An auxiliary device and method for improving the starting success rate of an engine at high altitudes

Abstract

The present invention provides an auxiliary device for improving the success rate of engine starting at high altitudes, including a static and dynamic pressure tester connected to a high-altitude regulator through a connection mechanism. The connection mechanism includes an air extraction joint connected to the housing of the high-altitude regulator. The air extraction joint is in communication with the interior of the housing of the high-altitude regulator. The other end of the air extraction joint is connected to a hose, and the other end of the hose is connected to the static and dynamic pressure tester. A method for improving the success rate of starting an aero-engine at high altitudes is also provided. By adjusting the pressure in the atmosphere-venting chamber of the high-altitude regulator through the static and dynamic pressure tester, the tension of the pull spring is further adjusted, and the fuel return amount is further adjusted. Finally, the fuel supply amount during the engine starting process is controlled, so as to ensure an appropriate fuel supply amount for the engine, and finally enable the engine to start successfully.

Description

Technical Field

[0001] The present invention relates to the technical field of aero-engine control, and particularly relates to an auxiliary device and method for improving the starting success rate of an engine at high altitudes. Background Art

[0002] For a gas turbine type aero-engine, the fuel supply amount during its starting process is regulated by a fuel pump regulator installed on this type of engine according to the gas pressure after the high-pressure compressor. As the altitude of the airport increases, the air becomes thinner, and the intake air volume of the engine decreases with the increase in altitude. If the fuel supply amount is still regulated according to the original control law, there may be a phenomenon that the combustion chamber is rich in fuel, resulting in engine overheating or thermal hang-up, and ultimately leading to the failure of engine starting.

[0003] In order to solve the above problems that may occur during the high-altitude starting of this type of engine, a high-altitude regulator is designed on the fuel pump regulator. The high-altitude regulator can automatically reduce the engine fuel supply amount according to the increase in the altitude of the airport, so as to ensure the normal starting of the engine. This starting regulator adjusts the opening degree of the oil return valve at any time according to the changes in oil pressure and gas pressure, controls the size of the oil return amount, and makes the starting fuel supply amount match the starting fuel demand amount. During the actual high-altitude starting process of the engine, it is relatively easy to have a phenomenon of thermal hang-up, resulting in the failure of engine starting. This phenomenon is mainly caused by excessive fuel supply. Therefore, it is very difficult to judge its working stability and accuracy, and it is thus very difficult to ensure the starting success rate at high-altitude airports. Summary of the Invention

[0004] In view of this, the present invention provides an auxiliary device and method for improving the starting success rate of an engine at high altitudes. By adjusting the pressure of the atmosphere chamber of the high-altitude regulator through a static and dynamic pressure tester, the appropriate fuel supply amount of the engine is ensured, and ultimately the engine starts successfully.

[0005] To solve the above technical problems, the present invention provides an auxiliary device for improving the starting success rate of an engine at high altitudes, including a static and dynamic pressure tester connected to a high-altitude regulator through a connection mechanism. The connection mechanism includes an air extraction joint connected to the housing of the high-altitude regulator. The air extraction joint is connected to the inside of the housing of the high-altitude regulator, and the other end of the air extraction joint is connected to a hose, and the other end of the hose is connected to the static and dynamic pressure tester.

[0006] Further, the air extraction joint includes a tubular joint body. One end of the joint body is a threaded end, and a threaded hole communicating with the inside is provided on the housing of the high-altitude regulator, and the threaded end is adapted to the threaded hole.

[0007] Further, the other end of the joint body is a connection end, and a plurality of convex rings are arranged on the connection end. One side of the convex ring facing the end of the connection end is an inclined surface, and one side of the convex ring facing the middle of the joint body is perpendicular to the axis of the joint body.

[0008] Further, the hose is made of an elastic material, and the inner diameter of the hose is smaller than the maximum diameter of the convex ring.

[0009] Further, the hose is made of rubber.

[0010] Further, a rotating disk is arranged in the middle of the joint body, and anti-slip lines are arranged on the edge of the rotating disk.

[0011] The method for improving the starting success rate of an aeroengine at high altitudes includes the following steps:

[0012] Adjust the pressure of the atmosphere passage of the altitude regulator through a static and dynamic pressure tester, thereby adjusting the tension of the pull spring, further adjusting the fuel return amount, and finally controlling the fuel supply amount during the engine starting process until the engine starts successfully.

