Simulation device and test method for the working of the lubricating oil system of the flight attachment box in the integrated test of aero-engine initiation and launch.

Abstract

This invention discloses a simulation device and method for the operation of the airborne attachment box lubricating oil system during an integrated start-up and launch test of an aero-engine. The simulation device mainly consists of an oil tank, a pressure sensor, a temperature sensor, a safety valve, a throttle valve acting as an equivalent nozzle, a centrifugal ventilator, a level gauge, a filter, a first shut-off valve, a second shut-off valve, and a third shut-off valve. During the integrated start-up and launch test, the inlet of the first shut-off valve is connected to the lubricating oil supply pipe from the engine oil tank to the airborne attachment box; the outlet of the third shut-off valve is connected to the lubricating oil return pipe from the engine oil tank to the airborne attachment box; and the throttle valve, acting as an equivalent nozzle, regulates the oil supply pressure and flow rate. This invention can simulate the operation of the airborne attachment box lubricating oil system of an aero-engine under conditions without the airborne attachment box during the integrated start-up and launch test, achieving accurate measurement of engine lubricating oil consumption.

Description

Technical Field

[0001] This invention belongs to the field of aero-engine testing and experimentation, and relates to aero-engine ground testing technology. Specifically, it is an aero-engine fly-attachment casing lubricating oil consumption simulation device and an integrated start-up and start-up test method, which replaces the lubricating oil system in the fly-attachment casing in the integrated start-up and start-up test of the engine. Background Technology

[0002] Currently, the traditional ground test bench mode for aero-engines involves using the same aircraft accessory housing (hereinafter referred to as the accessory housing), air starter, hydraulic pump, and generator as the aircraft itself. During engine testing, lubricating oil flows from the oil tank, is pumped through the oil pump, and enters the bearing cavity and accessory housing. The accessory housing lubricates and cools the oil, and then flows back to the oil tank through various oil filters and return pumps. The accessory housing, air starter, hydraulic pump, and generator are all actual aircraft accessories, making procurement difficult. To reduce the constraints of actual aircraft accessories on engine testing, and with the development of multi-electric and all-electric aircraft technologies, integrated engine start-up and generator testing technology has been researched. Integrated engine start-up and generator testing technology is an advanced technology that integrates engine starting and generator functions. It uses a single motor to achieve both engine starting and generator functions and is widely used in aviation, automotive, and other fields. For example, Zhang Zhuoran, Li Jincai, Han Jianbin, et al. Research and Implementation of High-Power High-Voltage DC Starter Generator System for Multi-Electric Aircraft [J]. Acta Aeronautica Sinica, 2020, 41(02):324-335. describes a 120kW / 270V high-voltage DC starter generator system, constructs an integrated starter-generator experimental platform, and completes generator and engine simulated start-up operation experiments. Another example is Chinese Invention Patent CN110261121A, a test method for an integrated starter-generator test bench simulating rapid loading function, which describes the application of integrated starter-generator testing technology in the automotive field.

[0003] In the integrated start-up and start-up test technology, the integrated start-up and start-up drive system replaces the air-attachment casing and its accessories. The oil supply and return system between the oil tank and the air-attachment casing in the lubrication system has been interrupted. How to effectively simulate the operation of the lubrication system in the air-attachment casing without affecting the measurement of engine oil consumption has become a key issue. Summary of the Invention

[0004] In response to the problems described in the background art, the present invention aims to provide a device and method for simulating the operation of the lubricating oil system of the airborne attachment box in an integrated launch and start-up test of an aero-engine. This device can simulate the operation of the lubricating oil system of the airborne attachment box in an integrated launch and start-up test without the airborne attachment box, thereby achieving accurate measurement of engine lubricating oil consumption. This solves a key problem in the integrated launch and start-up test technology, simulates the operation of the lubricating oil system in the airborne attachment box, and does not affect the final evaluation of engine lubricating oil consumption.

[0005] To achieve the above objectives, the present invention adopts the following technical solution:

[0006] A simulation device for the operation of the lubricating oil system of the flight attachment box in integrated aero-engine start-up and launch tests includes:

[0007] The oil tank body is used to store lubricating oil, and the oil tank body is provided with a lubricating oil inlet, a lubricating oil outlet, a liquid level interface and a vent.

[0008] The lubricating oil inlet pipeline has a first end connected to the lubricating oil inlet and a second end connected to the outlet of the first shut-off valve.

[0009] The lubricating oil outlet pipeline has a first end connected to the lubricating oil outlet and a second end connected to the inlet of the third shut-off valve.

[0010] A pressure sensor and a temperature sensor are provided, which are installed on the lubricating oil inlet pipeline and located between the outlet of the first shut-off valve and the lubricating oil inlet.

