A control valve structure for an emergency lubrication system of an aircraft engine

Abstract

The utility model discloses a control valve structure of an emergency lubrication system of an aircraft engine, comprising a shell, a guide sleeve and a valve, a valve channel is arranged in the shell, the guide sleeve is slidably connected with the inner wall of the valve channel, the valve is arranged at the upper end of the guide sleeve, an air inlet is arranged at the upper end of the shell, the valve corresponds to the air inlet and forms a conical contact seal, an outlet is arranged on the upper side of the shell, an oil inlet is arranged on the lower side of the shell, the oil inlet is connected with a lubricating oil pump through a pipeline, the outlet is connected with an emergency oil tank through a pipeline, the guide sleeve and the valve are connected by threads, a sealing gasket is arranged between the guide sleeve and the valve, and the sealing gasket contacts the inner wall of the shell; by controlling the opening and closing of the valve, the control valve can quickly respond to changes in the state of the lubrication system of the aircraft engine, and when the main lubrication system fails or the pressure is insufficient, the control valve can be quickly opened to start the emergency lubrication system to ensure timely supply of lubricating oil.

Description

Technical Field

[0001] The utility model relates to the technical field of control valves, in particular to a control valve structure for an emergency lubrication system of an aircraft engine. Background Art

[0002] During operation, aircraft engines require a lubrication system to lubricate the transmission parts of the engine. When the aircraft engine is operating normally, it relies on the main lubrication system for lubrication; when there is an abnormal condition such as a failure of the main lubrication system or too low oil pump pressure, the aircraft engine is in an emergency state and requires an emergency lubrication system for lubrication. In addition to the main lubrication system, traditional engines also require a spare system to solve the emergency lubrication problem, which increases the complexity of the system and the quality of the whole machine; Patent Publication No. CN113090392B This patent mainly focuses on the oil return and ventilation system of the aircraft engine, and its core technology involves the flow of lubricating oil and the optimization of the ventilation system; although it also involves fluid control, it does not directly involve how to control the opening and closing of the emergency lubrication system; for this reason, there is an urgent need for a control valve structure that can stably and reliably control the opening and closing of the emergency lubrication system, so as to reduce a system for the engine to achieve the purpose of weight reduction and load reduction. Utility Model Content

[0003] The technical problem to be solved by the utility model is to overcome the existing defects and provide a control valve structure for an emergency lubrication system of an aircraft engine. By controlling the opening and closing of a valve, the control valve can quickly respond to changes in the state of the lubrication system of the aircraft engine. When the main lubrication system fails or the pressure is insufficient, the control valve can be quickly opened to start the emergency lubrication system to ensure timely supply of lubricating oil, thereby avoiding wear or damage to internal engine parts caused by insufficient lubrication, and can effectively solve the problems in the background technology.

[0004] To achieve the above-mentioned purpose, the utility model provides the following technical solutions: a control valve structure of an aircraft engine emergency lubrication system, comprising a shell, a guide sleeve and a valve, a valve channel is arranged in the shell, the guide sleeve is slidably connected to the inner wall of the valve channel, the valve is arranged at the upper end of the guide sleeve, an air inlet is arranged at the upper end of the shell, the valve corresponds to the air inlet and forms a conical contact seal, an outlet is arranged on the upper side of the shell, an oil inlet is arranged on the lower side of the shell, the oil inlet is connected to a lubricating oil pump through a pipeline, and the outlet is connected to an emergency oil tank through a pipeline.

[0005] Furthermore, the guide sleeve and the valve are connected by threads, a sealing gasket is provided between the guide sleeve and the valve, and the sealing gasket contacts the inner wall of the shell.

[0006] Furthermore, an outer sealing ring is arranged on the outer circumference of the shell, and three outer sealing rings are arranged, which are respectively located above the outlet, between the outlet and the oil inlet, and below the oil inlet.

[0007] Furthermore, a boss is provided below the guide sleeve, and a movable sealing ring is provided between the guide sleeve and the inner wall of the shell.

