1. The utility model provides an aeroengine variable throttle valve test system which characterized in that includes:

the bearing cavity simulation cavity (5) is used for simulating a bearing cavity, and the bearing cavity simulation cavity (5) is communicated to a bearing cavity inlet of the variable throttle valve (1) through a pipeline;

the gearbox simulation cavity (6) is used for simulating a gearbox, and the gearbox simulation cavity (6) is communicated with a rear-stage outlet of the variable throttle valve (1) through a pipeline;

the air source (2) is used for providing pressure air for the variable throttle valve (1), and the air source (2) is respectively communicated to an inlet of the bearing cavity simulation cavity (5) and a ventilation inlet of the variable throttle valve (1) through a pipeline provided with a first valve (31);

the throttle nozzle (4) is arranged in front of an inlet of the bearing cavity simulation cavity (5), the displacement measuring device (7) is arranged in the gear box simulation cavity (6), the displacement measuring device (7) is connected with the movable slide valve of the variable throttle valve (1) and used for measuring the moving amount of the slide valve, and the gear box simulation cavity (6) is communicated with the atmosphere through a pipeline provided with a second valve (32) and a flow measuring device (8).

2. The aircraft engine variable throttle valve test system according to claim 1, characterized in that the throttle mouth (4) is determined according to the seal leakage characteristics of the aircraft engine by fixing the throttle mouth (4) to control the pressure of the bearing cavity simulation chamber (5).

3. An aircraft engine variable throttle valve test system as claimed in claim 2, characterized in that the volume of said bearing chamber simulation chamber (5) is determined according to the actual volume of the aircraft engine bearing chamber.

4. The aircraft engine variable throttle valve test system according to claim 1, characterized in that the volume of the gearbox simulation chamber (6) is determined according to the actual volume of the aircraft engine bearing chamber.

5. The test system for the variable throttle valve of the aircraft engine according to claim 1, wherein pressure measuring devices are arranged at the front ends of the ventilation inlets of the bearing cavity simulation cavity (5), the gearbox simulation cavity (6) and the variable throttle valve (1) and are respectively used for measuring the internal pressure of the bearing cavity simulation cavity (5), the internal pressure of the gearbox simulation cavity (6) and the ventilation inlet pressure of the variable throttle valve (1).

6. The aircraft engine variable throttle valve testing system of claim 5, wherein the pressure measuring device comprises a pressure gauge.

7. An aircraft engine variable throttle valve test system as in claim 1, characterized in that said displacement measuring means (7) comprise a dial gauge.

8. An aircraft engine variable throttle valve test system as claimed in claim 1, characterized in that said flow measuring means (8) comprise a flow meter.

9. A test method using an aircraft engine variable throttle valve test system according to any one of claims 1 to 8, characterized in that the test method comprises:

adjusting a first valve (31) to enable the pressure of a ventilation inlet of the variable throttle valve (1) to slowly rise;

when the displacement measuring device (7) indicates, the ventilation inlet value of the variable throttle valve (1) is the starting pressure of the variable throttle valve (1);

then, continuously increasing the pressure of a ventilation inlet of the variable throttle valve (1), wherein when the displacement measuring device (7) indicates the middle position of the stroke, the value of the ventilation inlet of the variable throttle valve (1) at the moment is the middle pressure of the variable throttle valve (1);

and then, continuously increasing the pressure of the ventilation inlet of the variable throttle valve (1), wherein when the displacement measuring device (7) indicates that the full stroke is reached, the value of the ventilation inlet of the variable throttle valve (1) at the moment is the closing pressure of the variable throttle valve (1).

10. A test method using an aircraft engine variable throttle valve test system according to any one of claims 1 to 8, characterized in that the test method comprises:

adjusting a first valve (31) to enable the pressure of a ventilation inlet of the variable throttle valve (1) to slowly rise;

then adjusting the pressure of a ventilation inlet of the variable throttle valve (1) to a preset test value, and acquiring the pressure values and the outlet flow of a bearing cavity simulation cavity (5) and a gear box simulation cavity (6) after test value parameters are stable;

and obtaining the resistance performance of the variable throttle valve (1) under preset pressure and flow according to the difference value of the pressure values of the bearing cavity simulation cavity (5) and the gear box simulation cavity (6).

