large amount of lubricating oil. Since it is in direct contact with the outer wall surface 103 and the inner wall surface 104 of the casing 1, the lubricating oil in the oil storage chamber 2 can undergo preliminary natural convection and radiation heat dissipation through the outer wall surface 103 and the inner wall surface 104 of the casing 1.

[0054] The lubricating oil flows within the oil reservoir 2 and continues to cool in two separate paths: a portion of the lubricating oil, under the influence of gravity, flows from the oil reservoir 2 into the air-oil radiator 3 located below it. Since the first oil chamber 303 of the air-oil radiator is connected to the oil reservoir 2, the lubricating oil flows into the cavity of the first oil chamber 303. When the lubricating oil flowing into the first oil chamber 303 passes through the first fork rib 304 fixed inside the first oil chamber 303, it is disturbed and comes into contact with the first fork rib 304 and the wall of the first oil chamber 303. Heat is transferred to the wall of the first oil chamber 303 through convection heat transfer. At the same time, the high temperature from the engine compartment... Rapidly cooling air is guided into the air cavity 301 through the inlet of the air cavity 301 opened on the outer wall surface 103. The heat dissipation fins 302 provided inside the air cavity 301 increase the heat dissipation area of ​​the air cavity 301. The heat of the first lubricating oil cavity 303 is conducted to the air cavity 301 through the wall surface and the first partition 305 and carried away by the high-speed cold air, thereby cooling the lubricating oil. The cooled lubricating oil collects at the bottom of the first lubricating oil cavity 303 under the action of gravity. Since the first lubricating oil cavity 303 is connected to the oil storage cavity 2, the cooled lubricating oil flows directly back into the interior of the oil storage cavity 2 from the outlet of the first lubricating oil cavity 303 connected to the oil storage cavity 2.

[0055] The fuel oil radiator 4 has a second lubricating oil inlet 402A and a second lubricating oil outlet 402B at one end. The second lubricating oil inlet 402A is connected to the oil storage chamber 2, and the second lubricating oil outlet 402B is connected to the lubricating oil outlet 202. A fuel oil radiator core 404 is located beside the second lubricating oil inlet 402A inside the fuel oil radiator 4. The fuel oil radiator core 404 is composed of multiple stacked second partitions 405, with fuel passages and lubricating oil passages alternately formed between adjacent second partitions 405. Another portion of the lubricating oil, driven by the lubricating oil pump, is pumped from the oil storage chamber 2 through the second lubricating oil inlet 402A into the lubricating oil passages in the fuel oil radiator core 404, and exits through the second lubricating oil outlet 402B. Because the lubricating oil passages are equipped with second forked ribs 403, the lubricating oil flow... Heat is transferred to the wall of the second lubricating chamber inlet 402A and the second forked rib 403 via the lubricating oil channel. The second lubricating chamber inlet 402A and the second lubricating chamber outlet 402B are connected to each other through a non-linear, angled channel. The other end of the lubricating oil radiator 4 is provided with a fuel inlet 401A and a fuel outlet 401B. The fuel inlet 401A and the fuel outlet 401B are connected to each other through a non-linear, angled channel, allowing gas, liquid or other substances to flow between them. The inlet end of the fuel channel is connected to the fuel inlet 401A, and the outlet end of the fuel channel is connected to the fuel outlet 401B. The fuel inlet 401A is connected to the fuel inlet 205, and the fuel outlet 401B is connected to the fuel outlet 204.

[0056] Low-temperature fuel enters the fuel inlet chamber 401A from the fuel inlet 205 under the action of the pump. Under the action of gravity, it flows through the fuel inlet chamber 401A into the fuel channel in the lubricating oil radiator core 404, absorbing the heat conducted by the pump and realizing the heat exchange between the fuel and the lubricating oil. Under the action of the pump, the fuel after heat exchange flows to the fuel outlet chamber 401B. Since the fuel outlet chamber 401B is connected to the fuel outlet 204, the fuel flows from the fuel outlet chamber 401B to the fuel outlet 204 and is then pumped away. The cooled lubricating oil flows from the lubricating oil channel through the second lubricating oil chamber outlet chamber 402B to the lubricating oil outlet 202. Since the lubricating oil outlet 202 is connected to the oil storage chamber 2, the lubricating oil returns to the oil storage chamber 2.

[0057] The cooled lubricating oil is delivered to high-temperature components such as engine bearings and gears for lubrication. After absorbing heat, the lubricating oil with an increased temperature returns to the oil reservoir 2 through the lubricating oil return port 203 for the next round of heat dissipation.

[0058] Performance Verification: The existing casing and oil tank, when connected together and with the radiator installed, have an external dimension of approximately φ520mm×150mm and a weight of 6.6kg, achieving a lubricating oil cooling capacity of 15kW. After integrating the radiator with the casing and oil tank, as proposed in this invention, the external dimension is reduced to φ500mm×120mm, the weight is reduced to 5.5kg, and the lubricating oil cooling capacity is increased to 17.5kW. It is evident that this invention, through integrated design, reduces the system size and weight while improving heat dissipation performance by optimizing channels and heat exchange efficiency.

[0059] The various embodiments in this specification are described in a related manner. The same or similar parts between the various embodiments can be referred to each other. Each embodiment focuses on describing the differences from other embodiments.

[0060] The above description is merely a preferred embodiment of the present invention and is not intended to limit the scope of protection of the present invention. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention are included within the scope of protection of the present invention.

