Aero-engine component transition state heat exchange boundary analysis method and system
By fitting the cavity temperature change as a function related to time or rotational speed in a piecewise manner, a nonlinear heat transfer analysis model is constructed, which solves the error problem in the calculation of the heat transfer boundary of the transition state of components in the existing technology, and improves the accuracy and reliability of thermodynamic simulation of aero-engine components.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- AECC SICHUAN GAS TURBINE RES INST
- Filing Date
- 2026-02-12
- Publication Date
- 2026-06-12
AI Technical Summary
Existing methods for calculating the transition state heat transfer boundary of aero-engine components typically employ linear interpolation, which leads to temperature field changes that do not match reality, affecting performance, safety, and lifespan assessments.
By collecting experimental data, the cavity temperature change is piecewise fitted as a function related to time or rotation speed. The heat transfer coefficient curve is obtained by interpolation, and a nonlinear heat transfer analysis model is constructed to ensure that the simulation model matches the actual situation.
It significantly improves the accuracy and realism of thermodynamic simulation calculations for engine components, avoids prediction deviations caused by boundary condition distortion, and provides a more accurate basis for thermal load and stress distribution.
Smart Images
Figure CN122197303A_ABST
Abstract
Description
Technical Field
[0001] This invention relates to the field of aero-engine technology, and discloses a method and system for analyzing the heat transfer boundary in the transition state of aero-engine components. Background Technology
[0002] Transition state thermal analysis of components is a crucial step in the development of aero-engines. The accuracy of transition state heat transfer boundary calculation directly determines the engine's performance, safety, lifespan, and cost assessment results. It is the core foundation for accurately predicting component temperature, thermal stress, fatigue life, optimizing cooling, controlling dynamic clearances, and verifying numerical simulations, and is directly related to the engine's structural integrity, reliability, efficiency, and economy.
[0003] When an engine undergoes state transitions during actual operation, the cavity temperature and pressure of the secondary flow system, which determine the heat transfer boundary of components, are not always linearly changing due to factors such as the cavity effect. When performing transition state thermal analysis of components, existing heat transfer boundary calculation methods usually involve linear difference between two states to obtain the heat transfer boundary during the state transition process. This linear difference method for heat transfer boundaries causes the temperature field change process of components to be inconsistent with reality, thereby affecting the assessment of performance, safety, and lifespan. Summary of the Invention
[0004] The purpose of this invention is to provide a method and system for analyzing the transition state heat transfer boundary of aero-engine components, which can improve the accuracy and realism of thermodynamic simulation calculations of engine components and effectively avoid prediction deviations caused by boundary condition distortion.
[0005] To achieve the above-mentioned technical effects, the technical solution adopted by the present invention is as follows:
[0006] A method for analyzing the heat transfer boundary in the transition state of aero-engine components, comprising: Data on the temperature and pressure changes of the chambers related to the components to be analyzed in the aero-engine under test conditions during typical transition states are collected; the boundaries of the chambers include part or all of the surface of the components to be analyzed, and the typical transition states include the process from idle to cruise and back to idle; Plot the cavity temperature change curve over time and divide the change curve into multiple continuous time periods, including the first flat segment of the initial idle steady state, the first transition segment from the initial idle pull-up to the cruise state, the second flat segment of the cruise process, the second transition segment from the cruise pull-down to the idle state, and the third flat segment of the end of the idle steady state. For each time period, the cavity temperature is fitted as a function related to time or rotation speed based on the cavity temperature change data; Based on the cavity temperature and cavity pressure of each straight section, the heat transfer coefficient of the component to be analyzed under the corresponding straight section is obtained by simulation analysis method, and the heat transfer coefficient curve of the component to be analyzed under the transition section between two adjacent straight sections is obtained by interpolation method. The cavity temperature function for each time period and the heat transfer coefficient or heat transfer coefficient curve for the corresponding time period are determined as the heat transfer boundary of the component to be analyzed, and used as input for the heat transfer analysis model to analyze the temperature change curve of the component to be analyzed.
[0007] Furthermore, the dividing point on the change curve is the position where the rate of change of the curve slope is less than a preset threshold.