Background

The variable throttle valve (or called test piece) is a valve which uses air source to automatically adjust the size of a throttle nozzle so as to control the pressure distribution of a bearing cavity and a ventilation flow path of an aeroengine.

In the prior art, a simulation test system controls an actuating mechanism based on a single air source, the back pressure is atmospheric pressure, so that parameters such as opening pressure, closing pressure and flow resistance are obtained, and the working condition simulated by the model is greatly different from the actual working condition of an engine. During testing, the functional relationship between the control air source and the pressure of the bearing cavity and the functional relationship between the back pressure and the pressure of the bearing cavity cannot be simulated, and the two requirements cannot be met.

According to the conventional test method, before the variable throttle valve is assembled to the engine, an accurate working rule can not be obtained and the working rule is consistent with the state of the engine. In addition, the working rule of the variable throttle valve is also influenced by other components such as a shell, a spring, a valve core and the like and machining tolerances thereof, so that related tests and verifications must be carried out in advance to ensure the performance and the reliability of the variable throttle valve.

Disclosure of Invention

The application aims to provide a variable throttle valve test system and a test method for an aircraft engine, so as to solve or reduce at least one problem in the background art.

In one aspect, the technical solution provided by the present application is: an aircraft engine variable throttle valve test system, comprising:

the bearing cavity simulation cavity is used for simulating a bearing cavity and communicated to a bearing cavity inlet of the variable throttle valve through a pipeline;

the gearbox simulation cavity is used for simulating a gearbox and is communicated with a rear-stage outlet of the variable throttle valve through a pipeline;

the air source is used for providing pressure air for the variable throttle valve and is respectively communicated to an inlet of the bearing cavity simulation cavity and a ventilation inlet of the variable throttle valve through a pipeline provided with a first valve;

the device comprises a bearing cavity simulation cavity, a gear box simulation cavity, a variable throttle valve movable slide valve, a throttle nozzle, a displacement measuring device, a second valve and a flow measuring device, wherein the throttle nozzle is arranged in front of an inlet of the bearing cavity simulation cavity, the displacement measuring device is arranged in the gear box simulation cavity, the displacement measuring device is connected with the variable throttle valve movable slide valve and is used for measuring the movement amount of the slide valve, and the gear box simulation cavity is communicated with the atmosphere through a pipeline provided with the second valve and the flow measuring device.

In the present application, the pressure of the bearing cavity simulation chamber is controlled by adjusting the throttle valve, which is determined according to the seal leakage characteristics of the aircraft engine.

In the application, the volume of the bearing cavity simulation cavity is determined according to the actual volume of the bearing cavity of the aeroengine.

In the present application, the volume of the gearbox simulation cavity is determined according to the actual volume of the bearing cavity of the aircraft engine.

In the application, the front ends of the ventilation inlets of the bearing cavity simulation cavity, the gear box simulation cavity and the variable throttle valve are provided with pressure measuring devices which are respectively used for measuring the internal pressure of the bearing cavity simulation cavity, the internal pressure of the gear box simulation cavity and the pressure of the ventilation inlet of the variable throttle valve.

Further, the pressure measuring device comprises a pressure gauge.

Further, the displacement measuring device comprises a dial indicator.

Further, the flow measuring device comprises a flow meter.

On the other hand, the technical scheme provided by the application is as follows: a test method adopting the test system for the variable throttle valve of the aircraft engine, which comprises the following steps:

adjusting the first valve to enable the pressure of the ventilation inlet of the variable throttle valve to slowly rise;

when the displacement measuring device indicates, the ventilation inlet value of the variable throttle valve is the starting pressure of the variable throttle valve;

then continuing to increase the pressure of the ventilation inlet of the variable throttle valve, and when the displacement measuring device indicates the middle position of the stroke, the value of the ventilation inlet of the variable throttle valve at the moment is the middle pressure of the variable throttle valve;

and then, continuously increasing the pressure of the ventilation inlet of the variable throttle valve, wherein when the displacement measuring device indicates that the full stroke is reached, the value of the ventilation inlet of the variable throttle valve at the moment is the closing pressure of the variable throttle valve.

