Aero-engine swirler flow detection device capable of automatically controlling pressure

Abstract

The invention provides an aero-engine swirler flow detection device capable of automatically controlling pressure, a test bed is used for installing and fixing a hydraulic system, the upper part is a working chamber, and a tested piece lifting mechanism and an angle measuring device are arranged in the working chamber; a measurement distribution system, a hydraulic element and a pipeline are arranged at the lower part; the right side of the rack is an electrical control cabinet; an oil tank, a hydraulic element, a pump set and a radiator are arranged behind the rack; an interface flange is reserved in the working chamber, is firstly connected with an oil mist separator and then is butted with a factory air draft system; the electromagnetic valve, the starting test pump set, oil and the oil tank are sequentially connected through the oil suction filter and the ball valve and then connected with the crude oil filter, the essential oil filter and the hose. The oil liquid distribution mechanism, the oil liquid reversing mechanism and the oil collecting box are connected; the lifting mechanism is connected with the computer, and the camera is connected with the rotating mechanism and the computer. The method has the advantages of being high in detection efficiency, reliable in data and the like, guaranteeing smooth scientific research and production of companies, and improving economic benefits.

Description

Technical Field

[0001] The invention relates to the field of experiment and test technology, and in particular to an aircraft engine vortex flow detection device capable of automatically controlling pressure. Background Art

[0002] After a certain type of engine vortex finder is assembled, the vortex finder flow, spray angle, and spray distribution need to be measured to determine whether the vortex finder meets the process requirements. This project is an aircraft engine vortex finder flow detection device that can automatically control pressure. The device mainly includes a control device, an oil pump, an oil tank, a filter, a voltage regulator, a solenoid valve, a pressure regulating valve, a pressure sensor, a measuring cylinder, and other parts. The device uses a variable frequency motor to drive the oil pump. At different speeds, the system automatically adjusts the oil pressure at the outlet of the oil pump. When the pressure is stable, the computer collects, records, processes, and analyzes the flow data within a fixed time, and reliably detects the various performance indicators of the vortex finder. Summary of the invention

[0003] The purpose of the present invention is to collect, record, process and analyze flow data, spray angle and spray distribution within a fixed time by computer, so as to reliably detect various performance indicators of vortex finder, and provide an aircraft engine vortex finder flow detection device which can automatically control pressure.

[0004] The present invention provides an aircraft engine vortex flow detection device capable of automatically controlling pressure, which is characterized by:

[0005] The test bench is used to install and fix the hydraulic system. The upper part is the working room, inside which are placed the lifting mechanism of the test piece and the angle measuring device; the lower part is installed with the measurement distribution system, hydraulic components and pipelines; the right side of the bench is the electrical control cabinet; the rear side of the bench is arranged with the oil tank, flow test pump group and radiator.

[0006] The oil tank is used to store oil to ensure sufficient supply to the hydraulic pump and to receive the return oil after the test. The pump group provides oil of a certain pressure for the hydraulic system to meet the flow test, angle test and distribution test. The studio uses double doors. Closing them during the test can ensure that the oil does not splash and the light source is stable during the angle test. The test piece lifting mechanism and angle measuring device are placed inside the studio to lift the test piece for angle test or lower the test piece for flow test and distribution test. A distribution mechanism is designed under the studio. The test piece oil passes through the distribution mechanism and enters 12 oil collection boxes. The nozzle distribution test is carried out by measuring the weight of the oil in the oil collection box. A mass flow meter is also set under the studio for flow test of the test piece. The rear side of the test bench is the oil tank, hydraulic components, pump group and radiator for collecting cooling oil. The studio has a reserved interface flange, which is first connected to the oil mist separator and then connected to the factory exhaust system to facilitate the discharge of oil and gas generated during the test piece test.

[0007] When the test piece is subjected to the vortex flow test, the solenoid valve 11 is opened, the test pump group 3 is started, and the oil is extracted from the oil tank 1 through the oil suction filter and the ball valve 2, and then enters the test piece through the coarse oil filter 6, the fine oil filter 7, and the hose. The computer automatically adjusts the pressure to make the system reach the flow test pressure, and the test piece flow test is carried out. The oil flows out through the test piece, and the flow value is collected and recorded by the computer through the mass flowmeter. The computer automatically adjusts the pressure to make the system pressure reach the test piece distribution test pressure, and the test piece distribution test is carried out. The oil flows out through the test piece, passes through the oil distribution mechanism 25, the oil reversing mechanism 26, and flows into the oil collecting box 28. Through the weighing sensor 29, the computer automatically calculates the distribution rate of the test piece.