[0011] A throttle valve is installed on the lubricating oil inlet pipe and between the pressure sensor and the lubricating oil inlet. The throttle valve uses a precision throttle valve as an equivalent nozzle to simulate the lubricating oil resistance inside the fly attachment casing and sprays lubricating oil with the same pressure and flow rate as the actual fly attachment casing into the oil tank.

[0012] A centrifugal ventilator, wherein the centrifugal ventilator is installed at the vent of the oil tank body;

[0013] A filter is installed on the lubricating oil outlet line and is located between the inlet and outlet of the third shut-off valve;

[0014] A level gauge is installed at the level interface of the oil tank.

[0015] Furthermore, the simulation device for the working of the air-mounted casing lubricating oil system in the integrated test of aero-engine launch also includes a safety valve, the first end of which is connected to the outlet end of the first shut-off valve, and the second end of which is connected to the inlet end of the third shut-off valve.

[0016] Furthermore, the safety valve is a manual pressure regulating valve with a dual-piston balanced structure.

[0017] Furthermore, an oil drain port is provided at the bottom of the oil tank, and a second shut-off valve is installed at the oil drain port.

[0018] Furthermore, the lubricating oil inlet and lubricating oil outlet are located on the same side of the oil tank.

[0019] Furthermore, the ventilation opening is located on the top surface of the fuel tank.

[0020] Furthermore, the pressure sensor is a sensor with reverse polarity protection and instantaneous overcurrent and overvoltage protection; the temperature sensor is a screw-in resistance temperature detector (RTD) sensor.

[0021] The integrated test method for aircraft engine start-up and recovery uses the aforementioned simulation device to simulate the supply and recovery of lubricating oil, and includes:

[0022] Connect the inlet of the first shut-off valve to the oil supply line from the engine oil tank to the airframe casing.

[0023] Connect the outlet of the third shut-off valve to the oil return pipe from the engine oil tank to the fuselage casing.

[0024] The oil supply pressure and flow rate are adjusted by using a throttle valve as an equivalent nozzle.

[0025] Furthermore, the simulation device is mounted on the mounting bracket of the fixed start-up integrated drive system.

[0026] Compared with traditional methods, this invention can simulate the lubricating oil pressure and flow rate under real operating conditions during engine start-up and test runs without using the flyweight casing. It simulates the working conditions of the flyweight casing lubricating oil system by using the equivalent nozzle (throttle valve) of the process oil tank, thus more accurately measuring the engine lubricating oil consumption and solving a key problem in the start-up and test technology. Attached Figure Description

[0027] Figure 1 This is a schematic diagram of the working simulation device for the lubricating oil system of the flight attachment box in the integrated test of aero-engine start-up;

[0028] Figure 2 This is a 3D diagram of a simulation device for the working of the lubricating oil system of the flight attachment box during an integrated test of an aero-engine start-up and launch system.

[0029] Figure 3 This is a part drawing of a simulation device for the working of the lubricating oil system of the flight attachment box during the integrated test of an aero-engine start-up and launch.

[0030] Figure 4 This is a schematic diagram of the working simulation device for the lubricating oil system of the flight attachment box during the integrated test of an aero-engine start-up and launch.

[0031] In the diagram: 1—First shut-off valve; 2—Pressure sensor; 3—Temperature sensor; 4—Safety valve; 5—Throttle valve; 6—Centrifugal ventilator; 7—Oil tank; 8—Level gauge; 9—Second shut-off valve; 10—Filter; 11—Third shut-off valve. Detailed Implementation

[0032] The present invention will be further described below with reference to the accompanying drawings and specific embodiments. However, it should not be construed that the scope of the subject matter of the present invention is limited to the following embodiments. All modifications, substitutions and alterations made based on ordinary technical knowledge and common practices in the art without departing from the above-described technical concept of the present invention are included within the scope of the present invention.

[0033] In order to simulate the operation of the aircraft engine's fly-attachment box lubrication system under conditions without the fly-attachment box during integrated engine-launch tests, such as... Figure 1 In this embodiment, a process oil tank is designed as a simulation device to simulate the inlet and outlet lubricating oil interfaces and specifications of the actual fly attachment. A throttle valve 5 is used as an equivalent nozzle to simulate the lubricating oil resistance when the fly attachment casing is working, thereby adjusting the lubricating oil pressure and flow rate to be the same as the lubricating oil pressure and flow rate when the actual fly attachment casing is working. The inlet and outlet of the process oil tank are connected to the lubricating oil supply pipe and return pipe from the lubricating oil tank to the fly attachment casing, respectively. The process oil tank mainly consists of an oil tank body 7, a pressure sensor 2, a temperature sensor 3, a safety valve 4, a throttle valve 5 (equivalent nozzle), a centrifugal ventilator 6, a level gauge 8, a filter 10, a first shut-off valve 1, a second shut-off valve 9, and a third shut-off valve 11, as well as other pipe valves, etc.

