An aero-engine blade turnover detection tool

Abstract

The present application relates to a kind of aero-engine blade turnover detection tool, including base and the installation pipe fixed in its top, the top of the installation pipe is fixedly connected with the detection pipe being transversely arranged, the detection pipe is square tube, and the inside of detection pipe is movably provided with the regulating mechanism for adjusting the angle of aero-engine blade, the side of the detection pipe is provided with the air supply mechanism for simulating airflow;When the protruding end of the cylinder is in the shortest state, the output end of the external refrigerator is moved to the vicinity of the detection fan, the highest gear of the detection fan is turned on, so that the wind blowing to the front of aero-engine blade is relatively cold, it is convenient to simulate the environment of aero-engine blade operating in high temperature environment, whether the cold air has greater influence on aero-engine blade when contacting high temperature aero-engine blade, to improve the accuracy of detection data.

Description

Technical Field

[0001] This invention relates to the field of engine blade inspection technology, specifically to a tooling for inspecting the flipping of aero-engine blades.

[0002] Reflection technology

[0003] Aero engines are highly complex and precise thermodynamic machines. As the heart of an aircraft, they not only power flight but also serve as a vital driving force for the development of the aviation industry. Aero engine blades are an indispensable component, making their inspection particularly important. However, due to the special nature of engine blades, their high-temperature resistance and reliability under rapid temperature changes must be considered during use. Therefore, engine blades need to be tested under high-temperature conditions. Existing testing devices lack the ability to detect temperature changes in engine blades, necessitating a solution to address these technical challenges.

[0004] As described in the patent document with publication number CN115096558A, this device increases the ambient temperature of the test chamber by energizing the heating element, simulating whether the state of the engine blades is affected by different ambient temperatures. During the heating process, the fan is started, valve one is closed, and valve two is opened, allowing the hot air to flow rapidly and evenly, thus increasing the heating speed by quickly and evenly distributing the heat generated by the heating element within the inner wall of the test chamber. At this time, the engine blades are kept rotating, and the mounting plate is kept moving. After heating, an infrared thermometer located at the bottom of the mounting plate can measure the temperature at different positions of the engine blades, which can determine the temperature response of the engine blades when the temperature changes.

[0005] However, when an aircraft is in flight, the air temperature is lower at higher altitudes, and the aero-engine blades are at high temperatures. It is necessary to detect whether the cold air has a significant impact on the high-temperature aero-engine blades when it comes into contact with them. The aforementioned device does not provide a realistic environment for testing aero-engine blades, which affects the accuracy of the test data. In addition, the hot airflow in the aforementioned device is used to test the front of the aero-engine blades, which is not convenient for testing the back side, thus affecting the comprehensiveness of the test data. Summary of the Invention

[0006] The technical problem solved by this solution is:

[0007] (1) How to solve the problem of inspecting aero-engine blades in a more realistic environment and improving the accuracy of inspection data;

[0008] (2) How to solve the problem of ensuring the comprehensiveness of test data by inspecting both the front and back sides of the aero-engine blades.

[0009] The objective of this invention can be achieved through the following technical solution: an aero-engine blade flipping detection fixture, comprising a base and an mounting tube fixed on its top, wherein a horizontally arranged detection tube is fixedly connected to the top of the mounting tube, the detection tube is a square tube, and an adjustment mechanism for adjusting the angle of the aero-engine blade is movably arranged inside the detection tube, and an air supply mechanism for simulating airflow is arranged on one side of the detection tube.

[0010] The control mechanism includes a baffle, both the baffle and the mounting tube are made of heat-insulating material, and a ventilation hole is provided in the middle of the baffle. A bracket is fixedly installed on the baffle on one side of the ventilation hole, and a lever is fixedly installed on the top of the bracket. An L-shaped frame is rotatably provided on the inner wall of the detection tube via a pin. A connector for fixing the aero-engine blade is rotatably provided on the top of the L-shaped frame. The connector is existing technology. The bottom of the L-shaped frame is movably connected to the lever. A blocking unit for blocking airflow is provided at the end of the baffle near the air supply mechanism.

