Water flow experiment device for inner cavity of aero-engine blade

Abstract

The invention discloses an aero-engine blade inner cavity water flow experiment device, which comprises a hydraulic system and a mechanical system, and is characterized in that the hydraulic system is provided with a water tank, the water tank is connected to a water absorption filter through a pipeline, the water absorption filter is shunted to a manual ball valve, and the manual ball valve is connected to a high-pressure centrifugal pump and a low-pressure centrifugal pump respectively; the high-pressure centrifugal pump is connected to the needle valve, the needle valve is used for shunting, one end of the needle valve is connected to the energy accumulator, the flow meter is connected to the pressure transmitter and then connected with the pilot-operated type two-position two-way valves, and the pilot-operated type two-position two-way valves are symmetrically arranged. Through the effect of the automatic assembly, the automatic measurement of the water flow of the high-pressure turbine blade of the aero-engine is realized. Except that the blades need to be manually placed on the measuring clamp one by one, the other processes are completed by the machine, and the automation rate is high.

Description

Technical Field

[0001] The present invention relates to the technical field of water flow measurement in the inner cavity of high-pressure turbine blades of aero-engines, and particularly to an experimental device for water flow in the inner cavity of aero-engine blades. Background Art

[0002] This tester is used to measure the water flow in the inner cavity of the high-pressure turbine blade of the engine. Using water as the working fluid, under the conditions of constant temperature and constant pressure, it is injected into the air inlet hole at the bottom of the tenon of the high-pressure turbine blade with a certain pressure, and then, under the stable state, the water flow flowing through the inner cavity of the high-pressure turbine blade and flowing out through the air film holes and / or exhaust slits of the blade body is measured. Based on this, it is judged whether the part meets the flow specified value of the process technical requirements, ensuring the flow capacity of the cooling air in the inner cavity of the blade, ensuring the consistency of production quality, and at the same time avoiding the influence of abnormal inner cavity structures (such as foreign object blockage, residual core, solder flow) on the use of the blade.

[0003] In the prior art, the measurement of the water flow in the inner cavity of the high-pressure turbine blade of an aero-engine is mainly detected by using a test bench composed of a simple tooling and a water pump. The disadvantages of this method are as follows: manual operation one by one, with great difficulty for personnel operation, long time consumption, and inaccurate manual data recording, which cannot meet the use requirements. Summary of the Invention

[0004] In order to overcome the deficiencies of the prior art, the present invention provides a device for water flow in the inner cavity of a high-pressure turbine blade of an aero-engine with high repeatability, high automation degree, and high detection efficiency.

[0005] An experimental device for water flow in the inner cavity of aero-engine blades includes a hydraulic system and a mechanical system. The hydraulic system is provided with a water tank, the water tank is connected to a suction filter through a pipeline, the suction filter is branched to a manual ball valve, the manual ball valve is respectively connected to a high-pressure centrifugal pump and a low-pressure centrifugal pump, the high-pressure centrifugal pump is connected to a needle valve, the needle valve is branched, one end is connected to an accumulator, the other end is connected to a pressure relief valve, the low-pressure centrifugal pump is connected to the accumulator, the accumulator is connected to a filter, behind the filter there is a flow meter, the flow meter is connected to a pressure transmitter and then connected to a pilot-operated two-way two-position valve. The pilot-operated two-way two-position valve is symmetrically arranged, with a detection fixture in the middle. After passing through the pilot-operated two-way two-position valve, it is connected to a sealed measurement chamber.

[0006] Further, check valves are arranged between the high-pressure centrifugal pump and the low-pressure centrifugal pump and the accumulator.

[0007] Further, the sealed measurement chamber is branched to two direct-acting valves. One of the direct-acting valves is connected to a weighing water tank, the weighing water tank is connected to a return water filter, the other direct-acting valve is directly connected to the return water filter, the return water filter is connected to the pressure relief valve, and the needle valve and the check valve on the pipeline of the low-pressure centrifugal pump are connected to the pressure relief valve through a pipeline after merging.

[0008] Further, the other end of the water tank is connected to a ball valve, and a temperature sensor and a liquid level gauge are arranged between the water tank and the ball valve.

[0009] Further, the mechanical system is provided with an equipment bed body, a table top is arranged on the top of the equipment bed body, a detection fixture is installed on the surface of the table top, a blade positioning and sealing unit is arranged above the center of the detection fixture, the blade positioning and sealing unit is connected to a sealing measurement cavity, a protective cover is arranged outside the table top, and an operation interface is arranged beside the protective cover.

[0010] Further, the detection fixture is a forty-equal division unit. The center of the forty-equal division unit is a disc structure, the outer edge of the disc is equally divided into forty parts, and each part is provided with a blade fixture. The detection fixture is driven by a servo motor in cooperation with a planetary reducer.

