Flying and attaching casing lubricating oil system work simulation device in aero-engine starting and launching integrated test and starting and launching integrated test method

Abstract

The invention discloses a flight attachment casing lubricating oil system work simulation device in an aero-engine starting and launching integrated test and a starting and launching integrated test method. The simulation device is mainly composed of an oil tank body, a pressure sensor, a temperature sensor, a safety valve, a throttle valve serving as an equivalent nozzle, a centrifugal ventilator, a liquid level meter, a filter, a first stop valve, a second stop valve and a third stop valve. During an integrated starting test, an inlet of the first stop valve is connected with a lubricating oil supply pipe from an engine lubricating oil tank to a flying attachment casing; an outlet of the third stop valve is connected with a lubricating oil return pipe from the engine lubricating oil tank to the flying attachment casing; and the throttle valve is used as an equivalent nozzle to adjust the oil supply pressure and the oil supply flow of the lubricating oil. According to the invention, the working condition of the lubricating oil system of the flying-attached casing of the aero-engine can be simulated under the working condition of no flying-attached casing in the starting and generating integrated test, and the accurate measurement of the lubricating oil consumption of the engine is realized.

Description

Technical Field

[0001] The present invention belongs to the field of aircraft engine experiment and testing, and relates to aircraft engine ground test technology, specifically an aircraft engine flight accessory casing lubricating oil consumption simulation device and a starting-integrated test method, which replaces the lubricating oil system in the flight accessory casing in the engine starting-integrated test. Background Art

[0002] At present, the traditional aircraft engine ground test bench test mode is to use the same aircraft accessory casing (hereinafter referred to as the flight accessory casing), air starter, hydraulic pump, and generator for testing. During the engine test, the lubricating oil comes out of the lubricating oil tank and enters the bearing cavity and the accessory casing through the lubricating oil pump. The flight accessory casing lubricates and cools it, and then flows back to the lubricating oil tank through various oil filters and return oil pumps. The flight accessory casing, air starter, hydraulic pump, and generator are all real aircraft accessories, which are difficult to purchase. In order to reduce the constraints of real aircraft accessories on engine testing, and with the development of multi-electric and all-electric aircraft technology, the engine starter integrated test technology is studied. The starter integrated test technology is an advanced technology that integrates the engine starting and power generation functions. It realizes the two functions of engine starting and power generation through one motor. It is widely used in aviation, automobile 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 More Electric Aircraft [J]. Acta Aeronautica Sinica, 2020, 41(02): 324-335. The 120kW / 270V high-voltage DC starter generator system was recorded, and an integrated starter-generator experimental platform was built to complete the power generation and engine simulation start-up operation experiments. Another example is the Chinese invention patent CN110261121A, a test method for a starter-generator integrated bench simulating rapid loading function, which records the application of the starter-generator integrated test technology in the automotive field.

[0003] In the integrated starting and starting test technology, the integrated starting and starting drive system replaces the attachment casing and its accessories. The oil supply and return system between the oil tank and the attachment casing in the lubricating oil system has been interrupted. How to effectively simulate the operation of the lubricating oil system in the attachment casing without affecting the measurement of the engine lubricating oil consumption becomes a key issue. Summary of the invention

[0004] In response to the problems recorded in the background technology, the present invention aims to provide a flight attachment casing lubricating oil system working simulation device and a starting and starting integrated test method for aircraft engines, which can simulate the working condition of the flight attachment casing lubricating oil system of an aircraft engine under the condition of no flight attachment casing in the starting and starting integrated test, achieve accurate measurement of the engine lubricating oil consumption, solve the key problems in the starting and starting integrated test technology, simulate the working condition of the lubricating oil system in the flight attachment casing, and do not affect the final judgment of the engine lubricating oil consumption.