[0008] The lifting mechanism 15 automatically lifts the test piece, and the computer automatically adjusts the pressure to the test pressure of the test piece atomization angle to perform the test of the test piece atomization angle. The test piece atomization angle data is collected by the camera 23, and the rotating mechanism 17 is started to collect another set of data of the test piece.

[0009] The computer automatically collects, calculates, and enters the test data. The overflow valve 4 is used as a safety valve in the system to prevent the system from overpressure. The accumulator 8 can absorb the pulsation of the system oil to stabilize the pressure. The oil tank is used to store the oil. When the oil temperature exceeds the test working temperature, the cooling circulation pump group 34 is started, and the oil is sucked out of the oil tank 1 through the radiator and returned to the oil tank, which plays a role in cooling the oil.

[0010] A 20μm and a 5μm oil filter are connected in series in the hydraulic system to better filter out large particles of impurities in the oil to prevent contamination of the test piece. When the tester is working, the pressure of the pneumatic pressure reducing valve 21 reaches 0.25-0.3MPa, and the pressure of the pneumatic triple-piece pressure reducing valve 20 is 0.4-0.6MPa, which is used for the operation of various mechanisms of the system.

[0011] Compared with the prior art, the present invention has the following advantages:

[0012] The aircraft engine vortex flow detection device capable of automatically controlling pressure described in the present invention is based on the application of a certain type of aircraft engine nozzle performance detection device operated digitally by a computer, which ensures the demand for aircraft engine vortex flow detection performance testing, has the characteristics of high detection efficiency and reliable data, and ensures the smooth progress of the company's scientific research and production, and improves economic benefits. BRIEF DESCRIPTION OF THE DRAWINGS

[0013] The present invention is further described in detail below with reference to the accompanying drawings and embodiments:

[0014] Figure 1 It is an aircraft engine vortex flow detection device capable of automatically controlling pressure;

[0015] In the figure, 1 oil tank 2 ball valve 3 pump group 4 overflow valve 5 switch valve 6 coarse oil filter 7 fine oil filter 8 accumulator 9 pressure gauge 10 mass flow meter 11 solenoid valve 12 pressure sensor 13 pneumatic solenoid valve 14 tooling 15 lifting mechanism 16 pneumatic solenoid valve 17 rotating mechanism 18 gas volume regulating valve 19 pneumatic solenoid valve 20 pneumatic triplet 21 cylinder 22 explosion-proof lamp 23 camera 24 oil mist separator 25 oil distribution mechanism 26 oil reversing mechanism 27 reversing cylinder 28 oil collecting box 29 weighing sensor 30 solenoid valve 31 oil return pipe 32 refrigerator 33 radiator 34 circulating pump. DETAILED DESCRIPTION

[0016] The present invention will be further explained below in conjunction with specific implementation plans, but the present invention is not limited thereto. The structures, proportions, sizes, etc. illustrated in the drawings of the specification are only used to match the contents disclosed in the specification for people familiar with this technology to understand and read, and are not used to limit the restrictive conditions under which the present invention can be implemented. Therefore, they have no substantive technical significance. Any structural modification, change in proportional relationship or adjustment of size should still fall within the scope of the technical content disclosed by the present invention without affecting the effects and purposes that can be achieved by the present invention.

[0017] The present invention provides an aircraft engine vortex flow detection device capable of automatically controlling pressure. The test bench is used for installing and fixing the hydraulic system. The upper part is a working room, and a lifting mechanism of a test piece and an angle measuring device are placed inside the working room; a measuring distribution system, hydraulic components and pipelines are installed at the lower part; an electrical control cabinet is arranged on the right side of the bench; an oil tank, a flow test pump group and a radiator are arranged at the rear side of the bench; the oil tank is used for storing oil to ensure sufficient supply to the hydraulic pump and to receive the return oil after the test; the pump group provides oil of a certain pressure for the hydraulic system to meet the flow test, angle test and distribution test; the working room adopts a double-door opening, and a lifting mechanism of a test piece and an angle measuring device are placed inside the working room; a distribution mechanism is designed at the bottom of the working room, and the oil of the test piece is distributed through the distribution mechanism. The nozzle distribution test is carried out by measuring the weight of the oil in the oil collecting boxes through the distribution mechanism. A mass flow meter is also arranged below the studio for flow test of the test piece. The rear side of the test bench is the oil tank, hydraulic components, pump group and radiator for collecting cooling oil. The studio has a reserved interface flange, which is first connected to the oil mist separator and then to the factory exhaust system. The solenoid valve 11, the start-up test pump group 3, the oil and the oil tank 1 are connected in sequence through the oil suction filter and the ball valve 2, and then connected to the coarse oil filter 6, the fine oil filter 7 and the hose. The oil distribution mechanism 25, the oil reversing mechanism 26 and the oil collecting box 28 are connected. The weighing sensor 29 is connected to the computer. The lifting mechanism 15 is connected to the computer, and the camera 23 is connected to the rotating mechanism 17 and the computer respectively.