In a final aspect, the present application provides the following technical solutions: a test method adopting the test system for the variable throttle valve of the aircraft engine, which comprises the following steps:

adjusting the first valve to enable the pressure of the ventilation inlet of the variable throttling valve to slowly rise;

then adjusting the pressure of a ventilation inlet of the variable throttle valve to a preset test value, and acquiring the pressure values and the outlet flow of a bearing cavity simulation cavity and a gear box simulation cavity after the test value parameters are stable;

and obtaining the resistance performance of the variable throttle valve under preset pressure and flow according to the difference value of the pressure values of the bearing cavity simulation cavity and the gearbox simulation cavity.

The test system provided by the application can simulate the functional relation between the engine control air source and the bearing cavity pressure relatively truly, so that various performances of the variable throttle valve can be obtained accurately, and the reliability of the device in use on the engine is improved.

Drawings

In order to more clearly illustrate the technical solutions provided by the present application, the following briefly introduces the accompanying drawings. It is to be expressly understood that the drawings described below are only illustrative of some embodiments of the invention.

Fig. 1 shows a variable throttle valve of an aircraft engine of typical construction.

FIG. 2 is a schematic view of an aircraft engine variable throttle valve testing system according to the present application.

Reference numerals:

1-variable throttle valve

2-gas source

3-valve

4-throttling nozzle

5-bearing cavity simulation cavity

6-gear box simulation cavity

7-Displacement measuring device

8-flow measuring device

Detailed Description

In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present application.

The application aims at providing a test system capable of simulating that the change rule of gas pressure and bearing cavity pressure under the control of a single gas source is consistent with that of an engine, and under the test system, the relationship between simulated back pressure and bearing cavity pressure is consistent with that of the engine.

As shown in fig. 1, a variable throttle valve 1 of a typical structure has a housing 101 of a three-way structure, and a spool valve 102 is provided inside the housing 101, and the spool valve 102 is supported by a spring 103. The second inlet 104 of the variable throttle valve 1 is connected to the bearing cavity, and sealed bleed air is realized by using pressure gas in the bearing cavity, and the sealed bleed air has a certain pressure and provides a certain pressure to the slide valve 102. The first inlet 103 of the variable throttle valve is communicated with pressure gas, when the pressure gas is introduced into the first inlet 103 of the variable throttle valve, the pressure gas overcomes the elastic force of the spring 103 and the bearing cavity pressure to move the slide valve 102 to the left side to assume an open state, and the pressure gas is discharged from the third outlet 105 to a rear stage structure and finally to the atmosphere.

As shown in fig. 1, the test system for the variable throttle valve of the aircraft engine provided by the application mainly comprises: the device comprises a variable throttle valve 1 (namely a tested piece), an air source 2, a valve 3, a throttle nozzle 4, a bearing cavity simulation cavity 5, a gear box simulation cavity 6, a displacement measuring device 7, a flow measuring device 8, a plurality of pressure measuring devices and pipelines.

The bearing cavity simulation cavity 5 is used for simulating a bearing cavity in a real engine, and an outlet of the bearing cavity simulation cavity 5 is communicated to an inlet of the bearing cavity of the variable throttle valve 1 through a pipeline;

the gearbox simulation cavity 6 is used for simulating a gearbox of a real engine, and an inlet of the gearbox simulation cavity 6 is communicated with a rear-stage outlet of the variable throttle valve 1 through a pipeline;

the air source 2 is used for providing pressure air for the variable throttle valve 1 to control the opening and closing of the variable throttle valve 1, and the air source 2 is respectively communicated to an inlet of the bearing cavity simulation cavity 5 and a ventilation inlet of the variable throttle valve 1 through a pipeline provided with a first valve 31;

the throttle nozzle 4 is arranged in front of an inlet of the bearing cavity simulation cavity 5, the displacement measuring device 7 is arranged in the gear box simulation cavity 6, the displacement measuring device 7 is connected with the movable slide valve of the variable throttle valve 1 and used for measuring the movement amount of the slide valve, and the gear box simulation cavity 6 is communicated with the atmosphere through a pipeline provided with a second valve 32 and a flow measuring device 8.