[0034] The process oil tank simulates the supply and return oil of a real engine attachment. The inlet of the process oil tank receives a fixed flow rate from the lubricating oil pump on the engine accessory housing. The supply pressure and flow rate are simulated by adjusting the opening of the throttle valve 5 (equivalent nozzle). The supply pressure and flow rate are adjustable. Pressure sensor 2 and temperature sensor 3 are installed to measure the lubricating oil temperature and pressure. The oil tank body 7 is equipped with a centrifugal ventilator 6 to maintain atmospheric pressure balance inside and outside the oil tank body 7. A level gauge 8 detects the liquid level in the oil tank body 7 to ensure it remains within a safe range. The lubricating oil stored in the oil tank body 7 is drawn out by the return oil pump on the engine attachment. A filter 10 is installed in the lubricating oil outlet pipeline to filter the oil and ensure the cleanliness of the return oil. Manual valves are installed at the lubricating oil inlet and outlet for manual control of the oil circuit.

[0035] Pressure sensor 2 is selected from 0 to 1 MPa sensors with reverse polarity protection and instantaneous overcurrent and overvoltage protection, and is used to measure the working pressure in the oil circuit in real time.

[0036] Temperature sensor 3 is a screw-in resistance temperature detector (RTD) sensor used to measure the operating temperature in the oil circuit.

[0037] Safety valve 4 uses a manual pressure regulating valve with a double-piston balanced structure to stabilize the pressure before the valve, resulting in smoother pressure control. The pressure adjustment range can meet 0.1~0.5MPa, and the adjustment accuracy is higher.

[0038] The equivalent nozzle uses a precision throttle valve 5 to simulate the lubricating oil resistance inside the flywheel casing and spray the lubricating oil into the oil tank. It has a high degree of precision adjustment and is resistant to high temperatures. By adjusting the opening of the throttle valve 5, lubricating oil with an inlet pressure of 0.32MPa~0.35MPa and a flow rate of 7L / min~8L / min can be sprayed into the oil tank body 7 without back pressure.

[0039] Filter 10 is a 5μm precision filter, installed on the lubricating oil outlet pipeline to filter out solid particles and colloidal substances in the working medium, effectively controlling the contamination level in the return oil.

[0040] Finally, the process oil tank is installed on the mounting bracket, with its inlet and outlet connected to the oil supply and return lines from the lubricating oil tank to the flywheel casing, respectively. During engine testing, the throttle valve 5 of the process oil tank is adjusted to establish the same oil pressure and flow rate as the actual engine's lubricating oil tank and flywheel casing, simulating the operation of the actual flywheel casing lubricating oil system.

[0041] In the integrated start-up test of an aero-engine, a simulation device for the lubricating oil system of the flight attachment casing was designed. A process oil tank was used to simulate the inlet and outlet lubricating oil interfaces and specifications of the actual flight attachment. A throttle valve was used as an equivalent nozzle to regulate the pressure and flow rate. The inlet and outlet of the process oil tank were connected to the lubricating oil supply pipe and return pipe from the lubricating oil tank to the flight attachment casing, respectively.

[0042] The specific steps for conducting integrated start-up and launch tests of aircraft engines using an aircraft engine flight attachment box lubrication system working simulation device are as follows:

[0043] 1) Install the aircraft engine flywheel casing lubrication system working simulation device on the mounting bracket of the fixed start-up integrated drive system, such as... Figure 4 As shown.

[0044] 2) The front end pipe interface (inlet) of the first shut-off valve 1 is connected to the oil supply pipe from the engine oil tank to the airframe casing, and the rear end pipe interface (outlet) of the third shut-off valve 11 is connected to the oil return pipe from the engine oil tank to the airframe casing.

[0045] 3) During the test run, lubricating oil is input into the inlet of the oil tank 7 by the flywheel lubricating oil pump. The lubricating oil temperature and pressure are measured by pressure sensor 2 and temperature sensor 3 installed on the pipeline. The opening of the throttle valve 5 (equivalent nozzle) is adjusted to simulate the lubricating oil resistance of the flywheel casing, so that lubricating oil with an inlet pressure of 0.32MPa~0.35MPa and a flow rate of 7L / min~8L / min is injected into the oil tank 7 without back pressure. A centrifugal ventilator 6 is installed on the oil tank 7 to maintain the atmospheric pressure balance inside and outside the oil tank 7. A level gauge 8 is installed on the oil tank 7 to detect the liquid level in the oil tank 7 to ensure that the liquid level is within the safe liquid level range. A filter 10 is installed in the return oil line (lubricating oil outlet pipeline) to filter the oil to ensure the cleanliness of the return oil. The lubricating oil stored in the oil tank 7 is extracted by the return oil pump on the flywheel.

