Measuring device for atmospheric parameters of tail jet flow of aero-engine

Abstract

The utility model discloses an aero-engine tail jet flow atmospheric parameter measuring device, belongs to the technical field of aero-engine infrared characteristic measuring devices, and solves the technical problem that the aero-engine tail jet flow atmospheric parameter measurement is inaccurate. The device comprises a base, a driving module, a transmission module, a rotating rod, an airflow conduit, an atmospheric parameter sensor, a power supply and a computer. And a probe of the atmospheric parameter sensor is arranged in the airflow conduit and is communicated with the computer. The driving module and the transmission module are installed on the base, and the rotating rod is connected with the base through the transmission module. The airflow guide pipe is fixedly connected with the rotating rod and can pitch along with the rotating rod. The rotating rod is connected with the driving module and the transmission module. The aero-engine tail jet flow atmospheric parameter measuring device is used for measuring aero-engine tail jet flow atmospheric parameters.

Description

Technical Field

[0001] The utility model belongs to the technical field of aircraft engine infrared characteristic measuring devices, in particular to a measuring device for atmospheric parameters of an aircraft engine tail jet. Background Art

[0002] The infrared radiation characteristics of an aircraft engine are a key indicator for measuring its infrared stealth performance. To assess and evaluate an aircraft engine's infrared stealth performance, it is necessary to obtain the engine's true infrared radiation characteristics. Infrared radiation characteristic testing is the only way to obtain the target's true radiation characteristics. During aircraft engine infrared radiation characteristic testing, the infrared radiation energy is attenuated by atmospheric transmittance, resulting in the radiation intensity received by the detector being lower than the actual value of the aircraft engine, affecting the accuracy of the test results. To obtain the engine's true infrared radiation characteristics, it is necessary to accurately calculate the atmospheric transmittance along the test path.

[0003] In the static infrared characteristic test of aircraft engines on the ground, atmospheric parameter sensors can be arranged on the test path at different angles, and the atmospheric parameters of the tail jet can be obtained to calculate the atmospheric transmittance on this path; however, since the engine test bench is at a certain height from the ground, the tail jet is a high-speed and high-pressure gas during the engine test, and the atmospheric parameter sensor is difficult to fix on the engine axis. The current practice is to place the atmospheric parameter sensor on the ground. Therefore, the atmospheric parameter sensor placed horizontally on the ground in the past cannot collect real data on the engine axis; at the same time, if the atmospheric parameter sensor is fixed on the engine axis, it will inevitably affect the infrared detector's test of the engine's infrared radiation intensity, which not only affects the measurement accuracy of the tail jet's atmospheric transmittance, but also is related to the success or failure of the aircraft engine infrared characteristic test.

[0004] Chinese invention patent CN110907188B discloses a method for selecting the length of the tail jet flow direction test section for infrared radiation testing. This method rapidly evaluates and interprets the lengths of the initial and main sections of the tail plume to select an appropriate distance for infrared radiation characteristic testing, thereby improving the signal-to-noise ratio of the measurement results and ensuring the accuracy and repeatability of the measurement results. Alternatively, the method rapidly evaluates the proportion of infrared radiation emitted by the initial and main sections of the tail plume within the entire tail plume. If the effect of the main section's radiation on the test results is negligible, only the infrared radiation of the initial section of the tail plume needs to be tested. Alternatively, if the ratio of the initial and main sections remains constant, the infrared radiation of the entire tail plume can be deduced from the infrared radiation of the initial section. However, this method still cannot directly measure the infrared radiation of the entire tail plume, and its accuracy is somewhat insufficient. Utility Model Content

[0005] In order to overcome the deficiency that accurate atmospheric transmittance calculation parameters cannot be obtained in the measurement of infrared characteristics of aircraft engines, the utility model proposes a device for measuring atmospheric parameters of aircraft engine tail jet.

[0006] The technical solution adopted by the utility model to solve its technical problems is:

[0007] A device for measuring atmospheric parameters of an aircraft engine tail jet comprises a base, a drive module, a transmission module, a rotating rod, an airflow duct, an atmospheric parameter sensor, a power supply, and a computer.

[0008] The probe of the atmospheric parameter sensor is placed in the airflow duct to collect atmospheric parameters passing through the airflow duct and is connected to a computer, which is used to display the atmospheric parameters. A power supply is used to power the drive module, the atmospheric parameter sensor, and the computer.

[0009] The drive module and transmission module are mounted on a base, and the rotating rod is connected to the base via the transmission module. The airflow duct is fixedly connected to the rotating rod and can pitch and tilt with the rotating rod. The rotating rod is connected to the drive module and transmission module, and the drive module and transmission module are used to drive the rotating rod to pitch between horizontal ground and vertical planes.