[0013] Further, if the engine has a hot hang, that is, the exhaust temperature rises rapidly while the speed does not rise, it indicates that the engine is rich in fuel. Without adjusting the engine adjustment point, by operating the static and dynamic pressure tester, reduce the pressure of the atmosphere passage of the altitude regulator on the basis of the local atmospheric pressure until the engine starts successfully.

[0014] Further, the pressure of the atmosphere passage of the altitude regulator is gradually reduced. First, reduce it by 1000 Pa and test whether the engine can start successfully. If it starts successfully, the pressure of the atmosphere passage will no longer be adjusted; if the engine still has a hot hang during the starting process, continue to reduce it by 1000 Pa, and so on until the engine starts successfully.

[0015] Further, if the engine has a cold hang, that is, the exhaust temperature does not rise and the speed does not rise, it indicates that the engine is lean in fuel. Without adjusting the engine adjustment point, by operating the static and dynamic pressure tester, increase the pressure of the atmosphere passage of the altitude regulator on the basis of the local atmospheric pressure until the engine starts successfully.

[0016] Further, the pressure of the atmosphere passage of the altitude regulator is gradually increased. First, increase it by 1000 Pa and test whether the engine can start successfully. If it starts successfully, the pressure of the atmosphere passage will no longer be adjusted; if the engine still has a cold hang during the starting process, continue to increase it by 1000 Pa, and so on until the engine starts successfully.

[0017] The beneficial effects of the above technical solutions of the present invention are as follows:

[0018] After the static and dynamic pressure tester is connected to the inside of the high-altitude regulator through the connecting mechanism, the pressure in the atmosphere chamber of the high-altitude regulator can be increased or decreased through the static and dynamic pressure tester. According to the engine state judgment, it is selected to increase or decrease, so as to assist the engine to start successfully.

[0019] In addition, the connecting mechanism adopts an air extraction joint, and both ends of the joint have different structures. One end is a threaded end for the high-altitude regulator, and the other end is a connecting end for fixing the hose. The whole auxiliary device is convenient to disassemble and assemble and flexible to use. Brief Description of the Drawings

[0020] Figure 1 It is a schematic structural diagram of the auxiliary device for improving the high-altitude starting success rate of the engine of the present invention

[0021] 1. Static and dynamic pressure tester; 2. Hose; 3. Convex ring; 4. Connecting end; 5. Rotating disk; 6. Anti-slip pattern; 7. Threaded end; 8. Threaded hole; 9. High-altitude regulator; 10. Housing. Detailed Embodiments

[0022] For the purposes, technical solutions and advantages of the embodiments of the present invention to be more clear, the following will be combined with the accompanying drawings of the embodiments of the present invention Figure 1 , the technical solutions of the embodiments of the present invention will be clearly and completely described. Obviously, the described embodiments are part of the embodiments of the present invention, rather than all of the embodiments. Based on the described embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art belong to the scope of protection of the present invention.

[0023] Embodiment 1

[0024] As Figure 1 shown:

[0025] This embodiment provides an auxiliary device for improving the high-altitude starting success rate of an engine, including a static and dynamic pressure tester 1 connected to a high-altitude regulator 9 through a connecting mechanism. The connecting mechanism includes an air extraction joint connected to the housing 10 of the high-altitude regulator 9. The air extraction joint is connected to the inside of the housing 10 of the high-altitude regulator 9, and the other end of the air extraction joint is connected to a hose 2, and the other end of the hose 2 is connected to the static and dynamic pressure tester 1.

[0026] Specifically, after the static and dynamic pressure tester 1 is connected to the atmosphere chamber of the high-altitude regulator 9 through the connecting mechanism, the internal air pressure can be adjusted through the static and dynamic pressure tester 1. The connecting mechanism includes an air extraction joint and a hose 2. The air extraction joint is connected to the inside of the housing 10 of the high-altitude regulator 9, and the use of the hose 2 makes the installation and operation more flexible.