[0005] To achieve the above object, the present invention adopts the following technical solutions:

[0006] The working simulation device of the flight casing lubricating oil system in the aircraft engine starting and launching integrated test includes:

[0007] An oil tank body, 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] a lubricating oil inlet pipeline, wherein a first end of the lubricating oil inlet pipeline is connected to the lubricating oil inlet, and a second end of the lubricating oil inlet pipeline is connected to an outlet of the first stop valve;

[0009] a lubricating oil outlet pipeline, wherein a first end of the lubricating oil outlet pipeline is connected to the lubricating oil outlet, and a second end of the lubricating oil outlet pipeline is connected to an inlet of a third stop valve;

[0010] A pressure sensor and a temperature sensor, wherein the pressure sensor and the temperature sensor are arranged on the lubricating oil inlet pipeline and between the outlet of the first stop valve and the lubricating oil inlet;

[0011] A throttle valve, which is arranged on the lubricating oil inlet pipeline 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 in the flight attachment casing and spray the lubricating oil with the same pressure and flow rate as that used in the actual flight attachment casing into the oil tank body;

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

[0013] A filter, the filter being installed on the lubricating oil outlet pipeline and between the inlet of the third stop valve and the lubricating oil outlet;

[0014] A liquid level meter is installed at the liquid level interface of the oil tank body.

[0015] Furthermore, the flight casing oil system operation simulation device in the aircraft engine starting integrated test also includes a safety valve, a first end of the safety valve is connected to the outlet end of the first stop valve, and a second end is connected to the inlet end of the third stop valve.

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

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

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

[0019] Furthermore, the vent is opened on the top surface of the oil tank body.

[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 thermal resistance sensor.

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

[0022] Connect the inlet of the first stop valve to the lubricating oil supply pipe from the engine oil tank to the flight accessory casing;

[0023] Connect the outlet of the third stop valve to the oil return pipe from the engine oil tank to the flight accessory casing;

[0024] The throttle valve acts as an equivalent nozzle to adjust the oil supply pressure and oil flow.

[0025] Furthermore, the simulation device is installed on a mounting frame that fixes the integrated starting and starting drive system.

[0026] Compared with the traditional method, the present invention can simulate the oil pressure and flow of the real working conditions through the equivalent nozzle (throttle valve) of the process oil tank in the engine starting-integrated test without using the flight attachment casing, simulate the working condition of the flight attachment casing lubricating oil system, measure the engine lubricating oil consumption more accurately, and solve the key problems in the starting-integrated test technology. BRIEF DESCRIPTION OF THE DRAWINGS

[0027] Figure 1 It is the principle diagram of the working simulation device of the flight casing lubricating oil system in the aircraft engine starting and starting integrated test;

[0028] Figure 2 It is a three-dimensional diagram of the working simulation device of the flight casing lubricating oil system in the aircraft engine starting and starting integrated test;

[0029] Figure 3 It is a parts diagram of the working simulation device of the flight casing lubricating oil system in the aircraft engine starting and starting integration test;

[0030] Figure 4 It is a schematic diagram of the installation of the flight casing oil system working simulation device in the aircraft engine starting integration test;

[0031] In the figure: 1 - first stop valve; 2 - pressure sensor; 3 - temperature sensor; 4 - safety valve; 5 - throttle valve; 6 - centrifugal ventilator; 7 - oil tank body; 8 - liquid level gauge; 9 - second stop valve; 10 - filter; 11 - third stop valve. DETAILED DESCRIPTION

[0032] The present invention is further described below in conjunction with the accompanying drawings and specific embodiments, but it should not be understood that the scope of the subject matter described in the present invention is limited to the following embodiments. Without departing from the above-mentioned technical ideas of the present invention, various modifications, substitutions and changes made according to the common technical knowledge and customary means in the field are included in the scope of the present invention.