[0018] The computer is connected to the overflow valve 4, which is used as a safety valve in the system to prevent the system from overpressure; the accumulator 8 can absorb the pulsation of the system oil to stabilize the pressure; the oil tank is used to store oil. When the oil temperature exceeds the test working temperature, the cooling circulation pump group 34 is started, and the oil is sucked out of the oil tank 1 through the radiator and returned to the oil tank; a 20μm and a 5μm oil filter are connected in series in the hydraulic system. When the tester is working, the pressure of the pneumatic pressure reducing valve 21 reaches 0.25-0.3MPa, and the pressure of the pneumatic three-piece pressure reducing valve 20 is 0.4-0.6MPa, which are used for the operation of various mechanisms of the system.

[0019] Matters not covered by the present invention are known technologies.

[0020] Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that various changes, modifications, substitutions and variations may be made to the embodiments without departing from the principles and spirit of the present invention, and that the scope of the present invention is defined by the appended claims and their equivalents.

Claims

1. An aircraft engine vortex flow detection device capable of automatically controlling pressure, characterized in that: The test bench is used to install and fix the hydraulic system. The upper part is the studio, inside which the lifting mechanism of the test piece and the angle measuring device are placed; the lower part is installed with the measurement distribution system, hydraulic components and pipelines; the right side of the bench is the electrical control cabinet; the rear side of the bench is arranged with the oil tank, flow test pump group and radiator; the oil tank is used to store oil to ensure sufficient supply to the hydraulic pump and to receive the return oil after the test; the pump group provides the hydraulic system with oil of a certain pressure to meet the flow test, angle test and distribution test; the studio adopts double-door, inside which the lifting mechanism of the test piece and the angle measuring device are placed, and the distribution mechanism is designed at the bottom of the studio, through which the oil of the test piece passes into 12 oil collecting boxes and then passes through the distribution mechanism. The nozzle distribution test is carried out by measuring the weight of the oil in the oil collecting box; a mass flow meter is also arranged below the studio for flow test of the test piece; the rear side of the test bench is an oil tank, hydraulic components, a pump group and a radiator for collecting cooling oil; the studio has a reserved interface flange, which is first connected to the oil mist separator and then connected to the factory exhaust system; the solenoid valve 11, the start-up test pump group 3, the oil, and the oil tank 1 are connected in sequence through the oil suction filter and the ball valve 2, and then connected to the coarse oil filter 6, the fine oil filter 7 and the hose; the oil distribution mechanism 25, the oil reversing mechanism 26 and the oil collecting box 28 are connected; the weighing sensor 29 is connected to the computer; the lifting mechanism 15 is connected to the computer, and the camera 23 is connected to the rotating mechanism 17 and the computer respectively.

2. The aircraft engine vortex flow detection device capable of automatically controlling pressure according to claim 1, characterized in that: The computer is connected to the overflow valve 4, which is used as a safety valve in the system to prevent the system from overpressure; the accumulator 8 can absorb the pulsation of the system oil to stabilize the pressure; the oil tank is used to store oil. When the oil temperature exceeds the test working temperature, the cooling circulation pump group 34 is started, and the oil is sucked out of the oil tank 1 through the radiator and returned to the oil tank; a 20μm and a 5μm oil filter are connected in series in the hydraulic system. When the tester is working, the pressure of the pneumatic pressure reducing valve 21 reaches 0.25-0.3MPa, and the pressure of the pneumatic three-piece pressure reducing valve 20 is 0.4-0.6MPa, which are used for the operation of various mechanisms of the system.

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