[0008] Furthermore, a fixing platform is provided below the shell, and fixing holes are provided in the circumferential direction of the fixing platform.

[0009] Compared with the prior art, the beneficial effects of the utility model are:

[0010] 1. The control valve can be opened or closed by automatically sensing whether the main lubrication system of the aircraft engine is faulty. The control valve is small in size, light in weight, and has a simple and reliable installation method. It can combine the main lubrication system with the emergency lubrication system, thereby improving the engine utilization rate. The operation is simple, and the control is stable and reliable. In addition, the sealing structure of the control valve adopts the sealing form of a valve and a sealing gasket, which can effectively seal the air, is reliable in sealing, and has a compensation function.

[0011] 2. The control valve structure adopts a simple and efficient design, avoiding the more complex mechanical or hydraulic control mechanism in traditional designs; this not only reduces the complexity and manufacturing cost of the system, but also facilitates subsequent maintenance and inspection; aircraft engine maintenance personnel can detect and repair the lubrication system more quickly and conveniently, reducing downtime and improving aircraft operating efficiency. BRIEF DESCRIPTION OF THE DRAWINGS

[0012] Figure 1 It is a schematic diagram of the structure of the utility model;

[0013] Figure 2 This is a schematic diagram showing the application of the utility model in a normal state;

[0014] Figure 3 This is a schematic diagram of the application of the utility model in an emergency state.

[0015] In the figure: 1 housing, 2 valve, 3 sealing gasket, 4 guide sleeve, 5 movable sealing ring, 6 outer sealing ring, 7 outlet, 8 oil inlet, 9 fixing hole, 10 fixing platform, 11 air inlet, 12 valve channel, 13 boss. DETAILED DESCRIPTION

[0016] In the description of the present invention, it should be understood that the terms "longitudinal", "lateral", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside" and "outside" etc., indicating orientations or positional relationships, are based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as a limitation on the present invention. Example 1

[0017] See also Figure 1-3 The utility model provides a technical solution: a control valve structure of an emergency lubrication system of an aircraft engine, comprising a housing 1, a guide sleeve 4 and a valve 2, a valve channel 12 is arranged in the housing 1, the guide sleeve 4 is slidably connected to the inner wall of the valve channel 12, the valve 2 is arranged at the upper end of the guide sleeve 4, an air inlet 11 is arranged at the upper end of the housing 1, the air inlet 11 is connected to the bearing cavity sealing air, the valve 2 corresponds to the air inlet 11, and a conical contact seal is formed, an outlet 7 is arranged on the upper side of the housing 1, an oil inlet 8 is arranged on the lower side of the housing 1, the oil inlet 8 is connected to a lubricating oil pump through a pipeline, the lubricating oil pump is connected to a main lubrication system through a pipeline, the outlet 7 is connected to an emergency oil tank through a pipeline, and the emergency oil tank is connected to a main lubrication nozzle of the main lubrication system through an oil injection one-way valve.

[0018] As attached Figure 2 As shown, when the aircraft engine is in normal working condition, the lubricating oil pump supplies oil, the main lubrication system operates normally, the pressure on the oil inlet 8 is greater than the pressure on the air inlet 11, the valve 2 is upward and in a sealed state, the control valve valve is in a closed state, and the emergency lubrication system is closed;

[0019] As attached Figure 3 As shown, the emergency oil tank is connected to the emergency lubrication nozzle of the emergency lubrication system through the emergency injection pipeline. When the aircraft engine is in an emergency state, the lubricating oil pump pressure is reduced or no oil is supplied, the main lubrication system fails, and the pressure on the lubricating oil side of the oil inlet 8 is reduced to less than the air side pressure of the air inlet 11, the valve 2 opens downward, and the air enters the emergency injection pipeline through the outlet 7 of the valve, and the emergency lubrication system is turned on.

[0020] When the emergency state of the aircraft engine is lifted, the lubricating oil pump resumes normal oil supply, the main lubrication system resumes normal operation, the pressure on the lubricating oil side is restored to be greater than the pressure on the air side, valve 2 of the control valve is closed, and the emergency lubrication system is closed.