[0033] In order to simulate the working conditions of the aircraft engine flight casing lubricating oil system in the condition without flight casing in the start-up integrated test, 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 a real flying attachment, and a throttle valve 5 is used as an equivalent nozzle to simulate the lubricating oil resistance when the flying attachment casing is working, and then the lubricating oil pressure and flow are adjusted to make them the same as the lubricating oil pressure and flow when the real flying attachment casing is working. The inlet and outlet of the process oil tank are respectively connected to the lubricating oil supply pipe and return pipe from the lubricating oil tank to the flying attachment casing. The process oil tank is mainly composed 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 liquid level gauge 8, a filter 10, a first stop valve 1, a second stop valve 9 and a third stop valve 11 and other pipeline valves.

[0034] The process oil tank simulates the oil supply and return of a real flight. The inlet of the process oil tank is fed with a fixed flow rate by the lubricating oil pump on the engine accessory casing. By adjusting the opening of the throttle valve 5 (equivalent nozzle), the oil supply pressure and flow rate are simulated. The oil supply pressure and flow rate are adjustable. The pressure sensor 2 and the temperature sensor 3 are set to measure the lubricating oil temperature and pressure. The oil tank body 7 is provided with a centrifugal ventilator 6 to maintain the atmospheric pressure balance inside and outside the oil tank body 7. The liquid level meter 8 detects the liquid level in the oil tank body 7 to ensure that the liquid level is within the safe liquid level range. The lubricating oil stored in the oil tank body 7 is pumped out by the return oil pump on the engine. The lubricating oil outlet pipeline is provided with a filter 10 to filter the oil to ensure the cleanliness of the return oil. Manual valves are set at the lubricating oil inlet and outlet to manually control the on and off of the oil circuit.

[0035] The pressure sensor 2 is a 0-1MPa sensor with reverse polarity protection and instantaneous overcurrent and overvoltage protection, which is used to measure the working pressure in the oil circuit in real time.

[0036] The temperature sensor 3 is a screw-in thermal resistance sensor, which is used to measure the working 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, making the pressure control more stable. The pressure adjustment range can meet 0.1 to 0.5 MPa, and the adjustment accuracy is higher.

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

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

[0040] Finally, the process oil tank is installed on the mounting frame, and the inlet and outlet of the process oil tank are connected to the oil supply pipe and return pipe from the oil tank to the flight attachment casing respectively. During the engine test, the throttle valve 5 of the process oil tank is adjusted to establish the same oil pressure and flow rate between the oil tank and the flight attachment casing as those of the real engine, simulating the working conditions of the real flight attachment casing oil system.

[0041] The simulation device for the flight attachment casing lubricating oil system in the aircraft engine start-up integrated test designs a process oil tank to simulate the inlet and outlet lubricating oil interfaces and specifications of the real flight attachment, and uses a throttle valve as an equivalent nozzle to adjust the pressure and flow. The inlet and outlet of the process oil tank are respectively connected to the oil supply pipe and return pipe from the oil tank to the flight attachment casing.

[0042] The specific steps of using the aircraft engine flight casing oil system working simulation device to conduct an aircraft engine starting and starting integration test are as follows:

[0043] 1) Install the aircraft engine flight casing oil system working simulation device on the mounting frame of the fixed starter drive system, such as Figure 4 shown.

[0044] 2) The front pipeline interface (inlet) of the first stop valve 1 is connected to the lubricating oil supply pipe from the engine lubricating oil tank to the flight accessory casing, and the rear pipeline interface (outlet) of the third stop valve 11 is connected to the lubricating oil return pipe from the engine lubricating oil tank to the flight accessory casing.

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

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

[0047] The present invention realizes the simulation of the operation of the lubricating oil system of the auxiliary casing when the aircraft engine does not use the auxiliary casing to carry out the integrated starting test, and uses an equivalent nozzle to simulate the protection of the oil supply pressure and oil supply flow of the auxiliary casing.

[0048] The contents not described in detail in the specification of the present invention belong to the prior art known to the professional and technical personnel in the field. Although the illustrative specific embodiments of the present invention are described above to facilitate the understanding of the present invention by the technical personnel in the field, it should be clear that the present invention is not limited to the scope of the specific embodiments. For ordinary technicians in the field of this technology, as long as various changes are within the spirit and scope of the present invention defined and determined by the attached claims, these changes are obvious, and all inventions and creations using the concept of the present invention are protected.