[0027] According to an embodiment of the present invention, as Figure 1 shown,

[0028] The air extraction joint includes a tubular joint body, one end of which is a threaded end 7. A threaded hole 8 communicating with the interior is provided on the shell 10 of the altitude regulator 9, and the threaded end 7 is adapted to the threaded hole 8. The air extraction joint is a joint body of a tubular structure, and in order to communicate with the altitude regulator 9, a threaded end 7 is provided at one end thereof, and a threaded hole 8 is provided on the altitude regulator 9. The threaded end 7 is screwed into the threaded hole 8 by rotation, so as to realize the communication between the dynamic and static pressure tester 1 and the altitude regulator 9. In addition, the threaded hole 8 can be blocked by a rubber plug when not in use.

[0029] According to one embodiment of the present invention, Figure 1 As shown,

[0030] The other end of the connector body is a connection end 4, on which a plurality of convex rings 3 are arranged, and the side of the convex ring 3 facing the end of the connection end 4 is an inclined surface, and the side of the convex ring 3 facing the middle of the connector body is perpendicular to the axis of the connector body. The hose 2 is made of elastic material, and the inner diameter of the hose 2 is smaller than the maximum diameter of the convex ring 3.

[0031] This device emphasizes flexible installation, so the other end of the connector body needs to be able to flexibly fix the hose 2, and four convex rings 3 are set on the connection end 4, of course, it can also be three or other numbers. The structure of the convex ring 3 is annular and is set around the connection end 4. Because of its specific structure, the convex ring 3 makes it easier to put the hose 2 inward, but when it is pulled outward, the convex ring 3 can grasp the inner wall of the hose 2. In addition, the gripping force can meet the work needs, but when it needs to be removed, it will not cause damage to the hose 2 even if it is directly pulled hard. In addition, in order to cooperate with the connection end 4, the hose 2 is made of elastic material, and the inner diameter of the hose 2 is smaller than the maximum diameter of the convex ring 3, so that the hose 2 can be elastically hugged after being put on the connection end 4.

[0032] According to one embodiment of the present invention, Figure 1 As shown,

[0033] The hose 2 is made of rubber material, preferably rubber material, which has better wear resistance and longer service life.

[0034] In one embodiment of the present invention, Figure 1 As shown,

[0035] A rotating disk 5 is arranged in the middle of the joint body, and anti-slip grooves 6 are arranged on the edge of the rotating disk 5. The rotating disk 5 is arranged to facilitate the rotation of the joint body.

[0036] In one embodiment of the present invention,

[0037] A method for improving the success rate of high-altitude starting of an aircraft engine is also provided, comprising the following steps:

[0038] Adjust the pressure of the air chamber communicating with the atmosphere of the altitude regulator 9 through the hydrostatic tester 1, thereby adjusting the spring force, further adjusting the oil return amount, and finally controlling the fuel supply amount during the engine starting process until the engine starts successfully.

[0039] If the engine has a hot hang-up, that is, the exhaust temperature rises rapidly while the speed does not rise, it indicates that the engine is rich in fuel. Without adjusting the engine adjustment point, by operating the hydrostatic tester 1, reduce the pressure of the air chamber communicating with the atmosphere of the altitude regulator 9 based on the local atmospheric pressure until the engine starts successfully.

[0040] Gradually reduce the pressure of the air chamber communicating with the atmosphere of the altitude regulator 9. First, reduce it by 1000 Pa in the first step and test whether the engine can start successfully. If it starts successfully, no further adjustment is made to the pressure of the air chamber communicating with the atmosphere; if there is still a hot hang-up during the starting process, continue to reduce it by 1000 Pa, and so on until the engine starts successfully.

[0041] If the engine has a cold hang-up, that is, the exhaust temperature does not rise and the speed does not rise, it indicates that the engine is lean in fuel. Without adjusting the engine adjustment point, by operating the hydrostatic tester 1, increase the pressure of the air chamber communicating with the atmosphere of the altitude regulator 9 based on the local atmospheric pressure until the engine starts successfully.

[0042] Gradually increase the pressure of the air chamber communicating with the atmosphere of the altitude regulator 9. First, increase it by 1000 Pa in the first step and test whether the engine can start successfully. If it starts successfully, no further adjustment is made to the pressure of the air chamber communicating with the atmosphere; if there is still a cold hang-up during the starting process, continue to increase it by 1000 Pa, and so on until the engine starts successfully.

[0043] In the present invention, unless otherwise clearly specified and limited, for example, it can be a fixed connection, a detachable connection, or integrated; it can be a mechanical connection or an electrical connection; it can be directly connected or indirectly connected through an intermediate medium, and it can be the communication inside two components or the interaction relationship between two components. Unless otherwise clearly limited, for those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood according to specific situations.