[0011] A further technical improvement of the present invention is that: a baffle plate is fixedly connected to the end of the baffle away from the blocking unit, and the baffle plate is slidably connected to the inner wall of the detection tube; when the extended end of the cylinder is in the shortest state, the baffle plate is disengaged from the detection tube, and at this time, the position of the ventilation hole corresponds to the position of the inner wall of the detection tube. At the same time, the plug is disengaged from the air outlet, and the highest setting of the detection fan is turned on, so that the airflow blown by the detection fan blows on the front of the aero-engine blade, and in conjunction with the airflow blowing on the back of the aero-engine blade, the front and back sides of the aero-engine blade are detected, thus ensuring the comprehensiveness of the detection data.

[0012] A further technical improvement of the present invention is that: the blocking unit includes a support frame fixedly connected to the baffle, a plug is fixedly installed on the top of the support frame, the bottom of the baffle is slidably connected to the inner wall of the detection tube through a slider, and the position of the slider corresponds to the position of the support frame.

[0013] A further technical improvement of the present invention is that: the air supply mechanism includes an air supply box fixedly connected to the base via a mounting seat; the air supply box has an air outlet on the side facing the detection tube; a detection fan is fixedly installed on the side wall of the air supply box away from the air outlet; an air outlet pipe is connected to the bottom of the air supply box; the output end of the air outlet pipe is connected to the bottom of the detection tube; when the cylinder is in its longest extended state, the baffle plate blocks the end of the detection tube away from the air outlet, and the electric heating tube and the detection fan are turned on to their lowest settings. At this time, the plug blocks the air outlet, and the air blown out by the detection fan is injected into the bottom of the detection tube through the air outlet pipe, so that the high-temperature gas inside the detection tube... Airflow blows through the ventilation holes toward the reverse side of the aero-engine blades, heating them and causing them to rotate in the opposite direction, thus simulating the real working environment of aero-engine blades. When the cylinder extension is at its shortest position, the output of the external refrigeration unit is moved near the testing fan, and the fan is turned on at its highest setting. This makes the air blowing onto the front of the aero-engine blades colder, simulating the high-temperature operating environment of the aero-engine blades. This allows for testing whether the cold air has a significant impact on the hot aero-engine blades, thereby improving the accuracy of the test data.

[0014] A further technical improvement of the present invention is that the position of the air outlet corresponds to the position of the plug, and the inner wall size of the air outlet is the same as the size of the plug.

[0015] A further technical improvement of the present invention is that: an installation plate is fixedly installed on the top of the base away from the air supply mechanism, and a cylinder is horizontally installed on the installation plate, with the extended end of the cylinder fixedly connected to the wind baffle plate.

[0016] Compared with the prior art, the beneficial effects of the present invention are:

[0017] In use, when the cylinder's extended end is at its longest position, the baffle plate blocks the end of the detection tube furthest from the air outlet. The electric heating tube and the detection fan are turned on to their lowest settings. At this time, the plug blocks the air outlet, and the air blown out by the detection fan is injected into the bottom of the detection tube through the air outlet pipe. This causes the high-temperature airflow inside the detection tube to blow towards the reverse side of the aero-engine blade through the ventilation hole, which heats the aero-engine blade and drives it to rotate in the opposite direction. When the cylinder's extended end is at its shortest position, the output end of the external refrigeration unit is moved to the vicinity of the detection fan, and the detection fan is turned on to its highest setting. This makes the air blown onto the front of the aero-engine blade colder, which is conducive to simulating the environment in which the aero-engine blade operates in a high-temperature environment. This allows for the detection of whether the cold air has a significant impact on the high-temperature aero-engine blade when it comes into contact with it, thereby improving the accuracy of the detection data.

