A turbofan engine inlet temperature simulation temperature field online monitoring method and system

Abstract

The application discloses a turbofan engine inlet temperature simulation temperature field online monitoring method, which comprises the following steps: expanding the temperature field section of the engine inlet channel according to the polar coordinates, dividing the temperature field section into m parts along the circumferential direction clockwise and dividing the temperature field section into n equal parts along the radial direction, so as to obtain an m*n grid area, each grid area represents the temperature value of a unit body, and the temperature value of each unit body is obtained; the radial average temperature of each angular position and the surface average temperature of the temperature field section are obtained according to the temperature value of each unit body; the circumferential range of the high-temperature zone is determined according to the distribution of the area-weighted radial average value measured at different radii on the aerodynamic interface along the circumferential direction, the average value of the airflow temperature in the high-temperature zone is calculated, the temperature field unevenness and the temperature distortion intensity are calculated according to the average value of the airflow temperature in the high-temperature zone, and at least one of the circumferential range of the high-temperature zone, the average value of the airflow temperature in the high-temperature zone, the temperature field unevenness and the temperature distortion intensity is displayed in real time.

Description

Technical Field

[0001] This application belongs to the field of aero-engine testing technology, and specifically relates to an online monitoring method and system for simulating the temperature field of turbofan engine inlet temperature. Background Technology

[0002] Ground-based inlet temperature simulation for turbofan engines is a crucial part of sustained pre-flight testing and is one of the engine type approval tests stipulated in relevant standards. It is an important test for assessing the engine's reliability and operational capabilities. Inlet heating testing plays a vital role at every stage of development. The inlet heating simulation device in engine testing is a crucial link between ground testing and flight testing, performance compliance and structural reliability, and overall engine durability assessment and component life analysis. One of the common problems encountered during turbofan engine operation is the aerodynamic instability of the compression system. Due to the complex structure of the inlet heating simulation device and its essential air intake channel, the non-uniformity of the engine inlet temperature field becomes a key test parameter, directly affecting the engine's operational safety, in addition to the parameters monitored on the ambient temperature test bench.

[0003] While mature temperature field evaluation criteria exist in China, they primarily rely on post-experiment analysis and evaluation of the temperature field based on obtained experimental data. This evaluation process mainly employs a semi-automatic approach, utilizing data processing software like Excel for simplified linear interpolation analysis after data acquisition. Furthermore, this method only provides data on the circumferential non-uniformity and circumferential distortion index of the temperature field, failing to obtain the angular positions θ, number, and circumferential range θ of the high-temperature and low-temperature zones at the engine inlet in this experiment. + Important information such as temperature field distortion cannot be accurately determined online due to the lack of conditions for online monitoring. During actual test runs, abnormal factors such as equipment malfunctions can cause sudden changes in air supply conditions and temperature field distortion. Furthermore, the inability to promptly and accurately pinpoint the angular location of the temperature field anomaly and take appropriate action can seriously jeopardize engine safety. Summary of the Invention

[0004] The purpose of this application is to provide a method and system for online monitoring of the simulated temperature field of a turbofan engine inlet, so as to solve or mitigate at least one of the problems in the background art.

[0005] The technical solution of this application is: a method for online monitoring of simulated temperature field at the inlet temperature of a turbofan engine, the method comprising:

[0006] The temperature field section of the engine intake duct is unfolded in polar coordinates, divided into m equal parts clockwise along the circumference, and divided into n equal parts radially along equal toroidal planes, resulting in an m×n grid region. Each grid region represents the temperature value of a single element, and the temperature value T of each element is obtained. i,j (θ,r), where θ is the circumferential angle and r is the radial radius;

[0007] According to the temperature value T of each unit body i,j (θ, r) obtains the radial average temperature T of each angular position r (θ) and the surface average temperature T of the temperature field section 2FAV ;

[0008] According to the circumferential distribution of the area-weighted radial average value measured at different radii on the aerodynamic interface, the circumferential range θ of the high-temperature zone is determined + , the average value T of the airflow temperature in the high-temperature zone is calculated HAV , the average value T of the airflow temperature in the high-temperature zone is calculated HAV , the temperature field non-uniformity is calculated and the temperature distortion strength δT 2FAV ;

[0009] At least one of the circumferential range of the high-temperature zone, the average value of the airflow temperature in the high-temperature zone, the temperature field non-uniformity, and the temperature distortion strength is displayed in real time.

[0010] Further, the temperature value T of each unit body is obtained by polynomial fitting i,j (θ, r).

