Aero-engine simulation experiment table of multifunctional testing device

Abstract

The invention discloses an aero-engine simulation experiment table of a multifunctional testing device. The experiment table comprises an experiment table shell, a sensor information processing system, a detachable turbine disc assembly, a double-layer vacuum heat insulation exhaust nozzle, a power interface, an intelligent water storage system and a blade heating monitoring system. The method has the advantages that the experiment table adopts the NACA airfoil profile to construct the bionic shell, and the proportion of the curvature of the front edge to the chord length is strictly matched with the geometrical characteristics of the aero-engine fan casing. The air inlet system is designed to be a three-channel gradually-shrinking flow channel, all the channels are separated through asymmetric flow guide rib plates, the shrinkage ratio of the flow channel is optimized according to the typical working condition of a civil aviation engine, and the air inlet acceleration effect and the circumferential pressure gradient of the high-bypass-ratio aero-engine can be accurately simulated. The core section is provided with a modularized turbine assembly, a base disc is forged through aviation-grade alloy, a standardized dovetail box connector is arranged so that blade modules of different configurations can be rapidly replaced, and various simulation requirements are met.

Description

Technical Field

[0001] The invention belongs to the technical field of aviation engine maintenance, and in particular relates to an aviation engine simulation test bench of a multifunctional testing device. Background Art

[0002] In the field of deep maintenance of civil aviation engines, the measurement accuracy and realistic simulation of experimental cleaning devices are directly related to the quality of line maintenance and the engine's on-wing time. In the current engine water washing procedures regulated by CAAC CCAR-145, existing engine cleaning test devices suffer from the following deficiencies: 1) insufficient measurement accuracy of the water storage system (generally >±5mL); 2) unrealistic blade temperature field simulation; and 3) the inlet structure fails to replicate the actual aerodynamic environment. Furthermore, while traditional test devices utilize multiple sensors for monitoring, they fail to address temperature compensation and zoned heating. Summary of the Invention

[0003] In order to solve the above problems, the purpose of the present invention is to provide an aviation engine simulation test bench as a multifunctional testing device.

[0004] In order to achieve the above-mentioned purpose, the aviation engine simulation test bench of the multifunctional test device provided by the present invention includes a test bench shell, a sensor information processing system, a detachable turbine disc assembly, a double-layer vacuum insulation tail nozzle, a power interface, an intelligent water storage system and a blade heating monitoring system; wherein, the test bench shell is an annular structure, located at the front of the test bench, and the front port is provided with a three-channel tapered air inlet with a compressed air flow acceleration function, and asymmetric guide ribs are provided between each channel for reproducing the real aerodynamic environment to ensure the rationality of the test bench structure; the detachable turbine disc assembly is installed at the air inlet; the power interface is located at the upper part of the test bench shell for external power supply for subsequent experiments; the intelligent water storage system is located in the middle of the test bench, including an annular water collecting tank, a capacitive liquid level sensor array, a self-cleaning ultrasonic probe, a centrifugal water pump and a temperature compensation module; the annular water collecting tank is installed at the rear end of the test bench shell, and a drain outlet for installing a centrifugal water pump is provided at the bottom of the box, which is used to cooperate with an external water spraying experimental device to carry out water spraying experiments, and the top of the box is provided with The annular water collection tank has a water inlet to ensure sufficient water. A capacitive liquid level sensor array is evenly distributed on the inner circumferential wall of the annular water collection tank. A temperature compensation module is electrically connected to the capacitive liquid level sensor array. A self-cleaning ultrasonic probe is installed at the bottom of the tank. A double-layer vacuum-insulated tail nozzle is installed at the rear end of the annular water collection tank. The blade heating monitoring system includes a PCB-embedded heating film, an aluminum nitride ceramic substrate, an infrared thermal imager, and a thermocouple. The PCB-embedded heating film is attached to the surface of the turbine blade on the removable turbine disk assembly via the aluminum nitride ceramic substrate. The infrared thermal imager and thermocouple form a dual-mode temperature monitoring assembly. Multiple infrared thermal imagers and thermocouples are distributed at the leading edge, blade body, and trailing edge of the turbine blade to form multiple temperature measurement points, thereby achieving zoned control. The sensor information processing system is installed in the center of the removable turbine disk assembly and uses an industrial touch screen. It is electrically connected to the capacitive liquid level sensor array, temperature compensation module, infrared thermal imager, and thermocouple to display the temperature on the turbine blade and the liquid level and temperature information in the annular water collection tank in real time.