In the present application, the chamber pressure in the bearing chamber simulation chamber 5 is controlled by fixing the throttle valve 4, the throttle valve 4 being determined according to the seal leakage characteristics of the aircraft engine. The volume of the bearing cavity simulation cavity 5 is determined according to the actual volume of the bearing cavity of the aero-engine, and the volume of the gearbox simulation cavity 6 is determined according to the actual volume of the bearing cavity of the aero-engine.

In addition, in the test system of this application, bearing chamber simulation chamber 5, gear box simulation chamber 6 and variable throttle valve 1's ventilation inlet front end are equipped with pressure measurement device, are used for measuring bearing chamber simulation chamber 5 internal pressure, gear box simulation chamber 6 internal pressure and variable throttle valve 1's ventilation inlet pressure respectively.

In this embodiment of the present application, the pressure measuring device is pressure gauges P1-P3, the displacement measuring device 7 adopts a dial indicator, and the flow measuring device 7 is a flowmeter.

In order to be able to view the values displayed by the displacement measuring device 7, a transparent viewing window is provided in the gearbox simulation chamber 6, through which the measured values of the displacement measuring device 7 can be viewed.

In addition, the application also provides a test method based on the test system, the test method mainly comprises an opening and closing pressure calibration test and a throttling characteristic test of the variable throttling valve 1, and the specific test method or steps are as follows:

first, open/close pressure calibration test of variable throttle valve 1

1.1, firstly, adjusting a first valve 31 to enable a pressure gauge P1 to rise slowly (at the moment, the pressure gauge P2 and the pressure gauge P3 also rise along with the rising), enabling a slide valve inside a tested piece to be under the action of air source pressure, and if the acting force is larger than the resistance of a spring, indicating a displacement measuring device, namely a dial indicator;

1.2, when the dial indicator indicates, the pressure value of the pressure gauge P1 is the starting pressure of the tested piece;

1.3, continuously increasing the inlet pressure of the tested piece (measured by a pressure gauge P1), wherein when the dial indicator indicates the middle of the stroke, the pressure value of the pressure gauge P1 is the middle pressure of the tested piece;

1.4, then continuously increasing the inlet pressure of the tested piece (measured by a pressure gauge P1), and when the dial indicator indicates that the full stroke is reached, the pressure value P1 is the closing pressure of the tested piece.

It should be noted that, in the above process, the full stroke of the dial indicator is equal to the moving stroke of the slide valve in the variable throttle valve, and a large-stroke dial indicator whose full stroke is greater than the moving stroke of the oil may be adopted as required, the full stroke in step 1.4 is the corresponding position of the large-stroke dial indicator, and the intermediate value in step 1.3 is the intermediate value of the corresponding position. In addition, the bearing chamber pressure P2 can be controlled by the throttle valve 4, and the initial chamber pressure P3 of the gear box simulation chamber 6 can be adjusted and controlled by the second valve 32.

Second, resistance performance test of (tested piece) of variable throttle valve 1

2.1, removing a dial indicator in the gear box simulation cavity 6;

2.2, adjusting the first valve 31 to enable the pressure gauge P1 to rise slowly (at the moment, the pressure gauges P2 and P3 rise along with the rise);

2.3, adjusting the inlet pressure (measured by a pressure gauge P1) of the tested piece to a certain test value, and extracting the pressure values displayed by the pressure gauge P2 and the pressure gauge P3 and the outlet flow rate displayed by the flow meter after the parameters are stable;

2.4, the difference value between the pressure gauge P2 and the pressure gauge P3 is the resistance performance of the tested piece under a certain pressure and flow.

The test system and the test method provided by the application overcome the problem that when the conventional simple method is used for verification, the simulation test system controls the actuating mechanism based on a single air source, the backpressure is atmospheric pressure, and parameters capable of meeting the working requirements of the engine cannot be obtained (the higher the state is, the larger the difference is), and the like.

The test system and the test method provided by the application have the following advantages:

1) the test system can simulate the functional relation between the engine control air source and the bearing cavity pressure more truly, so that various performances of the variable throttle valve can be obtained accurately, and the reliability of the device in use on the engine is improved;

2) the test method can directly and simply measure the starting pressure, the middle pressure and the stopping pressure of the variable throttle valve;

3) the test method has the advantages of simple structure, convenience in operation and accurate and reliable test result.

The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.