[0011] Further, the sealing measurement cavity is a rectangular frame structure, and is sealed with a silicone rubber gasket between the table top. Windows are opened on both sides and the top surface of the sealing measurement cavity, transparent acrylic is installed, and a hydrophobic film is pasted.

[0012] Further, a water isolation ring is also arranged at the lower end of the sealing measurement cavity on the surface of the table top, a water accumulation collection and reflux groove is arranged outside the water isolation ring, and a water collection and reflux groove is also arranged beside the water isolation ring. Further, the flowmeter is connected to a pressure stabilizing tank, and a heating device is also arranged at the front end of the flowmeter.

[0013] Advantages of the present invention: 1. High degree of automation. In this application, the automatic rotation and positioning technology of the equal division unit is introduced for feeding, and through the action of automatic components, the automatic measurement of the water flow of the high-pressure turbine blade of the aero-engine is realized. Except for manually placing the blades one by one on the measurement fixture, the rest of the process is completed by the machine, and the automation rate is high.

[0014] 2. High measurement accuracy and test efficiency. High-precision weighing sensors, pressure sensors and flowmeters are used, effectively improving the accuracy of the test results. The equipment tests each blade through a beat, reducing the test cycle and improving the test efficiency. Description of the Drawings

[0015] Figure 1 is a hydraulic system control schematic diagram of an experimental device for the water flow in the inner cavity of an aero-engine blade; Figure 2 is a structural diagram of the mechanical system of a hydraulic system of an experimental device for the water flow in the inner cavity of an aero-engine blade In the figure: 1 - water tank, 2 - suction filter, 3 - manual ball valve, 4 - high-pressure centrifugal pump, 5 - low-pressure centrifugal pump, 6 - check valve, 7 - needle valve, 8 - accumulator, 9 - filter, 10 - flowmeter, 11 - pressure transmitter, 12 - pilot-operated two-way two-position valve, 13 - detection fixture, 14 - sealed measurement chamber, 15 - direct-acting valve, 16 - weighing water tank, 17 - weighing module, 18 - return water filter, 19 - pressure relief valve, 20 - temperature sensor, 21 - liquid level gauge, 22 - ball valve, 23 - tabletop, 24 - equipment bed, 25 - shield, 26 - blade positioning seal unit, 27 - operation interface. Detailed implementation manners

[0016] The following specific embodiments illustrate the implementation manners of the present invention. Those skilled in the art can easily understand other advantages and effects of the present invention from the content disclosed in this specification. Although the description of the present invention will be introduced in conjunction with preferred embodiments, this does not mean that the features of this invention are limited to this implementation manner. On the contrary, the purpose of introducing the invention in conjunction with the implementation manner is to cover other alternatives or modifications that may be extended based on the claims of the present invention. To provide a deep understanding of the present invention, many specific details will be included in the following description. The present invention can also be implemented without these details. In addition, to avoid confusing or obscuring the key points of the present invention, some specific details will be omitted in the description. It should be noted that, without conflict, the embodiments in this application and the features in the embodiments can be combined with each other. It should be noted that in this specification, similar reference numerals and letters indicate similar items in the following drawings. Therefore, once an item is defined in one drawing, it does not need to be further defined and explained in subsequent drawings.

[0017] Unless otherwise defined, technical terms or scientific terms used in the present invention shall have the ordinary meanings as understood by those of ordinary skill in the art to which the present invention pertains. The "first", "second" and similar terms used in the present invention do not denote any order, quantity or importance, but are only used to distinguish different components. Similarly, terms such as "a" or "an" do not denote a quantity limitation, but mean that there is at least one. Terms such as "provided", "connected" and "coupled" should be understood in a broad sense. For example, they can be fixedly connected, detachably connected or integrally connected; they can be mechanically connected or electrically connected; they can be directly connected or indirectly connected through an intermediate medium, and can be the communication inside two components. For those of ordinary skill in the art, the specific meanings of the above terms in this embodiment can be understood according to specific circumstances. The orientation or positional relationship indicated by "upper", "lower", "left", "right", "inner", "bottom", etc. is based on the orientation or positional relationship shown in the drawings, or the orientation or positional relationship in which the product of the invention is usually placed during use. It is only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying 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 construed as a limitation to the present invention.

[0018] To make the objectives, technical solutions and advantages of the present invention clearer, the following will further describe the embodiments of the present invention in detail with reference to the drawings.