[0005] The contraction ratio of the three-channel tapered air inlet is 1:2.5.

[0006] The double-layer vacuum insulation tail nozzle includes a zirconium oxide fiber insulation layer and a 316L stainless steel shell.

[0007] The aluminum nitride ceramic substrate serves as a heating film carrier and has a thickness of 0.8 mm.

[0008] The volume of the annular water collecting tank is 10L, and the bottom of the tank is set at an inclination angle of 5° to facilitate drainage.

[0009] The protection grade of the power interface is IP67.

[0010] The aviation engine simulation test bench of the multifunctional testing device provided by the present invention has the following beneficial effects:

[0011] The test bench utilizes a NACA airfoil profile to create a biomimetic shell, with the leading edge curvature and chord length ratio precisely matching the geometric characteristics of an aircraft engine fan case. The intake system features a three-channel, tapered flow path separated by asymmetric guide ribs. The flow path contraction ratio is optimized for typical civil aviation engine operating conditions, accurately simulating the intake acceleration and circumferential pressure gradient of high-bypass ratio aircraft engines. The core section features a modular turbine assembly, with a forged disc constructed from aircraft-grade alloy and a standardized dovetail box interface for rapid replacement of blade modules with varying configurations, supporting diverse simulation requirements.

[0012] The intelligent fluid management system consists of an annular water collection tank, a capacitive liquid level sensor array, and self-cleaning components. Multiple sets of liquid level sensors are arranged on the inner wall of the water collection tank. Combined with frequency-domain signal processing technology and temperature compensation algorithms, they enable precise metering in the typical vibration environments of aircraft engines. A self-cleaning ultrasonic probe effectively removes jet fuel emulsification residues, ensuring long-term operational stability. The thermodynamic simulation system deploys zoned heating films on the blade surface, with a gradient power density design in the leading edge area to simulate the thermal radiation effects of the combustion chamber. A composite temperature measurement network integrates armored thermocouple and infrared thermal imager data, reconstructing the three-dimensional temperature field using a Kalman filter algorithm. This fully captures the microscopic thermal stress changes during the thermal shock of aircraft engines. BRIEF DESCRIPTION OF THE DRAWINGS

[0013] Figure 1 Schematic diagram of the overall structure of the aviation engine simulation test bench of the multifunctional testing device provided by the present invention.

[0014] Figure 2 A cross-sectional view of the intelligent water storage system in the aviation engine simulation test bench of the multifunctional testing device provided by the present invention.

[0015] Figure 3 This is a layout diagram of the blade heating monitoring system in the aviation engine simulation test bench of the multifunctional testing device provided by the present invention. DETAILED DESCRIPTION

[0016] The present invention will be described in detail below with reference to the accompanying drawings and specific embodiments.