[0008] Furthermore, the cavity temperature of the first flat segment of the initial idle steady state, the second flat segment of the cruise process, and the third flat segment of the end of the idle steady state is fitted as a linear function of time; the cavity temperature of the first transition segment from the initial idle pull-up to the cruise state is fitted as a nonlinear function related to time or speed, using a quadratic polynomial function or a growth function; the cavity temperature of the second transition segment from the cruise pull-down to the idle state is fitted as a nonlinear function related to time or speed, using a polynomial function or a decay function.
[0009] Furthermore, the first transition phase from initial idle to cruise includes an initial stage where the cavity temperature change rate gradually increases, and a subsequent stage where the cavity temperature asymptotically approaches a first target value; wherein the initial stage is fitted using a quadratic polynomial function, and the cavity temperature in the subsequent stage... The inertial heating function based on time and rotational speed was used for fitting; ,in For the time variable of the first subsequent stage, For the rotational speed variable in the first subsequent stage, , , , For coefficients, , It is a constant.
[0010] Furthermore, the second transition phase from cruise control to idle includes a second initial stage where the cavity temperature change rate gradually increases, and a second subsequent stage where the cavity temperature asymptotically approaches the second target value; wherein the cavity temperature in the second initial stage is linearly fitted, and the cavity temperature in the second subsequent stage... A slow cooling function based on time and rotation speed was used for fitting. ,in For the time variable of the second subsequent stage, For the rotational speed variable in the second subsequent stage, , , , They are coefficients, , They are constants.
[0011] To achieve the above technical effects, the present invention also provides a transition state heat transfer boundary analysis system for aero-engine components, comprising: The data acquisition module is used to collect data on the changes in cavity temperature and cavity pressure of the chamber related to the aero-engine component under test conditions in a typical transition state; the boundary of the chamber includes part or all of the surface of the component under test, and the typical transition state includes the process from idle to cruise and back to idle; The curve segmentation module is used to plot the curve of cavity temperature change over time and divide the curve into multiple continuous time periods. The time periods include the first flat segment of the initial idle steady state, the first transition segment from the initial idle pull-up to the cruise state, the second flat segment of the cruise process, the second transition segment from the cruise pull-down to the idle state, and the third flat segment of the end of the idle steady state. The function model building module is used to fit the cavity temperature into a function related to time or rotation speed based on cavity temperature change data for each time period. The heat transfer coefficient analysis module is used to obtain the heat transfer coefficient of the component under analysis in each straight section based on the cavity temperature and cavity pressure, using simulation analysis methods. It also uses interpolation to obtain the heat transfer coefficient curve of the component under analysis in the transition section between two adjacent straight sections. The cavity temperature function of each time period and the corresponding heat transfer coefficient or heat transfer coefficient curve are determined as the heat transfer boundary of the component under analysis, which is used as the input of the heat transfer analysis model to analyze the temperature change curve of the component under analysis.
[0012] Furthermore, in the curve segmentation module, the segmentation point on the changing curve is the position where the rate of change of the curve slope is less than a preset threshold.
[0013] Furthermore, in the function model construction module, the cavity temperature of the first flat segment of the initial idle steady state, the second flat segment of the cruise process, and the third flat segment of the end of the idle steady state is fitted as a linear function of time; the cavity temperature of the first transition segment from the initial idle to the cruise state is fitted as a nonlinear function related to time or speed, using a quadratic polynomial function or a growth function; the cavity temperature of the second transition segment from the cruise pull-down to the idle state is fitted as a nonlinear function related to time or speed, using a polynomial function or a decay function.
[0014] Furthermore, in the function model construction module, the first transition segment from the initial idle to the cruise state includes a first initial stage where the cavity temperature change rate gradually increases and a first subsequent stage where the cavity temperature asymptotically approaches a first target value; wherein the first initial stage is fitted using a quadratic polynomial function, and the cavity temperature in the first subsequent stage... The inertial heating function based on time and rotational speed was used for fitting; ,in For the time variable of the first subsequent stage, For the rotational speed variable in the first subsequent stage, , , , For coefficients, , It is a constant.