[0019] In this embodiment, as shown in the attached Figure 1 - Figure 2 figures, an experimental device for the water flow rate in the inner cavity of an aeroengine blade includes a hydraulic system and a mechanical system. The hydraulic system is provided with a water tank 1. The water tank 1 is connected to a suction filter 2 through a pipeline. The suction filter 2 is branched to a manual ball valve 3. The manual ball valve 3 is respectively connected to a high-pressure centrifugal pump 4 and a low-pressure centrifugal pump 5. The high-pressure centrifugal pump 4 is connected to a needle valve 7. The needle valve 7 branches. One end is connected to an accumulator 8, and the other end is connected to a pressure relief valve 19. The low-pressure centrifugal pump 5 is connected to the accumulator 8. The accumulator 8 is connected to a filter 9. A flowmeter 10 is connected after the filter 9. The flowmeter 10 is connected to a pressure transmitter 11 and then connected to a pilot-operated two-way two-position valve 12. The pilot-operated two-way two-position valve 12 is symmetrically arranged, and a detection fixture 13 is arranged in the middle. After passing through the pilot-operated two-way two-position valve 12, it is connected to a sealed measurement chamber 14.

[0020] Further, check valves 6 are arranged between the high-pressure centrifugal pump 4 and the low-pressure centrifugal pump 5 and the accumulator 8.

[0021] Further, the sealed measurement chamber 14 is diverted to two direct-acting valves 15. One of the direct-acting valves 15 is connected to a weighing water tank 16, and the weighing water tank 16 is connected to a return water filter 18. The other direct-acting valve 15 is directly connected to the return water filter 18. The return water filter 18 is connected to a pressure relief valve 19. The needle valve 7 and the check valve 6 on the pipeline of the low-pressure centrifugal pump 5 are joined through a pipeline and then connected to the pressure relief valve 19.

[0022] Further, the other end of the water tank 1 is connected to a ball valve 22. A temperature sensor 20 and a liquid level gauge 21 are arranged between the water tank 1 and the ball valve 22.

[0023] Further, the mechanical system is provided with an equipment bed body 24. A table top 23 is arranged on the top of the equipment bed body 24. A detection fixture 13 is installed on the surface of the table top 23. Above the center of the detection fixture 13, there is a blade positioning and sealing unit 26. The blade positioning and sealing unit 26 is connected to the sealed measurement chamber 14. The outside of the table top 23 is covered with a protective cover 25, and an operation interface 27 is arranged beside the protective cover 25.

[0024] Further, the detection fixture 13 is a forty-equal division unit. The center of the forty-equal division unit is a disc structure. The outer edge of the disc is equally divided into forty parts, and each part is provided with a blade fixture. The detection fixture 13 is driven by a servo motor in cooperation with a planetary reducer.

[0025] Further, the sealed measurement chamber 14 is a rectangular frame structure, and is sealed with a silicone rubber gasket between it and the table top 23. Windows are opened on both side surfaces and the top surface of the sealed measurement chamber 14, and transparent acrylic is installed and a hydrophobic film is pasted.

[0026] Further, a water isolation ring is also arranged at the lower end of the sealed measurement chamber on the surface of the table top. A water accumulation collection and return groove is arranged outside the water isolation ring, and a water collection and return groove is also arranged beside the water isolation ring.

[0027] Further, the flow meter 10 is connected with a pressure stabilizing tank, and a heating device is also arranged at the front end of the flow meter 10. The pressure stabilizing tank can be used to buffer the water flow and ensure the stability of the test pipeline pressure. The capacity of the pressure stabilizing tank needs to be selected according to the measurement requirements and pipeline standards, and it needs to be inspected and maintained regularly to ensure that it has no deformation and no abnormal sound, and it needs to be drained regularly to ensure its normal operation. The heating device can keep the temperature of the detection environment stable. In addition, a temperature sensor is installed in the pipeline to monitor and record the temperature data in real time so as to make necessary corrections to the measurement results.

[0028] The specific working process of this application is as follows: S1. Manually place the blades on the measurement fixture in sequence; S2. The air cylinder automatically pushes the measurement fixture into the measurement chamber; S3. The hydraulic system injects the water in the water tank into the inner cavity of the blade; S4. The weighing unit collects the water ejected from the blade and transmits the weighing data to the computer in real time; S5. After weighing, the water will automatically flow back to the water tank; S6. The computer calculates the water flow rate based on the weight of the water within a specified time; S7. The cylinder retracts, and the forty-equal-part unit rotates to the next blade to repeat the above process until the testing of forty blades is completed.

[0029] Advantages of the present invention: 1. High degree of automation. In this application, the automatic rotation and positioning technology of the equal-part unit is introduced for feeding. Through the action of automated components, the automated measurement of the water flow rate of the high-pressure turbine blades of aeroengines is realized. Except for manually placing the blades one by one on the measurement fixture, the rest of the process is completed by machines, with a high automation rate.