[0046] 4) Finally, the simulation of the oil circulation between the engine oil tank and the flywheel casing is realized.

[0047] This invention realizes the simulation of the operation of the airborne attachment box lubrication system when the aero-engine is carried out in an integrated start-up test without using the airborne attachment box, and uses equivalent nozzles to simulate the protection of the airborne attachment box oil supply pressure and oil supply flow.

[0048] Contents not described in detail in this specification are prior art known to those skilled in the art. Although illustrative specific embodiments of the invention have been described above to facilitate understanding by those skilled in the art, it should be understood that the invention is not limited to the scope of the specific embodiments. Various modifications are readily apparent to those skilled in the art as long as they fall within the spirit and scope of the invention as defined and determined by the appended claims, and all inventions utilizing the concept of this invention are protected.

Claims

1. A device for simulating the operation of the lubricating oil system of the flight attachment casing during integrated start-up and launch testing of an aero-engine, characterized in that, include: Oil tank (7), the oil tank (7) is used to store lubricating oil, and the oil tank (7) is provided with lubricating oil inlet, lubricating oil outlet, liquid level interface and vent; The lubricating oil inlet pipeline has a first end connected to the lubricating oil inlet and a second end connected to the outlet of the first shut-off valve (1). The lubricating oil outlet pipeline has a first end connected to the lubricating oil outlet and a second end connected to the inlet of the third shut-off valve (11). Pressure sensor (2) and temperature sensor (3) are provided on the lubricating oil inlet pipeline and are located between the outlet of the first shut-off valve (1) and the lubricating oil inlet. Throttling valve (5) is installed on the lubricating oil inlet pipe and between the pressure sensor (2) and the lubricating oil inlet. Throttling valve (5) uses a precision throttle valve as an equivalent nozzle to simulate the lubricating oil resistance in the fly attachment casing and sprays the same pressure and flow rate of lubricating oil as the actual fly attachment casing into the oil tank (7). Centrifugal ventilator (6), said centrifugal ventilator (6) is installed at the vent of the oil tank body (7); A filter (10) is installed on the lubricating oil outlet line and is located between the inlet of the third shut-off valve (11) and the lubricating oil outlet; A level gauge (8) is installed at the level interface of the oil tank body (7).

2. The simulation device for the working of the lubricating oil system of the flight attachment box in the integrated test of an aero-engine launch and start-up as described in claim 1, characterized in that: It also includes a safety valve (4), the first end of which is connected to the outlet end of the first shut-off valve (1), and the second end is connected to the inlet end of the third shut-off valve (11).

3. The simulation device for the working of the lubricating oil system of the flight attachment box in the integrated test of an aero-engine launch and start-up as described in claim 2, characterized in that: The safety valve (4) is a manual pressure regulating valve with a double piston balanced structure.

4. The simulation device for the working of the lubricating oil system of the flight attachment box in the integrated test of an aero-engine launch and start-up as described in claim 1, characterized in that: The bottom of the oil tank (7) is also provided with an oil drain port, and a second shut-off valve (9) is installed at the oil drain port.

5. The simulation device for the working of the lubricating oil system of the flight attachment box in the integrated test of an aero-engine launch and start-up, as described in claim 1, is characterized in that: The lubricating oil inlet and lubricating oil outlet are located on the same side of the oil tank (7).

6. The simulation device for the working of the lubricating oil system of the flight attachment box in the integrated test of an aero-engine starting and starting as described in claim 1, characterized in that: The ventilation opening is located on the top surface of the fuel tank body (7).

7. The simulation device for the working of the lubricating oil system of the flight attachment box in the integrated test of an aero-engine launch and start-up as described in claim 1, characterized in that: The pressure sensor (2) is a sensor with reverse polarity protection and instantaneous overcurrent and overvoltage protection; The temperature sensor (3) is a screw-in resistance temperature detector (RTD) sensor.

8. An integrated test method for aircraft engine start-up and launch, characterized in that, The simulation apparatus of claim 1 or 2 is used to simulate the supply and recovery of lubricating oil, and includes: Connect the inlet of the first shut-off valve (1) to the oil supply pipe from the engine oil tank to the airframe casing; Connect the outlet of the third shut-off valve (11) to the oil return pipe from the engine oil tank to the airframe casing; The oil supply pressure and flow rate are adjusted by using a throttle valve (4) as an equivalent nozzle.

9. The integrated test method for aero-engine initiation and launch according to claim 8, characterized in that: The simulation device of claim 1 or 2 is mounted on the mounting bracket of the fixed start-up integrated drive system.

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