[0015] Furthermore, in the function model construction module, the second transition segment from cruise to idle includes a second initial stage where the cavity temperature change rate gradually increases, and a second subsequent stage where the cavity temperature asymptotically approaches a second target value; wherein the cavity temperature in the second initial stage is linearly fitted, and the cavity temperature in the second subsequent stage... A slow cooling function based on time and rotation speed was used for fitting. ,in For the time variable of the second subsequent stage, For the rotational speed variable in the second subsequent stage, , , , They are coefficients, , They are constants.
[0016] Compared with the prior art, the beneficial effects of this invention are: this invention can ensure that the simulation model of heat transfer boundary analysis of component transition state matches the nonlinear transient characteristics of cavity temperature "first slowly rise and then stabilize" observed by experiments, which significantly improves the accuracy and realism of thermodynamic simulation calculation of engine components, effectively avoids prediction deviation caused by boundary condition distortion, so as to obtain more accurate instantaneous heat load and thermal stress distribution of components, and provide a more reliable temperature field basis for engine durability design and reliability assessment. Attached Figure Description
[0017] Figure 1 This is a flowchart of the transition state heat transfer boundary analysis method for aero-engine components in Example 1 or 2; Figure 2 This is a block diagram of the transition state heat transfer boundary analysis system for aero-engine components in Example 1; Figure 3 This is a schematic diagram of the cavity structure of the component in Example 1 or 2; Figure 4 This is a graph showing the change in cavity temperature over time in Example 2; The module includes: 1. Components to be analyzed; 2. Thermocouples; 3. Data acquisition module; 4. Curve segmentation module; 5. Function model construction module; and 6. Heat transfer coefficient analysis module. Detailed Implementation
[0018] The present invention will now be described in further detail with reference to the embodiments and accompanying drawings. However, this should not be construed as limiting the scope of the above-described subject matter of the present invention to the following embodiments; all technologies implemented based on the content of the present invention fall within the scope of the present invention.
[0019] Example 1 See Figures 1 to 3 A method for analyzing the transition state heat transfer boundary of aero-engine components, comprising: Data on the temperature and pressure changes of the chambers associated with the aero-engine component 1 under test conditions during typical transition states are collected; the boundaries of the chambers include part or all of the surface of the component 1 under analysis, and the typical transition states include the process from idle to cruise and back to idle. Plot the cavity temperature change curve over time and divide the change curve into multiple continuous time periods, including the first flat segment of the initial idle steady state, the first transition segment from the initial idle pull-up to the cruise state, the second flat segment of the cruise process, the second transition segment from the cruise pull-down to the idle state, and the third flat segment of the end of the idle steady state. For each time period, the cavity temperature is fitted as a function related to time or rotation speed based on the cavity temperature change data; Based on the cavity temperature and cavity pressure of each straight section, the heat transfer coefficient of the component 1 to be analyzed under the corresponding straight section is obtained by simulation analysis method, and the heat transfer coefficient curve of the component 1 to be analyzed under the transition section between two adjacent straight sections is obtained by interpolation method. The cavity temperature function for each time period and the heat transfer coefficient or heat transfer coefficient curve for the corresponding time period are determined as the heat transfer boundary of the component to be analyzed 1, and used as input for the heat transfer analysis model to analyze the temperature change curve of the component to be analyzed 1.
[0020] In this embodiment, by segmenting the transient process of the aero-engine and fitting the cavity temperature boundary of each segment as a linear or nonlinear function of time, replacing the traditional fully linear interpolation method, the simulation model of the heat transfer boundary analysis of the component transition state is ensured to match the nonlinear transient characteristics of the cavity temperature "first slowly rises and then stabilizes" observed in the experiment. This significantly improves the accuracy and realism of the thermodynamic simulation calculation of engine components, effectively avoids prediction deviations caused by boundary condition distortion, and further obtains more accurate instantaneous heat load and thermal stress distribution of components, providing a more reliable temperature field basis for the durability design and reliability assessment of the engine.