[0030] 2. High measurement accuracy and testing efficiency. High-precision weighing sensors, pressure sensors, and flow meters are used, effectively improving the accuracy of the test results. The equipment tests each blade according to the beat, reducing the test cycle and enhancing the testing efficiency.

[0031] The above shows and describes the basic principles, main features, and advantages of the present invention. Those skilled in the art should understand that the present invention is not limited by the above embodiments. What is described in the above embodiments and the specification only illustrates the principles of the present invention. Without departing from the spirit and scope of the present invention, the present invention will have various changes and improvements, and these changes and improvements all fall within the scope of the present invention claimed. The scope of protection claimed by the present invention is defined by the appended claims and their equivalents.

Claims

1. A water flow test device for the inner cavity of an aircraft engine blade, characterized in that: The invention comprises a hydraulic system and a mechanical system. The hydraulic system is provided with a water tank (1). The water tank (1) is connected to a water suction filter (2) through a pipeline. The water suction filter (2) is diverted to a manual ball valve (3). The manual ball valve (3) is respectively connected to a high-pressure centrifugal pump (4) and a low-pressure centrifugal pump (5). The high-pressure centrifugal pump (4) is connected to a needle valve (7). The needle valve (7) performs diversion, one end of which is connected to an accumulator (8) and the other end is connected to a pressure relief valve (19). The low-pressure centrifugal pump (5) is connected to the accumulator (8). The accumulator (8) is connected to a filter (9). A flow meter (10) is connected to the filter (9). The flow meter (10) is connected to a pressure transmitter (11) and then to a pilot two-position two-way valve (12). The pilot two-position two-way valve (12) is symmetrically arranged and a detection fixture (13) is arranged in the middle. The detection fixture (13) is arranged on the surface of the equipment bed (24) and is connected to a sealed measuring chamber (14) after the pilot two-position two-way valve (12).

2. The device for testing water flow in the inner cavity of an aircraft engine blade according to claim 1, characterized in that: A one-way valve (6) is provided between the high-pressure centrifugal pump (4) and the low-pressure centrifugal pump (5) and the accumulator (8).

3. The device for testing water flow in the inner cavity of an aircraft engine blade according to claim 1, characterized in that: The sealed measuring chamber (14) is divided into two direct-acting valves (15), one of which is connected to a weighing water tank (16), which is connected to a return water filter (18), and the other direct-acting valve (15) is directly connected to a return water filter (18), which is connected to a pressure relief valve (19). The needle valve (7) and a one-way valve (6) located on the pipeline of the low-pressure centrifugal pump (5) are connected to the pressure relief valve (19) after being combined through a pipeline.

4. The device for testing water flow in the inner cavity of an aircraft engine blade according to claim 1, characterized in that: The other end of the water tank (1) is connected to the ball valve (22), and a temperature sensor (20) and a liquid level meter (21) are provided between the water tank (1) and the ball valve (22).

5. The device for testing water flow in the inner cavity of an aircraft engine blade according to claim 1, characterized in that: The mechanical system is provided with an equipment bed (24), a table (23) is provided on the top of the equipment bed (24), a detection fixture (13) is installed on the surface of the table (23), a blade positioning sealing unit (26) is provided above the center of the detection fixture (13), the blade positioning sealing unit (26) is connected to the sealed measurement chamber (14), a protective cover (25) is provided on the outside of the table (23), and an operation interface (27) is provided next to the protective cover (25).

6. The device for testing water flow in the inner cavity of an aircraft engine blade according to claim 1, characterized in that: The detection fixture (13) is a forty-equally divided graduation unit, the center of the forty-equally divided graduation unit is a disc structure, the outer edge of the disc is divided into forty equal parts, each of which is provided with a blade fixture, and the detection fixture (13) is driven by a servo motor in conjunction with a planetary reducer.

7. The device for testing water flow in the inner cavity of an aircraft engine blade according to claim 1, characterized in that: The sealed measurement cavity (14) is a rectangular frame structure, and is sealed with the table (23) by a silicone rubber sealing pad. The two side surfaces and the top surface of the sealed measurement cavity (14) are opened with windows, and transparent acrylic is installed, and a hydrophobic film is affixed.

8. The device for testing water flow in the inner cavity of an aircraft engine blade according to claim 5, characterized in that: The lower end of the sealed measuring cavity (14) on the surface of the table (23) is also provided with a water-blocking ring, a water collection reflux groove is provided on the outer side of the water-blocking ring, and a water collection reflux groove is also provided next to the water-blocking ring.

9. The water flow test device for the inner cavity of an aircraft engine blade according to claim 1, wherein the flow meter (10) is connected to a pressure regulating tank, and a heating device is also provided at the front end of the flow meter (10).

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