Claims

1. A simulation device for the operation of the lubricating oil system of the flight casing in the integrated starting test of an aircraft engine, characterized in that: include: An oil tank body (7), the oil tank body (7) is used to store lubricating oil, and the oil tank body (7) is provided with a lubricating oil inlet, a lubricating oil outlet, a liquid level interface and a vent; a lubricating oil inlet pipeline, wherein a first end of the lubricating oil inlet pipeline is connected to the lubricating oil inlet, and a second end of the lubricating oil inlet pipeline is connected to an outlet of the first stop valve (1); a lubricating oil outlet pipeline, wherein a first end of the lubricating oil outlet pipeline is connected to the lubricating oil outlet, and a second end of the lubricating oil outlet pipeline is connected to an inlet of a third stop valve (11); A pressure sensor (2) and a temperature sensor (3), wherein the pressure sensor (2) and the temperature sensor (3) are arranged on the lubricating oil inlet pipeline and between the outlet of the first stop valve (1) and the lubricating oil inlet; A throttle valve (5), the throttle valve (5) being arranged on the lubricating oil inlet pipeline and being located between the pressure sensor (2) and the lubricating oil inlet, the throttle valve (5) using a precision throttle valve as an equivalent nozzle, for simulating the lubricating oil resistance in the flight attachment casing, and spraying the lubricating oil with the same pressure and flow rate as that used in the actual flight attachment casing into the oil tank body (7); A centrifugal ventilator (6), wherein the centrifugal ventilator (6) is installed at a ventilating opening of the oil tank body (7); A filter (10), the filter (10) being installed on the lubricating oil outlet pipeline and being located between the inlet of the third stop valve (11) and the lubricating oil outlet; A liquid level meter (8) is installed at the liquid level interface of the oil tank body (7).

2. The device for simulating the operation of the lubricating oil system of the aircraft engine casing in the integrated starting test of the aircraft engine according to claim 1, characterized in that: It also comprises a safety valve (4), wherein a first end of the safety valve (4) is connected to the outlet end of the first stop valve (1), and a second end of the safety valve (4) is connected to the inlet end of the third stop valve (11).

3. The device for simulating the operation of the lubricating oil system of the aircraft engine casing in the integrated starting test according to claim 2 is characterized by: The safety valve (4) is a manual pressure regulating valve with a double-piston balanced structure.

4. The device for simulating the operation of the lubricating oil system of the aircraft engine casing in the integrated starting test according to claim 1, characterized in that: The bottom of the oil tank body (7) is also provided with an oil drain port, and a second stop valve (9) is installed at the oil drain port.

5. The device for simulating the operation of the lubricating oil system of the aircraft engine casing in the integrated starting test of the aircraft engine according to claim 1, characterized in that: The lubricating oil inlet and the lubricating oil outlet are arranged on the same side of the oil tank body (7).

6. The device for simulating the operation of the lubricating oil system of the aircraft engine casing in the integrated starting test according to claim 1, characterized in that: The vent is provided on the top surface of the oil tank body (7).

7. The device for simulating the operation of the lubricating oil system of the aircraft engine casing in the integrated starting test of the aircraft engine according to 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 thermal resistance sensor.

8. An integrated test method for starting an aircraft engine, characterized in that: The simulation device of claim 1 or 2 is used to simulate the supply and recovery of lubricating oil, and comprises: Connect the inlet of the first stop valve (1) to the lubricating oil supply pipe from the engine lubricating oil tank to the flight accessory casing; Connect the outlet of the third stop valve (11) to the oil return pipe from the engine oil tank to the flight accessory casing; The throttle valve (4) is used as an equivalent nozzle to adjust the oil supply pressure and oil supply flow rate of the lubricating oil.

9. The aircraft engine starting integrated test method according to claim 8, characterized in that: The simulation device of claim 1 or 2 is installed on a mounting frame that fixes the integrated starting and driving system.

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