[0011] Further, the radial average temperature calculation method of each angular position is:

[0012]

[0013] In the formula, is the relative radius of the hub;

[0014] is the radial radius at the circumferential θ;

[0015] is the total temperature at the hub

[0016] Further, the surface average temperature calculation method of the temperature field section is:

[0017]

[0018] Further, the average value calculation method of the airflow temperature in the high-temperature zone is:

[0019]

[0020] Further, the average value T of the airflow temperature in the high-temperature zone is calculated HAV The calculation method of the temperature field non-uniformity is:

[0021]

[0022] Further, according to the average value T of the temperature of the airflow in the high-temperature zone HAV The calculation method for calculating the temperature distortion intensity is as follows:

[0023]

[0024] In the formula, T0 is the total temperature of the undisturbed airflow before the engine.

[0025] In addition, the application also provides a turbofan engine inlet temperature simulation temperature field online monitoring system, the monitoring system comprises: an engine air inlet, a multi-branch point temperature test rake, a temperature compensation lead, a temperature scanning valve, a test run data acquisition server, an Ethernet switch, a temperature field online monitoring computer and a temperature field online monitoring analysis platform.

[0026] When the air inlet warming simulation test run is performed, the temperature scanning valve in the test run data acquisition system automatically acquires the temperature sensed by the annular multi-branch point temperature test rake in the engine air inlet in real time, and stores the temperature in the test run data acquisition system server. The temperature field online monitoring computer receives the engine air inlet inlet temperature data acquired by the test run data acquisition system through the Ethernet switch, and processes and calculates the current engine inlet average temperature, temperature field unevenness, temperature field circumferential distortion index and temperature field maximum temperature difference in real time through the temperature field online monitoring analysis platform installed on the temperature field online monitoring computer according to the method in any one of claims 1 to 7, and displays the temperature field change through a visual cloud map.

[0027] The online monitoring system and method provided by the application can intuitively display the engine temperature field uniformity during air inlet warming in real time, give the calculation results of the temperature field unevenness, distortion index, high-temperature zone angular position and range, maximize the visualization and automation of the temperature field, reduce the error of the calculation results, save manpower and time cost, improve the emergency response ability of the test site, and ensure the safety of the engine test run. BRIEF DESCRIPTION OF DRAWINGS

[0028] In order to more clearly illustrate the technical solutions provided by the application, the following will briefly introduce the drawings. Obviously, the drawings described below are only some embodiments of the application.

[0029] Figure 1 The figure is a schematic diagram of the turbofan engine inlet temperature simulation temperature field online monitoring system of the application.

[0030] Figure 2 The figure is a schematic diagram of the turbofan engine inlet temperature simulation temperature field online monitoring method of the application.

[0031] Figure 3 The figure is a schematic diagram of the cross-section finite element division process of the temperature field of the application. DETAILED DESCRIPTION

[0032] In order to make the purpose, technical scheme and advantages of the application clearer, the technical scheme of the application will be described in more detail below with reference to the drawings in the embodiments of the application.

[0033] As shown in the drawings, Figure 1 The application first provides a turbofan engine inlet temperature simulation temperature field online monitoring system, which mainly comprises an engine inlet channel 1, an annular multi-branch point temperature test rake 2, a temperature compensation lead 3, a temperature scanning valve 4, a test run data acquisition server 5, an Ethernet switch 6, a temperature field online monitoring computer 7 and a temperature field online monitoring analysis platform 8.

[0034] When the ground state bench performs the inlet temperature simulation test run, the temperature scanning valve 4 in the test run data acquisition system automatically acquires the temperature sensed by the annular multi-branch point temperature test rake 2 in the engine inlet channel 1 in real time, and stores it in the test run data acquisition system server 5 according to the specified order. The temperature field online monitoring computer 7 receives the engine inlet temperature data acquired by the test run data acquisition system through the Ethernet switch 6, and processes and calculates the current engine inlet average temperature, temperature field unevenness, temperature field circumferential distortion index, temperature field maximum temperature difference and other parameters in real time through the data polynomial fitting according to the following method through the temperature field online monitoring analysis platform installed on the temperature field online monitoring computer 6, and displays the temperature field change through the visual cloud map.