[0021] The guide sleeve 4 is connected to the valve 2 by means of threads. A sealing gasket 3 is arranged between the guide sleeve 4 and the valve 2. The sealing gasket 3 contacts the inner wall of the shell 1. The valve 2 can also prevent the sealing gasket 3 from being deformed due to extrusion, and can effectively seal the air. The sealing is reliable and has a compensation function. The sealing gasket 3 further improves the sealing performance of the valve 2.

[0022] The outer circumference of the housing 1 is provided with an outer sealing ring 6. Three outer sealing rings 6 are provided, which are respectively located above the outlet 7, between the outlet 7 and the oil inlet 8, and below the oil inlet 8, so as to achieve sealing connected to the equipment and make the outlet 7 and the oil inlet 8 completely sealed.

[0023] A boss 13 is provided below the guide sleeve 4. The boss 13 leaves a cavity between the guide sleeve 4 and the bottom of the valve channel 12 to facilitate the entry of oil, forming a pressure chamber to provide pressure for the guide sleeve 4. A movable sealing ring 5 is provided between the guide sleeve 4 and the inner wall of the housing 1 to ensure the sealing of the sliding connection between the guide sleeve 4 and the housing 1, thereby ensuring stable operation of the control valve.

[0024] A fixing platform 10 is arranged below the housing 1 , and fixing holes 9 are arranged in the circumferential direction of the fixing platform 10 , and the fixing holes 9 are used for connection with equipment.

[0025] During installation, the housing 1 is connected to the aircraft engine's oil pump, main lubrication system and emergency oil tank through pipelines; the oil inlet 8 is connected to the oil pump to ensure normal oil supply to the main lubrication system; the outlet 7 is connected to the emergency oil tank through a pipeline to ensure that the emergency lubrication system can be quickly started when problems occur in the main system.

[0026] The basic principles, main features and advantages of the present invention are shown and described above. Without departing from the spirit and scope of the present invention, the present invention may also be subject to various changes and improvements, which are all within the scope of the present invention to be protected.

Claims

1. A control valve structure for an emergency lubrication system of an aircraft engine, comprising a housing (1), a guide sleeve (4) and a valve (2), characterized in that: A valve channel (12) is arranged in the housing (1), the guide sleeve (4) is slidably connected to the inner wall of the valve channel (12), the valve (2) is arranged at the upper end of the guide sleeve (4), an air inlet (11) is arranged at the upper end of the housing (1), the valve (2) corresponds to the air inlet (11), and a conical contact seal is formed, an outlet (7) is arranged on the upper side of the housing (1), an oil inlet (8) is arranged on the lower side of the housing (1), the oil inlet (8) is connected to a lubricating oil pump through a pipeline, and the outlet (7) is connected to an emergency oil tank through a pipeline.

2. The control valve structure of an aircraft engine emergency lubrication system according to claim 1, characterized in that: The guide sleeve (4) and the valve (2) are connected by means of threads, a sealing gasket (3) is provided between the guide sleeve (4) and the valve (2), and the sealing gasket (3) is in contact with the inner wall of the housing (1).

3. The control valve structure of an aircraft engine emergency lubrication system according to claim 1, characterized in that: An outer sealing ring (6) is provided on the outer circumference of the housing (1), and three outer sealing rings (6) are provided, which are respectively located above the outlet (7), between the outlet (7) and the oil inlet (8), and below the oil inlet (8).

4. The control valve structure of an aircraft engine emergency lubrication system according to claim 1, characterized in that: A boss (13) is provided below the guide sleeve (4), and a movable sealing ring (5) is provided between the guide sleeve (4) and the inner wall of the housing (1).

5. The control valve structure of an aircraft engine emergency lubrication system according to claim 1, characterized in that: A fixing platform (10) is provided below the housing (1), and fixing holes (9) are provided in a circumferential direction of the fixing platform (10).

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