Claims

1. An integrated device for a casing radiator oil tank for an aircraft engine, comprising a front end cover (101) and a rear end cover (102) in an annular shape, the front end cover (101) and the rear end cover (102) being axially opposite each other, and a cylindrical outer wall surface (103) being sandwiched between the two and fixedly connected to them, together forming a cylindrical shell. The housing is coaxially fitted with an inner wall surface (104), and the two ends of the inner wall surface (104) are fixedly connected to the front cover (101) and the rear cover (102) respectively to form a casing (1). An annular sealed oil storage cavity (2) is formed between the inner wall surface (104) and the outer wall surface (103). An air lubricating oil radiator (3) and a fuel lubricating oil radiator (4) are fixedly connected inside the oil storage chamber (2). Both the air lubricating oil radiator (3) and the fuel lubricating oil radiator (4) have internal channel structures for heat exchange. The side of the air-oil radiator (3) and the fuel-oil radiator (4) facing the outer wall (103) is an arc-shaped surface and is fixedly connected to the inner side of the outer wall (103). The side of the air-oil radiator (3) and the fuel-oil radiator (4) facing the inner wall (104) is fixedly connected to the inner wall (104) through a support plate (206). One end of the support plate (206) is fixedly connected to the inner wall (104), and the other end is fixedly connected to one of the air-oil radiator (3) or the fuel-oil radiator (4). An oil outlet (202), an oil return port (203), a fuel inlet (205), and a fuel outlet (204) are provided through the outer wall surface (103). The oil outlet (202) and the oil return port (203) are both connected to the oil storage chamber (2), and the fuel outlet (204) and the fuel inlet (205) are both connected to the fuel and oil radiator (4). The outer wall surface (103) is provided with an oil outlet (202) and an oil return port. (203), the lubricating oil outlet (202) and the lubricating oil return outlet (203) are spaced apart in the circumferential direction on the outer wall surface (103); the lubricating oil radiator (4) is fixed to the inner side of the outer wall surface (103) of the casing (1), and the lubricating oil radiator (4) is provided with a lubricating oil radiator core (404), which is composed of multiple second partitions (405) stacked together, and two adjacent second partitions (405) The space between them is constructed as a heat exchange channel, and the fuel channel and the lubricating oil channel are arranged alternately in the stacking direction. One end of the lubricating oil channel is connected to the oil storage chamber (2), and the other end is connected to the lubricating oil outlet (202). One end of the fuel-lubricating oil radiator (4) is provided with a fuel inlet chamber (401A) and a fuel outlet chamber (401B). The inlet end of the fuel channel is connected to one end of the fuel inlet chamber (401A), and the outlet end of the fuel channel is connected to one end of the fuel outlet chamber (401B). The other end of the fuel inlet chamber (401A) is connected to the fuel inlet (205), and the other end of the fuel outlet chamber (401B) is connected to the fuel outlet (204). The other end of the fuel-lubricating oil radiator (4) is provided with a second lubricating oil chamber inlet chamber (402A) and a second lubricating oil chamber outlet chamber (402B). The second lubricating oil chamber inlet chamber (402A) is connected to the oil storage chamber (2), and the second lubricating oil chamber outlet chamber (402B) is connected to the lubricating oil outlet (202). A second forklift rib (403) is fixedly connected to the fuel passage and the lubricating oil passage. The diameter of the second forklift rib (403) is 0.5 mm to 0.6 mm and the height is 1 mm to 1.2 mm.

2. The integrated device for the casing radiator and lubricating oil tank of an aircraft engine according to claim 1, characterized in that, An air-oil radiator (3) is fixed to the inner side of the outer wall (103) of the casing (1). An air cavity (301) and a first oil cavity (303) are separated in the air-oil radiator (3) by a first partition (305). The air cavity (301) is close to the outer wall (103), and the first oil cavity (303) is close to the inner wall (104). The first partition (305) is connected to the housing of the air-oil radiator (3). The inlet and outlet of the air cavity (301) are opened on the outer wall (103). The air cavity (301) is provided with heat dissipation fins (302). The thickness of the heat dissipation fins (302) is 0.3mm to 0.5mm, the height is 1mm to 5mm, and the structure is any one of straight fins, serrated fins, corrugated fins or perforated fins. The extension direction of the heat dissipation fins (302) is parallel to the axial direction of the casing (1).

3. The integrated device for the casing radiator oil tank of an aircraft engine according to claim 2, characterized in that, The first lubricating oil cavity (303) is directly connected to the oil storage cavity (2). The first lubricating oil cavity (303) is provided with a first forked rib (304), and the first forked rib (304) is fixedly connected to the first partition (305).

4. The integrated device for the casing radiator and lubricating oil tank of an aircraft engine according to claim 1, characterized in that, The front cover (101) is provided with a plurality of mounting holes (107) and an oil filling port (201). The plurality of mounting holes (107) are evenly spaced along the circumference of the front cover (101), and the oil filling port (201) is located on the top of the front cover (101).

5. The integrated device for the casing radiator and lubricating oil tank of an aircraft engine according to claim 1, characterized in that, It also includes an inner ring (106) coaxially sleeved on the inner side of the inner wall surface (104) and a plurality of guide plates (105) evenly spaced along the circumference. Each guide plate (105) extends radially, with one end fixed to the outer wall of the inner ring (106) and the other end fixed to the inner wall of the inner wall surface (104).

6. The integrated device for the casing radiator and lubricating oil tank of an aircraft engine according to claim 1, characterized in that, The rear end cover (102) is provided with mounting holes (107), which are evenly spaced along the circumference of the rear end cover (102).

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