[0035] In addition, as shown in the drawings, Figure 2 The application also provides a turbofan engine inlet temperature simulation temperature field online monitoring method, which comprises the following steps:

[0036] As shown in the drawings, Figure 3 First, the temperature field cross-section 9 of the entire engine inlet channel is developed according to the polar coordinates, divided into m parts along the circumferential direction clockwise, and divided into n equal parts along the radial direction according to the equal annulus, to obtain a grid area 10 of m x n, wherein each grid area is a unit body 11, which represents the weight of the temperature value T i,j (θ, r) of each unit body. The temperature field cross-section has m x n temperature measuring points, which are distributed along the radial direction according to the equal annulus and uniformly distributed along the circumferential direction of 360°. The temperature value T i,j (θ, r) of each unit body is obtained through the polynomial fitting interpolation method during the test run.

[0037] Then, according to the temperature value T i,j (θ, r) of each unit body obtained through the interpolation, the radial average temperature Tr (θ) and the surface average temperature T of the temperature field section 2FAV :

[0038]

[0039]

[0040] wherein, is the relative radius of the hub; is the radial radius at the circumference θ; is the total temperature at the hub in the radial direction.

[0041] The circumferential range θ of the "high temperature zone" is determined according to the distribution of the area-weighted radial average values measured at different radii on the aerodynamic interface along the circumference + The average value T of the airflow temperature in the high temperature zone is calculated according to formula 3 HAV Then, the temperature field uniformity and the temperature distortion strength δT are calculated according to formula 4 and formula 5 2FAV :

[0042]

[0043]

[0044]

[0045] wherein, T0 is the total temperature of the undisturbed airflow in front of the engine.

[0046] The online monitoring system and method provided by the present application can display the uniformity of the temperature field of the engine when the intake air is heated in real time, give the calculation results of the temperature field uniformity, the distortion index, the angular position and range of the high temperature zone, and maximize the visualization and automation of the temperature field, reduce the error of the calculation results, save the labor and time cost, improve the emergency response ability of the test site, and ensure the safety of the engine test.

[0047] The above merely describes specific embodiments of the present application, but the protection scope of the present application is not limited thereto. Any changes or replacements within the technical scope disclosed by the present application can be easily thought of by those skilled in the art, and should be covered within the protection scope of the present application. Therefore, the protection scope of the present application should be subject to the protection scope of the claims.​

Claims

1. A method of on-line monitoring of a temperature field of a simulation of an inlet temperature of a turbofan engine, characterized in that, The method comprises: The temperature field section of the engine air inlet channel is expanded according to polar coordinates, is evenly divided into m parts clockwise along the circumferential direction, and is divided into n equal parts along the radial direction, so as to obtain an m*n grid area, each grid area representing the temperature value of a unit body, and the temperature value of each unit body is obtained , wherein θ is the circumferential angle, and r is the radial radius According to the temperature value of each unit body Obtain the radial average temperature of each angular position And the surface average temperature of the temperature field section , wherein, The relative radius of the hub is, The radial radius at the circumferential θ is, The total temperature at the hub is; The circumferential range of the high temperature zone is determined according to the circumferential distribution of the area-weighted radial average values measured at different radii on the aerodynamic interface The average value of the airflow temperature in the high temperature zone is calculated The average value of the airflow temperature in the high temperature zone is calculated The temperature field non-uniformity and the temperature distortion intensity are calculated and the temperature distortion intensity wherein T0 is the total temperature of the undisturbed airflow in front of the engine At least one of the circumferential range of the high-temperature zone, the average value of the airflow temperature in the high-temperature zone, the temperature field non-uniformity and the temperature distortion intensity is displayed in real time.

2. The method of on-line monitoring of the temperature field of the temperature simulation of the inlet of a turbojet engine according to claim 1, characterized in that, The temperature values of each unit are obtained by polynomial fitting .

3. A turbofan engine inlet temperature simulation temperature field on-line monitoring system, characterized in that, The monitoring system comprises: an engine air inlet, a multi-joint temperature testing rake, a temperature compensation lead, a temperature scanning valve, a test run data acquisition server, an Ethernet switch, an online temperature field monitoring computer and an online temperature field monitoring analysis platform; The temperature scanning valve automatically acquires the temperature sensed by the annular multi-joint temperature testing rake in the engine air inlet in real time and stores the temperature in the test run data acquisition system server. The online temperature field monitoring computer receives the engine air inlet inlet temperature data acquired by the test run data acquisition system through the Ethernet switch and, through the online temperature field monitoring analysis platform installed on the online temperature field monitoring computer, processes and calculates the current engine inlet average temperature, the temperature field non-uniformity, the temperature field circumferential distortion index and the temperature field maximum temperature difference in real time according to the method in any one of claims 1 to 2 and displays the temperature field change through a visual cloud map.

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