[0017] like Figure 1-Figure 3As shown, the aviation engine simulation test bench of the multifunctional test device provided by the present invention includes a test bench shell 1, a sensor information processing system 3, a detachable turbine disc assembly 4, a double-layer vacuum insulation tail nozzle 5, a power interface 6, an intelligent water storage system 7 and a blade heating monitoring system; wherein, the test bench shell 1 is an annular structure, located at the front of the test bench, and the front port is provided with a three-channel tapered air inlet 2, which has a compressed air flow acceleration function, and asymmetric guide ribs are provided between each channel to reproduce the real aerodynamic environment to ensure the rationality of the test bench structure; The turbine disc assembly 4 is installed at the air inlet 2; the power interface 6 is located at the upper part of the experimental platform shell 1, which is used for external power supply to facilitate subsequent experiments; the intelligent water storage system 7 is located in the middle of the experimental platform, including an annular water collecting tank 8, a capacitive liquid level sensor array 9, a self-cleaning ultrasonic probe 10, a centrifugal water pump 11 and a temperature compensation module 13; the annular water collecting tank 8 is installed at the rear end of the experimental platform shell 1, and a drain port for installing the centrifugal water pump 11 is provided at the bottom of the tank, which is used to cooperate with an external water spraying experimental device to carry out water spraying experiments, and a water injection port 12 is provided on the top of the tank to ensure the annular water collecting tank The water tank 8 has sufficient water; the capacitive liquid level sensor array 9 is evenly distributed on the inner circumferential wall of the annular water collecting tank 8; the temperature compensation module 13 is electrically connected to the capacitive liquid level sensor array 9; the self-cleaning ultrasonic probe 10 is installed at the bottom of the tank; the double-layer vacuum insulation tail nozzle 5 is installed at the rear end of the annular water collecting tank 8; the blade heating monitoring system includes a PCB embedded heating film 14, an aluminum nitride ceramic substrate 15, an infrared thermal imager 16 and a thermocouple 17; the PCB embedded heating film 14 is attached to the turbine on the detachable turbine disc assembly 4 through the aluminum nitride ceramic substrate 15 Blade surface; infrared thermal imager 16 and thermocouple 17 constitute a dual-mode temperature monitoring component, and multiple infrared thermal imagers 16 and thermocouples 17 are distributed at the leading edge, blade body and trailing edge of the turbine blade to constitute multiple temperature measuring points, thereby realizing zone control; the sensor information processing system 3 is installed in the middle of the detachable turbine disc assembly 4, adopts an industrial touch screen, and is electrically connected to the capacitive liquid level sensor array 9, the temperature compensation module 13, the infrared thermal imager 16 and the thermocouple 17, respectively, for real-time display of the temperature on the turbine blade and the liquid level and temperature information in the annular water collecting tank 8.

[0018] The contraction ratio of the three-channel tapered air inlet 2 is 1:2.5.

[0019] The double-layer vacuum insulation tail nozzle 5 includes a zirconium oxide fiber insulation layer and a 316L stainless steel shell.

[0020] The aluminum nitride ceramic substrate 15 serves as a heating film carrier and has a thickness of 0.8 mm.

[0021] The annular water collecting tank 8 has a capacity of 10 L and a bottom thereof is provided with an inclination angle of 5° for easy drainage.

[0022] The protection grade of the power interface 6 is IP67.

[0023] The method for using the aviation engine simulation test bench of the multifunctional testing device provided by the present invention is described as follows:

[0024] During the experimental preparation phase, the operator must install a dedicated water spray test device beneath the test bench housing 1 and connect it to the centrifugal water pump 11 on the intelligent water storage system 7 via a quick-connect interface. Then, connect the device to a 380V three-phase AC power supply through the power interface 6 located on the upper portion of the test bench housing 1. The blade heating monitoring system is activated, and the PCB-embedded heating film 14, through the uniform thermal conductivity of the aluminum nitride ceramic substrate 15, gradiently heats the turbine blades on the removable turbine disk assembly 4. The infrared thermal imager 16 and thermocouple 17, comprising the dual-mode temperature monitoring assembly, provide real-time feedback on the temperature distribution at multiple temperature measurement points along the leading edge, blade body, and trailing edge of the turbine blades, displaying this information on the sensor information processing system 3. Parameters are monitored during the experiment, and when the turbine blade temperature reaches a set threshold, the sensor information processing system 3 triggers an audible and visual prompt. At this time, the sensor information processing system 3 can be used to observe: the surface temperature field distribution of the turbine blades provided by the infrared thermal imager 16, the multi-point water level monitoring data provided by the capacitive liquid level sensor array 9, and the water level value corrected by the temperature compensation module 13; then a water spraying experiment is carried out. After confirming that the system is in normal condition, the centrifugal water pump 11 in the intelligent water storage system 7 is started. Several points should be noted during the experiment: keep the water level in the annular water collecting tank 8 not lower than the minimum warning line of 2L, regularly discharge sediments through the drain port designed at a 5° tilted bottom of the tank, and the self-cleaning ultrasonic probe 10 automatically starts every 30 minutes; when the capacitive liquid level sensor array 9 detects that the water storage volume in the annular water collecting tank 8 is lower than the preset value, the operator should add water through the top quick water injection port 12; after the experiment, the blade heating monitoring system must be turned off first, and the power supply should be disconnected after the turbine blade temperature drops below 50°C.

