Cooling system for aero-engine

Abstract

The utility model discloses a cooling system for an aero-engine. The cooling system comprises an oil cooler used for heat exchange between lubricating oil and cooling liquid. The pressure valve is communicated with the oil cooler; a cooling liquid connector and a lubricating oil connector of the oil cooler are both arranged on the side face of the oil cooler. The device further comprises an expansion pot which is communicated with a cooling liquid outlet of the oil cooler through a pipeline. According to the scheme, the problem that in the prior art, a cooling system is poor in universality due to the fact that the requirement for the installation space of an oil cooler is large is solved.

Description

TECHNICAL FIELD

[0001] The utility model relates to a cooling system for aero-engine. BACKGROUND

[0002] The cooling system for aero-engine is a system for cooling and temperature reduction of cylinder head, cylinder body and oil of aero-engine. The existing cooling system comprises a water pump for driving cooling liquid into the cooling channel of the cylinder head and cylinder body of aero-engine, an oil cooler for receiving the cooling liquid flowing out of the cooling channel of aero-engine and for heat exchange between the cooling liquid and oil, and a cooler for heat dissipation and temperature reduction of the cooling liquid, and the cooler retransmits the cooled cooling liquid to the water pump to make the cooling liquid circulate.

[0003] Chinese patent document CN211343091U discloses an aero-piston internal combustion engine, wherein a cooling system is disclosed, which comprises an oil cooler, the oil cooler comprises an oil cooler body with an oil cavity and a water cavity, a cooling water chamber is arranged on the oil cooler body, the cooling water chamber comprises an inlet water chamber and an outlet water chamber separated by a perforated partition plate, the inlet water chamber is provided with inlet water holes corresponding to the outlet water holes of the cylinder head water jacket one by one, the outlet water holes of each cylinder head water jacket are connected to the inlet water holes of the inlet water chamber through pipelines, the outlet water chamber is provided with outlet water holes, and the inlet water chamber and the outlet water chamber are communicated with the water cavity of the oil cooler body respectively; a gas collection chamber is further arranged on the top of the cooling water chamber, a gas hole is arranged between the gas collection chamber and the cooling water chamber, and a vent valve is arranged on the gas collection chamber, when the pressure of the gas collection chamber is too large and exceeds the limited pressure value of the vent valve, the vent valve opens and discharges gas.

[0004] In the above-mentioned prior art, the oil cooler is arranged vertically, that is, the oil cavity and the water cavity are distributed along the vertical direction; various pipelines are connected to the top surface and the side surface of the oil cooler, and a gas collection chamber and a vent valve are integrated on the top of the oil cooler, so that the height dimension of the entire oil cooler is relatively large, which leads to a relatively large installation space required during installation, thereby making the oil cooler only be installed beside the air intake manifold of the aero-engine and connected and fixed to the case body of the aero-engine by using an adapter bracket. In this way, the installation and arrangement of the oil cooler is limited, which reduces the universality of the cooling system. UTILITY MODEL CONTENTS

[0005] The utility model aims at providing a cooling system for aero-engine to solve the problem of poor universality of the cooling system in the prior art due to the large installation space requirement of the oil cooler.

[0006] In order to achieve the above-mentioned purpose, the basic scheme of the present utility model provides a cooling system for an aircraft engine, including an oil cooler for heat exchange between lubricating oil and coolant; also including a pressure valve connected to the oil cooler; the coolant interface and lubricating oil interface of the oil cooler are both arranged on the side of the oil cooler; and also including an expansion pot, which is connected to the coolant outlet of the oil cooler through a pipeline.