[0021] Based on the same inventive concept, this embodiment also provides a transition state heat transfer boundary analysis system for aero-engine components, including: The data acquisition module 3 is used to acquire the cavity temperature and cavity pressure change data of the cavity related to the aero-engine component 1 under test conditions in a typical transition state; the boundary of the cavity includes part or all of the surface of the component 1 to be analyzed, and the typical transition state includes the process from idle to cruise and back to idle. The curve segmentation module 4 is used to plot the curve of cavity temperature change over time and divide the curve into multiple continuous time periods. The time periods include the first flat segment of the initial idle steady state, the first transition segment from the initial idle pull-up to the cruise state, the second flat segment of the cruise process, the second transition segment from the cruise pull-down to the idle state, and the third flat segment of the end of the idle steady state. Function model building module 5 is used to fit the cavity temperature into a function related to time or rotation speed based on cavity temperature change data for each time period. The heat transfer coefficient analysis module 6 is used to obtain the heat transfer coefficient of the component 1 to be analyzed under the corresponding straight section based on the cavity temperature and cavity pressure of each straight section using simulation analysis methods, and to obtain the heat transfer coefficient curve of the component 1 to be analyzed under the transition section between two adjacent straight sections using interpolation method; the cavity temperature function of each time period and the heat transfer coefficient or heat transfer coefficient curve of the corresponding time period are determined as the heat transfer boundary of the component 1 to be analyzed, so as to serve as the input of the heat transfer analysis model to perform temperature change curve analysis of the component 1 to be analyzed.
[0022] Example 2 See Figure 1 , Figure 3 and Figure 4 This embodiment takes the transition state heat transfer boundary of a rotor grate disk of a compression component as an example to describe in detail the analysis process of the transition state heat transfer boundary of aero-engine components of the present invention. The analysis process is as follows: Step 1: Collect chamber temperature and pressure change data of the chamber related to the aero-engine component 1 under test conditions in a typical transition state; the boundary of the chamber includes part or all of the surface of the component 1 to be analyzed, and the typical transition state includes the process from idle to cruise and back to idle. In this embodiment, the compressor rotor toothed disc and its heat exchange boundary are as follows: Figure 3 As shown, with Figure 3 The chamber associated with the heat transfer boundary indicated by the dashed line is the analysis chamber. Figure 3 The dotted line in the diagram represents the rotating shaft. By arranging thermocouple 2 in this chamber, the chamber temperature change process of the typical transient state (idle-cruise-idle) load spectrum is recorded according to the aircraft's flight state.
[0023] Step 2: Plot the cavity temperature change curve over time and divide the curve into multiple consecutive time periods. The time periods include the first flat segment of the initial idle steady state, the first transition segment from the initial idle pull-up to the cruise state, the second flat segment of the cruise process, the second transition segment from the cruise pull-down to the idle state, and the third flat segment at the end of the idle steady state. In some other embodiments, the dividing point on the curve is selected at a position where the rate of change of the curve slope is less than a preset threshold.
[0024] This embodiment divides the typical slow-cruise-slow-drive transition process described above into 7 consecutive time periods, such as... Figure 4 As shown, they are 1#, 2#, 3#, 4#, 5#, 6#, and 7#, respectively, where: Time period #1 is the stage where the cavity temperature change rate approaches 0 during the initial slow-speed steady-state process; Time period #2 is the first initial stage during the transition from slow speed to cruise, in which the cavity temperature change rate gradually increases. Time period #3 is the first subsequent stage during the transition from slow speed to cruise, in which the cavity temperature gradually approaches the first target value; Time period #4 is the stage where the cavity temperature change rate approaches 0 during the cruise steady-state process; Time period #5 is the second initial stage during the cruise-slow-speed crossing process, in which the cavity temperature change rate gradually increases. Time period #6 is the second subsequent stage during the transition from cruise to idle state, in which the cavity temperature gradually approaches the second target value; The 7th time period is the stage where the cavity temperature change rate approaches 0 during the end of the slow-speed steady-state process.