[0044] The above is the preferred embodiment of the present invention. It should be noted that for those of ordinary skill in the technical field, without departing from the principle described in the present invention, several improvements and refinements can still be made, and these improvements and refinements should also be regarded as the protection scope of the present invention.

Claims

1. A method for improving the success rate of high-altitude starting of an aero-engine, characterized in that: This method is based on an auxiliary device for improving the success rate of starting an aero-engine at high altitudes. The device includes a static and dynamic pressure tester (1) connected to a high-altitude regulator (9) through a connecting mechanism. The connecting mechanism includes an air extraction joint connected to the housing (10) of the high-altitude regulator (9). The air extraction joint is internally connected to the housing (10) of the high-altitude regulator (9). The other end of the air extraction joint is connected to a hose (2), and the other end of the hose (2) is connected to the static and dynamic pressure tester (1). The method for improving the success rate of starting an aero-engine at high altitudes is as follows: Adjust the pressure of the atmosphere-venting chamber of the high-altitude regulator (9) through the static and dynamic pressure tester (1), thereby adjusting the tension spring force, further adjusting the fuel return amount, and finally controlling the fuel supply amount during the engine starting process until the engine starts successfully.

2. The method for improving the high-altitude starting success rate of an aero-engine according to claim 1, characterized in that: The air extraction joint includes a tubular joint body. One end of the joint body is a threaded end (7). A threaded hole (8) connected to the interior is provided on the housing (10) of the high-altitude regulator (9), and the threaded end (7) is adapted to the threaded hole (8).

3. The method for improving the high-altitude starting success rate of an aeroengine according to claim 2, characterized in that: The other end of the joint body is a connecting end (4). A number of convex rings (3) are arranged on the connecting end (4). One side of the convex ring (3) facing the end of the connecting end (4) is an inclined surface, and the side of the convex ring (3) facing the middle of the joint body is perpendicular to the axis of the joint body.

4. The method for improving the high-altitude starting success rate of an aeroengine according to claim 3, characterized in that: The hose (2) is made of an elastic material, and the inner diameter of the hose (2) is smaller than the maximum diameter of the convex ring (3).

5. The method for improving the high-altitude starting success rate of an aeroengine according to claim 4, characterized in that: A rotating disk (5) is provided in the middle of the joint body, and anti-slip lines (6) are provided on the edge of the rotating disk (5).

6. The method for improving the high-altitude starting success rate of an aeroengine according to any one of claims 1 to 5, characterized in that: If the engine has a hot hang-up, that is, the exhaust temperature rises rapidly while the speed does not rise, it indicates that the engine is rich in fuel. Without adjusting the engine adjustment point, by operating the static and dynamic pressure tester (1), on the basis of the local atmospheric pressure, reduce the pressure of the atmosphere-venting chamber of the high-altitude regulator (9) until the engine starts successfully.

7. The method for improving the high-altitude starting success rate of an aeroengine according to claim 6, characterized in that: The pressure of the atmosphere-venting chamber of the high-altitude regulator (9) is gradually reduced. First, reduce it by 1000 Pa in the first step to test whether the engine can start successfully. If it starts successfully, the pressure of the atmosphere-venting chamber will no longer be adjusted; if there is still a hot hang-up during the starting process, continue to reduce it by 1000 Pa, and so on until the engine starts successfully.

8. The method for improving the high-altitude starting success rate of an aero-engine according to claim 7, characterized in that: If the engine has a cold hang-up, that is, the exhaust temperature does not rise and the speed does not rise, it indicates that the engine is lean in fuel. Without adjusting the engine adjustment point, by operating the static and dynamic pressure tester (1), on the basis of the local atmospheric pressure, increase the pressure of the atmosphere-venting chamber of the high-altitude regulator (9) until the engine starts successfully.

9. The method for improving the high-altitude starting success rate of an aeroengine according to claim 8, characterized in that: The pressure of the atmosphere-venting chamber of the high-altitude regulator (9) is gradually increased. First, increase it by 1000 Pa in the first step to test whether the engine can start successfully. If it starts successfully, the pressure of the atmosphere-venting chamber will no longer be adjusted; if there is still a cold hang-up during the starting process, continue to increase it by 1000 Pa, and so on until the engine starts successfully.

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