[0018] When the cylinder is in its shortest position during use, the baffle plate is detached from the detection tube. At this time, the position of the ventilation hole corresponds to the position of the inner wall of the detection tube. Simultaneously, the plug is detached from the air outlet, and the detection fan is turned on to its highest setting. This allows the airflow from the detection fan to blow air onto the front of the aero-engine blade, in conjunction with blowing air onto the back of the aero-engine blade, thereby enabling the detection of both the front and back sides of the aero-engine blade and ensuring the comprehensiveness of the detection data. Attached Figure Description

[0019] To facilitate understanding by those skilled in the art, the present invention will be further described below with reference to the accompanying drawings.

[0020] Figure 1 This is a cross-sectional view of the overall structure of the present invention;

[0021] Figure 2 This is a schematic diagram of the control mechanism structure of the present invention;

[0022] Figure 3 This is a partial three-dimensional schematic diagram of the control mechanism structure of the present invention;

[0023] Figure 4 This is a schematic diagram of the air supply mechanism of the present invention;

[0024] Figure 5 For the present invention Figure 1 Enlarged view of the structure at point A in the middle.

[0025] In the diagram: 1. Placement ring; 2. Detection tube; 3. Cylinder; 4. Mounting plate; 5. Electric heating tube; 6. Mounting tube; 7. Base; 8. Air supply mechanism; 9. Control mechanism; 801. Air outlet; 802. Air outlet pipe; 803. Mounting seat; 804. Detection fan; 805. Air supply box; 901. Pin; 902. Baffle plate; 903. Baffle; 904. Ventilation hole; 905. Blocking unit; 906. Bracket; 907. L-shaped frame; 908. Lever; 9051. Plug; 9052. Support frame; 9053. Slider. Detailed Implementation

[0026] The technical solution of the present invention will be clearly and completely described below with reference to the embodiments. 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 of ordinary skill in the art without creative effort are within the scope of protection of the present invention.

[0027] Please see Figures 1-5As shown, an aero-engine blade flipping detection fixture includes a base 7 and an installation tube 6 fixed on its top. The top of the installation tube 6 is fixedly connected to a horizontally arranged detection tube 2. The detection tube 2 is a square tube, and the inside of the detection tube 2 is movably arranged with an adjustment mechanism 9 for adjusting the angle of the aero-engine blade. An air supply mechanism 8 for simulating airflow is arranged on one side of the detection tube 2.

[0028] Please see Figures 1-3 As shown, the aforementioned control mechanism 9 includes a baffle 903. Both the baffle 903 and the mounting pipe 6 are made of heat-insulating material. A ventilation hole 904 is provided in the middle of the baffle 903. A bracket 906 is fixedly installed on the baffle 903 on one side of the ventilation hole 904. A lever 908 is fixedly installed on the top of the bracket 906. An L-shaped frame 907 is rotatably provided on the inner wall of the detection pipe 2 via a pin 901. A connector for fixing the aero-engine blade is rotatably provided on the top of the L-shaped frame 907. The connector is existing technology. The bottom of the L-shaped frame 907 is movably connected to the lever 908. A blocking unit 905 for blocking airflow is provided at the end of the baffle 903 near the air supply mechanism 8.

[0029] Please see Figure 2 and Figure 3 As shown, the end of the baffle 903 away from the blocking unit 905 is fixedly connected to a baffle plate 902, which is slidably connected to the inner wall of the detection tube 2. When the extended end of the cylinder 3 is in its shortest state, the baffle plate 902 is disengaged from the detection tube 2. At this time, the position of the ventilation hole 904 corresponds to the position of the inner wall of the detection tube 2. At the same time, the plug 9051 is disengaged from the air outlet 801, and the highest setting of the detection fan 804 is turned on, so that the airflow blown by the detection fan 804 blows on the front of the aero-engine blade, and in conjunction with the airflow blowing on the back of the aero-engine blade, the front and back of the aero-engine blade are detected, thus ensuring the comprehensiveness of the detection data.