[0007] The beneficial effects of this basic solution are as follows: by locating both the coolant and lubricating oil interfaces of the oil cooler on the side of the oil cooler and connecting the oil cooler to the expansion pot, the oil cooler can eliminate the need for a plenum chamber, thereby significantly reducing the vertical height of the oil cooler and lowering the installation space requirement, allowing the oil cooler to be installed in smaller spaces. The separately installed expansion pot is also relatively small and can be flexibly installed in smaller spaces. This solution significantly reduces the installation space requirement of the cooling system, making it easier to install and use the cooling system on a variety of aircraft engines, thereby resolving the problem of poor versatility of cooling systems in the prior art due to the high installation space requirement of the oil cooler.

[0008] Preferably, the oil cooler is arranged in a flat shape. Such an arrangement further reduces the requirement for installation space of the oil cooler, thereby further improving the versatility of the cooling system.

[0009] Preferably, the pressure valve is connected to the top of the expansion pot. With this arrangement, when the oil cooler's pressure becomes excessive, the pressure in the expansion pot also increases. The expansion pot then releases pressure via the pressure valve, thus preventing excessive oil cooler pressure from impacting the normal operation of the cooling system. Placing the pressure valve on the expansion pot not only prevents the cooling system from experiencing excessive oil cooler pressure that could impact normal operation, but also further reduces the installation space required for the oil cooler, thereby improving the versatility of the cooling system.

[0010] Preferably, a mounting bracket is provided on the side of the oil cooler, and a shock-absorbing rubber pad is installed on the mounting bracket. With this arrangement, the oil cooler is directly mounted and fixed via the mounting bracket and the shock-absorbing rubber pad. This not only reduces the impact of the mounting bracket on the height of the oil cooler, thus reducing the required height of the installation space, but also helps to reduce the impact of aircraft engine vibration on the oil cooler, thereby improving the service life of the oil cooler.

[0011] Preferably, the bottom of the expansion pot is connected to a support frame, and a rubber sheath is provided on the bottom of the expansion pot. With this arrangement, the expansion pot is mounted and fixed by the support frame and protected by the rubber sheath, which not only facilitates the installation of the expansion pot, but also helps to reduce the phenomenon of damage to the expansion pot caused by bumps and collisions.

[0012] The utility model has the advantages of the following:

[0013] 1. In the scheme, the expansion pot is installed independently from the oil cooler, so that the oil cooler is designed without a gas collection chamber, thereby greatly reducing the volume of the oil cooler, and the cooling liquid interface and the oil interface are both arranged on the side surface of the oil cooler, so that the oil cooler greatly reduces the requirement for the size of the installation space, thereby enabling the cooling system to be installed and used on different types of aero-engines, thereby improving the versatility of the cooling system.

[0014] 2. In the scheme, the oil cooler is installed and arranged through the mounting bracket and the shock-absorbing rubber pad, and the expansion pot is installed and arranged through the support frame and the rubber sheath, so that the oil cooler and the expansion pot can be independently and reliably installed and fixed and can be shock-absorbed, thereby being beneficial to reducing the damage of the oil cooler and the expansion pot and being beneficial to improving the durability of the cooling system. BRIEF DESCRIPTION OF DRAWINGS

[0015] Figure 1 is a schematic view of an embodiment of the cooling system for an aero-engine of the utility model;

[0016] Figure 2 is a schematic view of another perspective of the utility model. DETAILED DESCRIPTION

[0017] The following will be further described in detail through specific embodiments:

[0018] The reference signs in the drawings of the specification include: a pressure valve 1, an expansion pot 2, a support frame 3, a pipeline 4, an oil cooler 5, a mounting bracket 6, a shock-absorbing rubber pad 7, a cooling liquid inlet 8, a cooling liquid outlet 9, and an oil interface 10.