[0025] Step 3: For each time period, fit the cavity temperature to a function related to time or rotation speed based on the cavity temperature change data; The cavity temperature change curves for each time period in this embodiment are as follows: Cavity temperature during time period #1 It is a constant. ,in This represents the average chamber temperature during time period #1. Cavity temperature during time period #2 A quadratic polynomial function was used for fitting. ,in For time period #2, , They are coefficients, It is a constant; Cavity temperature during time period #3 The inertial heating function based on time and rotational speed was used for fitting; ,in For time period #3, For time period #3, the rotational speed variable. , , , For coefficients, , It is a constant; Cavity temperature during time period #4 It is a constant. ,in This represents the average chamber temperature during time period #4. Cavity temperature during time period #5 Linear interpolation fitting is used. , For coefficients, It is a constant; Cavity temperature during time period #6 A slow cooling function based on time and rotation speed was used for fitting. ,in For time period #6, , , , They are coefficients, , They are constants; Cavity temperature during time period #7 It is a constant. ,in This represents the average chamber temperature during time period #7.
[0026] Step 4: Based on the cavity temperature and pressure of each straight section, obtain the heat transfer coefficient of the component 1 to be analyzed under the corresponding straight section using simulation analysis method, and obtain the heat transfer coefficient curve of the component 1 to be analyzed under the transition section between two adjacent straight sections using interpolation method; determine the cavity temperature function of each time period and the heat transfer coefficient or heat transfer coefficient curve of the corresponding time period as the heat transfer boundary of the component 1 to be analyzed, so as to use it as the input of the heat transfer analysis model, and perform temperature change curve analysis of the component 1 to be analyzed.
[0027] The above are merely preferred embodiments of the present invention and are not intended to limit the present invention. Any modifications, equivalent substitutions, and improvements made within the spirit and principles of the present invention should be included within the protection scope of the present invention.
Claims
1. A method for analyzing the heat transfer boundary in the transition state of aero-engine components, characterized in that, include: Data on the temperature and pressure changes of the chambers related to the components to be analyzed in the aero-engine under test conditions during typical transition states are collected; the boundaries of the chambers include part or all of the surface of the components to be analyzed, and the typical transition states include the process from idle to cruise and back to idle; Plot the cavity temperature change curve over time and divide the change curve into multiple continuous time periods, including the first flat segment of the initial idle steady state, the first transition segment from the initial idle pull-up to the cruise state, the second flat segment of the cruise process, the second transition segment from the cruise pull-down to the idle state, and the third flat segment of the end of the idle steady state. For each time period, the cavity temperature is fitted as a function related to time or rotation speed based on the cavity temperature change data; Based on the cavity temperature and cavity pressure of each straight section, the heat transfer coefficient of the component to be analyzed under the corresponding straight section is obtained by simulation analysis method, and the heat transfer coefficient curve of the component to be analyzed under the transition section between two adjacent straight sections is obtained by interpolation method. The cavity temperature function for each time period and the heat transfer coefficient or heat transfer coefficient curve for the corresponding time period are determined as the heat transfer boundary of the component to be analyzed, and used as input for the heat transfer analysis model to analyze the temperature change curve of the component to be analyzed.
2. The method for analyzing the transition state heat transfer boundary of aero-engine components according to claim 1, characterized in that, The dividing points on the curve are the positions where the rate of change of the curve slope is less than a preset threshold.
3. The method for analyzing the transition state heat transfer boundary of aero-engine components according to claim 1, characterized in that, The cavity temperature of the first flat segment of the initial idle steady state, the second flat segment of the cruise process, and the third flat segment of the end of the idle steady state is fitted as a linear function of time; the cavity temperature of the first transition segment from the initial idle pull-up to the cruise state is fitted as a nonlinear function related to time or speed, using a quadratic polynomial function or a growth function; the cavity temperature of the second transition segment from the cruise pull-down to the idle state is fitted as a nonlinear function related to time or speed, using a polynomial function or a decay function.
4. The method for analyzing the transition state heat transfer boundary of aero-engine components according to claim 1, characterized in that, The first transition phase from idle to cruise includes an initial stage where the cavity temperature change rate gradually increases, and a subsequent stage where the cavity temperature asymptotically approaches a first target value. The initial stage is fitted using a quadratic polynomial function, and the cavity temperature in the subsequent stage... The inertial heating function based on time and rotational speed was used for fitting; ,in For the time variable of the first subsequent stage, For the rotational speed variable in the first subsequent stage, , , , For coefficients, , It is a constant.