[0030] Please see Figure 2 and Figure 5 As shown, the blocking unit 905 includes a support frame 9052 fixedly connected to the baffle 903. A plug 9051 is fixedly installed on the top of the support frame 9052. The bottom of the baffle 903 is slidably connected to the inner wall of the detection tube 2 through a slider 9053. The position of the slider 9053 corresponds to the position of the support frame 9052.

[0031] Please see Figure 1 , Figure 4 and Figure 5As shown, the aforementioned air supply mechanism 8 includes an air supply box 805 fixedly connected to the base 7 via a mounting base 803. An air outlet 801 is provided on the side of the air supply box 805 facing the detection tube 2. The position of the air outlet 801 corresponds to the position of the plug 9051, and the inner wall size of the air outlet 801 is the same as that of the plug 9051. A detection fan 804 is fixedly installed on the side wall of the air supply box 805 away from the air outlet 801. An air outlet pipe 802 is connected to the bottom of the air supply box 805, and the output end of the air outlet pipe 802 is connected to the bottom of the detection tube 2. When the extended end of the cylinder 3 is in its longest state, the baffle plate 902 blocks the end of the detection tube 2 away from the air outlet 801, and the electric heating tube 5 and the detection fan 804 are turned on to their lowest setting. At this time, the plug 9051 blocks the air outlet 801, and the detection... The air blown out by the air testing fan 804 is injected into the bottom of the test tube 2 through the air outlet 802. This causes the high-temperature airflow in the test tube 2 to blow towards the reverse side of the aero-engine blade through the ventilation hole 904, which heats up the aero-engine blade and drives it to rotate in the opposite direction, thus simulating the real working environment of the aero-engine blade. When the extended end of the cylinder 3 is in its shortest state, the output end of the external refrigeration unit is moved to the vicinity of the air testing fan 804, and the air testing fan 804 is turned on at its highest setting. This makes the air blown onto the front of the aero-engine blade colder, which is conducive to simulating the operating environment of the aero-engine blade in a high-temperature environment. This allows for the detection of whether the cold air has a significant impact on the high-temperature aero-engine blade when it comes into contact with it, thereby improving the accuracy of the test data.

[0032] Please see Figure 1 As shown, a mounting plate 4 is fixedly installed on the top of the base 7 away from the air supply mechanism 8. A cylinder 3 is horizontally mounted on the mounting plate 4, and the extended end of the cylinder 3 is fixedly connected to the wind baffle 902.

[0033] Please see Figure 1 As shown, an electric heating tube 5 is fixedly installed in the middle of the inner wall of the aforementioned mounting tube 6. The electric heating tube 5 is existing technology.

[0034] Please see Figure 1 As shown, a placement ring 1 for facilitating the installation of aero-engine blades is fixedly installed at the top of the detection tube 2, corresponding to the position of the installation tube 6.

[0035] Working Principle: In use, the aero-engine blade to be tested is first fixedly mounted on the connector using external mounting equipment. When the extended end of cylinder 3 is at its longest position, the baffle plate 902 blocks the end of the detection tube 2 away from the air outlet 801. The electric heating tube 5 and the detection fan 804 are turned on to their lowest settings. At this time, the plug 9051 blocks the air outlet 801. The air blown out by the detection fan 804 is injected into the bottom of the detection tube 2 through the air outlet pipe 802. Then, the electric heating tube 5 heats the air inside the detection tube 2, causing the high-temperature airflow inside the detection tube 2 to blow towards the reverse side of the aero-engine blade through the ventilation hole 904. The airflow is ejected from the inside of the placement ring 1, which heats the aero-engine blade and simultaneously drives the aero-engine blade to rotate in the opposite direction, thus simulating the real working environment of the aero-engine blade. When the extended end of cylinder 3 is at its shortest position... In this state, the baffle plate 902 is detached from the detection tube 2. At this time, the position of the ventilation hole 904 corresponds to the position of the inner wall of the detection tube 2, preventing hot airflow from re-entering the detection tube 2. Simultaneously, the plug 9051 is detached from the air outlet 801, and the detection fan 804 is turned on to its highest setting, allowing the airflow blown by the detection fan 804 to blow on the front of the aero-engine blade. Combined with the aforementioned blowing on the back of the aero-engine blade, this achieves the function of detecting both the front and back of the aero-engine blade, ensuring the comprehensiveness of the detection data. At the same time, the output end of the external refrigeration unit is moved to the vicinity of the detection fan 804, making the air blown on the front of the aero-engine blade colder. This is to simulate the environment in which the aero-engine blade operates in a high-temperature environment, and to detect whether the cold air has a significant impact on the high-temperature aero-engine blade when it comes into contact with it, thereby improving the accuracy of the detection data.