[0010] In the above-mentioned measuring device, the pitch angle of the rotating rod in pitching motion between the horizontal ground and the vertical plane is 0° to 90°.

[0011] The measuring device further includes an angle adjustment mechanism, which is located between the rotating rod and the airflow conduit, wherein the airflow conduit, the angle adjustment mechanism, and the rotating rod are connected in sequence. The airflow conduit can rotate with the angle adjustment mechanism.

[0012] The measuring device further comprises a height adjustment mechanism, which is located between the rotating rod and the airflow conduit, wherein the airflow conduit, the height adjustment mechanism and the rotating rod are sequentially connected. The airflow conduit can move up and down along with the height adjustment mechanism.

[0013] The measuring device further includes a height adjustment mechanism located between the rotating rod and the angle adjustment mechanism, wherein the airflow conduit, the angle adjustment mechanism, the height adjustment mechanism, and the rotating rod are sequentially connected. The airflow conduit and the angle adjustment mechanism can move up and down together with the height adjustment mechanism.

[0014] In the above-mentioned measuring device, the driving module includes a gear driving motor and a rod driving motor. The transmission module includes a main transmission rod, a left transmission rod, a right transmission rod, a circular gear, and a horizontal gear.

[0015] The rod driving motor is used to drive the main transmission rod, the left transmission rod and the right transmission rod. The main transmission rod, the left transmission rod and the right transmission rod are respectively connected to the rotating rod and the base.

[0016] The gear drive motor is used to drive the circular gear and the horizontal gear, and the circular gear and the horizontal gear are connected to the rotating rod and the base respectively.

[0017] In the above-mentioned measuring device, the horizontal cross-section of the rotating rod parallel to the direction of the aircraft engine tail jet is streamlined.

[0018] The beneficial effects of the utility model are:

[0019] A device for measuring atmospheric parameters of an aircraft engine tail jet has an adjustable rotating rod height and is suitable for various aircraft engine test benches and test sites. The rotating rod has a streamlined cross-section, which reduces the device's impact on the engine tail jet flow.

[0020] A device for measuring atmospheric parameters of aircraft engine tail jets. A driving module and a transmission module can be used to rotate a rotating rod 90 degrees, accurately measuring atmospheric parameters such as temperature, pressure, humidity, carbon dioxide concentration, and carbon monoxide concentration at different positions on the engine axis. After the measurement is completed, the rotating rod can be retracted into the base to wait for the next engine operating state to avoid affecting the detector's test of the engine's infrared characteristics.

[0021] A device for measuring atmospheric parameters of an aircraft engine tail jet can rotate the angle of an airflow duct through an angle adjustment device and can be used to collect atmospheric parameters on test paths at different angles. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] Figure 1 It is a schematic structural diagram of a measuring device according to an embodiment of the present utility model.

[0023] Figure markings: 1. Base; 4. Rotating rod; 5. Air flow duct; 6. Angle adjustment mechanism; 7. Atmospheric parameter sensor; 9. Height adjustment mechanism; 10. Computer; 21. Gear drive motor; 22. Rod drive motor; 31. Main transmission rod; 32. Left transmission rod; 33. Right transmission rod; 34. Circular gear; 35. Horizontal gear. DETAILED DESCRIPTION

[0024] The present invention will be further described in detail below with reference to the accompanying drawings and specific embodiments.

[0025] Example 1

[0026] The positional relationship between the tail jet direction and the device is determined according to the relevant test requirements in GJB 241A-2010 "General Specifications for Aviation Turbojet and Turbofan Engines". During ground testing, the centerline behind the engine is defined as the azimuth angle of 0°. In the test, a total of 11 test azimuth angles are tested, namely 0°, 5°, 10°, 15°, 20°, 30°, 40°, 60°, 90°, 135°, and 180°.

[0027] A device for measuring atmospheric parameters of aircraft engine tail jet, such as Figure 1 As shown, it mainly includes a base 1, a drive module, a transmission module, a rotating rod 4, an airflow duct 5, an angle adjustment mechanism 6, an atmospheric parameter sensor 7, a power supply, a height adjustment mechanism 9, and a computer 10.

[0028] The base 1 serves as a fixed connection device, on which the drive module and the transmission module are installed, and the atmospheric parameter sensor 7 is placed.

[0029] The driving module includes a gear driving motor 21 and a rod driving motor 22 .

[0030] The transmission module includes a main transmission rod 31, a left transmission rod 32, a right transmission rod 33, a circular gear 34, and a horizontal gear 35. The motor drives the main transmission rod 31 to extend and rotate, while the circular gear 34 moves left and right on the horizontal gear 35. The transmission of the rods and the movement of the gears cause the rotating rod 4 to rotate 0° to 90°.