5. The method for analyzing the transition state heat transfer boundary of aero-engine components according to claim 1, characterized in that, The second transition phase from cruise control to idle includes a second initial stage where the cavity temperature change rate gradually increases, and a second subsequent stage where the cavity temperature asymptotically approaches the second target value; wherein the cavity temperature in the second initial stage is linearly fitted, and the cavity temperature in the second subsequent stage... A slow cooling function based on time and rotation speed was used for fitting. ,in For the time variable of the second subsequent stage, For the rotational speed variable in the second subsequent stage, , , , They are coefficients, , They are constants.
6. A transition state heat transfer boundary analysis system for aero-engine components, characterized in that, include: The data acquisition module is used to collect data on the changes in cavity temperature and cavity pressure of the chamber related to the aero-engine component under test conditions in a typical transition state; the boundary of the chamber includes part or all of the surface of the component under test, and the typical transition state includes the process from idle to cruise and back to idle; The curve segmentation module is used to plot the curve of cavity temperature change over time and divide the curve into multiple continuous time periods. The time periods include the first flat segment of the initial idle steady state, the first transition segment from the initial idle pull-up to the cruise state, the second flat segment of the cruise process, the second transition segment from the cruise pull-down to the idle state, and the third flat segment of the end of the idle steady state. The function model building module is used to fit the cavity temperature into a function related to time or rotation speed based on cavity temperature change data for each time period. The heat transfer coefficient analysis module is used to obtain the heat transfer coefficient of the component under analysis in each straight section based on the cavity temperature and cavity pressure, using simulation analysis methods. It also uses interpolation to obtain the heat transfer coefficient curve of the component under analysis in the transition section between two adjacent straight sections. The cavity temperature function of each time period and the corresponding heat transfer coefficient or heat transfer coefficient curve are determined as the heat transfer boundary of the component under analysis, which is used as the input of the heat transfer analysis model to analyze the temperature change curve of the component under analysis.
7. The transition state heat transfer boundary analysis system for aero-engine components according to claim 6, characterized in that, In the curve segmentation module, the segmentation points on the changing curve are the positions where the rate of change of the curve slope is less than a preset threshold.
8. The transition state heat transfer boundary analysis system for aero-engine components according to claim 6, characterized in that, In the function model construction module, the cavity temperature of the first flat segment of the initial idle steady state, the second flat segment of the cruise process, and the third flat segment of the end of the idle steady state is fitted as a linear function of time; the cavity temperature of the first transition segment from the initial idle to the cruise state is fitted as a nonlinear function related to time or speed, using a quadratic polynomial function or a growth function; the cavity temperature of the second transition segment from the cruise pull-down to the idle state is fitted as a nonlinear function related to time or speed, using a polynomial function or a decay function.
9. The transition state heat transfer boundary analysis system for aero-engine components according to claim 6, characterized in that, In the function model construction module, the first transition segment from initial idle to cruise includes a first initial stage where the cavity temperature change rate gradually increases, and a first subsequent stage where the cavity temperature asymptotically approaches a first target value. The first initial stage is fitted using a quadratic polynomial function, and the cavity temperature in the first subsequent stage... The inertial heating function based on time and rotational speed was used for fitting; ,in For the time variable of the first subsequent stage, For the rotational speed variable in the first subsequent stage, , , , For coefficients, , It is a constant.
10. The transition state heat transfer boundary analysis system for aero-engine components according to claim 6, characterized in that, In the function model construction module, the second transition segment from cruise down to idle includes a second initial stage where the cavity temperature change rate gradually increases, and a second subsequent stage where the cavity temperature asymptotically approaches the second target value; wherein the cavity temperature in the second initial stage is linearly fitted, and the cavity temperature in the second subsequent stage... A slow cooling function based on time and rotation speed was used for fitting. ,in For the time variable of the second subsequent stage, For the rotational speed variable in the second subsequent stage, , , , They are coefficients, , They are constants.