[0036] To further illustrate the technical means and effects of the present invention in achieving its intended purpose, the following detailed description of the specific implementation methods, structures, features, and effects of the present invention, in conjunction with the accompanying drawings and preferred embodiments, is provided below.

[0037] The above description is merely a preferred embodiment of the present invention and is not intended to limit the present invention in any way. Although the present invention has been disclosed above with reference to preferred embodiments, it is not intended to limit the present invention. Any person skilled in the art can make some modifications or alterations to the above-disclosed technical content to create equivalent embodiments without departing from the scope of the present invention. Any simple modifications, equivalent changes and alterations made to the above embodiments based on the technical essence of the present invention without departing from the scope of the present invention shall still fall within the scope of the present invention.

Claims

1. A fixture for detecting the flipping of aircraft engine blades, comprising a base (7) and a mounting tube (6) fixed on its top, characterized in that: The top of the mounting tube (6) is fixedly connected to a horizontally arranged detection tube (2). The inside of the detection tube (2) is movably provided with a control mechanism (9) for adjusting the angle of the aero-engine blades. The side of the detection tube (2) is provided with an air supply mechanism (8) for simulating airflow. The control mechanism (9) includes a baffle (903), a ventilation hole (904) is provided in the middle of the baffle (903), a bracket (906) is fixedly installed on the baffle (903) on one side of the ventilation hole (904), a lever (908) is fixedly installed on the top of the bracket (906), an L-shaped frame (907) is rotatably provided on the inner wall of the detection tube (2), a connecting piece for fixing the aero-engine blade is rotatably provided on the top of the L-shaped frame (907), and the bottom of the L-shaped frame (907) is movably connected to the lever (908). A blocking unit (905) for blocking the airflow is provided at one end of the baffle (903) near the air supply mechanism (8). The end of the baffle (903) away from the blocking unit (905) is fixedly connected to a wind baffle (902), and the wind baffle (902) is slidably connected to the inner wall of the detection tube (2); The blocking unit (905) includes a support frame (9052) fixedly connected to the baffle (903), a plug (9051) is fixedly installed on the top of the support frame (9052), and the bottom of the baffle (903) is slidably connected to the inner wall of the detection tube (2).

2. The aero-engine blade flipping detection fixture according to claim 1, characterized in that, The air supply mechanism (8) includes an air supply box (805) fixedly connected to the base (7). The air supply box (805) has an air outlet (801) on the side facing the detection tube (2). A detection fan (804) is fixedly installed on the side wall of the air supply box (805) away from the air outlet (801). An air outlet pipe (802) is connected to the bottom of the air supply box (805). The output end of the air outlet pipe (802) is connected to the bottom of the detection tube (2).

3. The aero-engine blade flipping detection fixture according to claim 2, characterized in that, The position of the air outlet (801) corresponds to the position of the plug (9051), and the inner wall size of the air outlet (801) is the same as that of the plug (9051).

4. The aero-engine blade flipping detection fixture according to claim 1, characterized in that, An mounting plate (4) is fixedly installed on the top of the base (7) away from the air supply mechanism (8). A cylinder (3) is horizontally mounted on the mounting plate (4). The extended end of the cylinder (3) is fixedly connected to the wind baffle plate (902).

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