[0019] The embodiment is basically as shown in the accompanying drawings Figure 1 and Figure 2As shown: a cooling system for an aero-engine, comprising an oil cooler 5 for heat exchange between oil and coolant. In this embodiment, the coolant interface and the oil interface 10 of the oil cooler 5 are arranged on the side of the oil cooler 5. The coolant interface of the oil cooler 5 comprises a coolant inlet 8 and a coolant outlet 9. The coolant inlet 8 is used to connect with the exhaust pipe of the cooling channel of the engine. The oil interface 10 of the oil cooler 5 comprises an oil inlet and an oil outlet. In this embodiment, the oil cooler 5 is arranged in a flat shape, so that the height dimension of the oil cooler 5 is lower than the length and width dimensions, thereby reducing the height requirement of the oil cooler 5 for the installation space. In this embodiment, the side of the oil cooler 5 is provided with mounting brackets 6. The mounting brackets 6 are provided with three, of which two are distributed on one side of the oil cooler 5, and one is distributed on the opposite side. In this embodiment, shock-absorbing rubber pads 7 are arranged on the mounting brackets 6. Specifically, the shock-absorbing rubber pads 7 are embedded in the mounting holes of the mounting brackets 6.

[0020] The cooling system further comprises an expansion pot 2. In this embodiment, the expansion pot 2 is communicated with the coolant outlet 9 of the oil cooler 5 through the pipeline 4, so that the coolant in the oil cooler 5 can enter the expansion pot 2. The cooling system further comprises a pressure valve 1 communicated with the oil cooler 5. In this embodiment, the pressure valve 1 is connected to the top of the expansion pot 2, so that the pressure valve 1 is communicated with the oil cooler 5 through the expansion pot 2 and the pipeline 4. The bottom of the expansion pot 2 is connected with a support frame 3, and a rubber sheath is sleeved on the bottom of the expansion pot 2, which is located between the expansion pot 2 and the support frame 3.

[0021] The specific implementation process is as follows: during assembly, the oil cooler 5 is connected with the transmission case of the engine through the mounting brackets 6, such as being connected and fixed with the transmission case of the engine through bolts and shock-absorbing pads. The expansion pot 2 is connected and fixed on the engine through the support frame 3. During operation, the water pump of the cooling system forcibly drives the coolant to enter the cooling channel of the engine and then converges into the oil cooler 5. Part of the coolant exchanges heat with the oil in the oil cooler 5 and then converges into the expansion pot 2 together with another part of the coolant. The coolant flowing out of the expansion pot 2 is cooled and then circulated again. By adopting this scheme, the expansion pot 2 is arranged to be independently installed with the oil cooler 5, so that the design of the gas collecting chamber is omitted on the oil cooler 5, thereby greatly reducing the volume of the oil cooler 5, and in combination with arranging the coolant interface and the oil interface 10 on the side of the oil cooler 5, the requirement for the size of the installation space of the oil cooler 5 is greatly reduced, thereby the cooling system can be installed and used on different types of aero-engines, thereby improving the universality of the cooling system.

[0022] The above only is the embodiment of the present application, and the well-known specific structure and characteristics and other common knowledge in the scheme are not described in detail here. It should be pointed out that for those skilled in the art, without departing from the structure of the present application, a number of variations and improvements can be made, which should also be considered as the protection scope of the present application, and these will not affect the effect and practicality of the present application.

Claims

1. A cooling system for an aeroengine comprising an oil cooler for heat exchange between oil and coolant; further comprising a pressure valve in communication with the oil cooler; characterized in that: The cooling liquid interface and the lubricating oil interface of the oil cooler are arranged on the side of the oil cooler; an expansion pot is arranged and communicates with the cooling liquid outlet of the oil cooler through a pipeline.

2. A cooling system for an aeroengine according to claim 1, characterised in that: The oil cooler is arranged in a flat shape.

3. A cooling system for an aeroengine according to claim 2, wherein: The pressure valve is connected to the top of the expansion pot.

4. A cooling system for an aeroengine according to claim 3, characterised in that: The side of the oil cooler is provided with a mounting bracket, and a shock-absorbing rubber pad is arranged on the mounting bracket.

5. A cooling system for an aeroengine according to claim 4, characterised in that: The bottom of the expansion pot is connected with a support frame, and the bottom of the expansion pot is provided with a rubber sheath.

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