Claims

1. An aerospace engine simulation test bench with a multifunctional testing device, characterized by: The aerospace engine simulation test bench of the multifunctional test device comprises a test bench housing (1), a sensor information processing system (3), a detachable turbine disc assembly (4), a double-layer vacuum insulation tail nozzle (5), a power interface (6), an intelligent water storage system (7) and a blade heating monitoring system; wherein the test bench housing (1) is an annular structure and is located at the front of the test bench, and a front port is provided with a three-channel tapered air inlet (2), and asymmetric guide ribs are provided between each channel; the detachable turbine disc assembly (4) is installed at the air inlet (2); the power interface (6) Located at the upper part of the experimental platform shell (1); the intelligent water storage system (7) is located in the middle of the experimental platform, including an annular water collecting tank (8), a capacitive liquid level sensor array (9), a self-cleaning ultrasonic probe (10), a centrifugal water pump (11) and a temperature compensation module (13); the annular water collecting tank (8) is installed at the rear end of the experimental platform shell (1), a drainage port for installing the centrifugal water pump (11) is provided at the bottom of the tank, and a water injection port (12) is provided at the top of the tank; the capacitive liquid level sensor array (9) is evenly distributed on the inner circumferential wall of the annular water collecting tank (8); the temperature compensation module ( 13) is electrically connected to the capacitive liquid level sensor array (9); a self-cleaning ultrasonic probe (10) is installed at the bottom of the box; a double-layer vacuum insulation tail nozzle (5) is installed at the rear end of the annular water collecting box (8); the blade heating monitoring system includes a PCB embedded heating film (14), an aluminum nitride ceramic substrate (15), an infrared thermal imager (16) and a thermocouple (17); the PCB embedded heating film (14) is attached to the surface of the turbine blade on the detachable turbine disk assembly (4) through the aluminum nitride ceramic substrate (15); the infrared thermal imager (16) and the thermocouple (17) A dual-mode temperature monitoring assembly is formed, and multiple infrared thermal imagers (16) and thermocouples (17) are distributed at the leading edge, blade body and trailing edge of the turbine blade to form multiple temperature measurement points, thereby realizing zone control; the sensor information processing system (3) is installed in the middle of the detachable turbine disk assembly (4), adopts an industrial touch screen, and is electrically connected to the capacitive liquid level sensor array (9), the temperature compensation module (13), the infrared thermal imager (16) and the thermocouple (17), respectively, for real-time display of the temperature on the turbine blade and the liquid level and temperature information in the annular water collecting tank (8).

2. The aviation engine simulation test bench of the multifunctional testing device according to claim 1, characterized in that: The contraction ratio of the three-channel tapered air inlet (2) is 1:2.

5.

3. The aircraft engine simulation test bench of the multifunctional testing device according to claim 1, characterized in that: The double-layer vacuum insulation tail nozzle (5) comprises a zirconium oxide fiber insulation layer and a 316L stainless steel outer shell.

4. The aircraft engine simulation test bench of the multifunctional testing device according to claim 1, characterized in that: The aluminum nitride ceramic substrate (15) serves as a heating film carrier and has a thickness of 0.8 mm.

5. The aircraft engine simulation test bench of the multifunctional testing device according to claim 1, characterized in that: The annular water collecting tank (8) has a capacity of 10 L and a 5° tilt angle is set at the bottom of the tank to facilitate drainage.

6. The aircraft engine simulation test bench of the multifunctional testing device according to claim 1, characterized in that: The protection grade of the power interface (6) is IP67.

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