[0031] The rotating rod 4 can rotate 90 degrees back and forth between the horizontal ground and the vertical under the action of the driving module and the transmission module.

[0032] The airflow duct 5 can provide a channel for the flow of tail jets on test paths at different angles, ensuring that the tail jet gas contacted by the probe of the atmospheric parameter sensor is not affected.

[0033] The angle adjustment mechanism 6 allows for flexible and accurate adjustment of the airflow duct angle, maintaining the stresses applied to the device when measuring atmospheric parameters along test paths at different angles, thereby ensuring efficient control of the movement of the rotating rod by the drive and transmission devices. The angle adjustment mechanism 6 can employ conventional screw locking, sleeve thread locking, or other similar mechanisms.

[0034] The atmospheric parameter sensor 7 is fixed to the base, and the sensor probe is connected to the airflow duct. The instrument probe samples and detects, and the data is transmitted to the computer in real time.

[0035] The power supply provides electrical energy to the driving module, the atmospheric parameter sensor 7 and the computer.

[0036] The height adjustment mechanism 9 can manually adjust the height of the device, making this device suitable for various aircraft engine test benches and test sites. The height adjustment mechanism 9 can adopt a telescopic rod, a hydraulic rod, etc.

[0037] The computer receives the signal from the atmospheric parameter sensor and displays the digital signal collected by the atmospheric parameter sensor.

Claims

1. A device for measuring atmospheric parameters of an aircraft engine tail jet, characterized in that: It includes a base (1), a driving module, a transmission module, a rotating rod (4), an airflow conduit (5), an atmospheric parameter sensor (7), a power supply, and a computer (10); The probe of the atmospheric parameter sensor (7) is placed in the airflow conduit (5) and is used to collect the atmospheric parameters of the tail jet passing through the airflow conduit (5). The probe is connected to the computer (10), and the computer (10) is used to display the atmospheric parameters of the tail jet; The power supply is used to power the driving module, the atmospheric parameter sensor (7), and the computer (10); The driving module and the transmission module are mounted on the base (1); the rotating rod (4) is connected to the base (1) via the transmission module; the airflow conduit (5) is fixedly connected to the rotating rod (4) and can pitch along with the rotating rod (4); the rotating rod (4) is connected to the driving module and the transmission module, and the driving module and the transmission module are used to drive the rotating rod (4) to pitch between the horizontal ground and the vertical plane.

2. The measuring device according to claim 1, characterized in that: The pitch angle of the rotating rod (4) in pitching motion between the horizontal ground and the vertical plane is 0° to 90°.

3. The measuring device according to claim 1, characterized in that: The invention also includes an angle adjustment mechanism (6), which is located between the rotating rod (4) and the air flow duct (5). The air flow duct (5), the angle adjustment mechanism (6), and the rotating rod (4) are connected in sequence; the air flow duct (5) can rotate with the angle adjustment mechanism (6).

4. The measuring device according to claim 1, characterized in that: The utility model further comprises a height adjustment mechanism (9), wherein the height adjustment mechanism (9) is located between the rotating rod (4) and the air flow conduit (5), and the air flow conduit (5), the height adjustment mechanism (9), and the rotating rod (4) are sequentially connected; and the air flow conduit (5) can move up and down along with the height adjustment mechanism (9).

5. The measuring device according to claim 3, characterized in that: The invention also includes a height adjustment mechanism (9), wherein the height adjustment mechanism (9) is located between the rotating rod (4) and the angle adjustment mechanism (6), and the air flow duct (5), the angle adjustment mechanism (6), the height adjustment mechanism (9), and the rotating rod (4) are connected in sequence; the air flow duct (5) and the angle adjustment mechanism (6) can move up and down together with the height adjustment mechanism (9).

6. The measuring device according to claim 1, characterized in that: The driving module includes a gear driving motor (21) and a rod driving motor (22); the transmission module includes a main transmission rod (31), a left transmission rod (32), a right transmission rod (33), a circular gear (34), and a horizontal gear (35); The rod driving motor (22) is used to drive the main transmission rod (31), the left transmission rod (32), and the right transmission rod (33); the main transmission rod (31), the left transmission rod (32), and the right transmission rod (33) are respectively connected to the rotating rod (4) and the base (1); The gear drive motor (21) is used to drive the circular gear (34) and the horizontal gear (35), and the circular gear (34) and the horizontal gear (35) are respectively connected to the rotating rod (4) and the base (1).

7. The measuring device according to claim 1, characterized in that: The horizontal cross section of the rotating rod (4) parallel to the direction of the aircraft engine tail jet is streamlined.

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