A method and device for evaluating the cooling performance of a hot end component of an aero-engine
By calculating the temperature gradient and high-temperature zone area of hot-end components of aero-engines, the shortcomings of existing cooling performance evaluation technologies have been addressed, enabling accurate prediction of cracks and ablation, and ensuring the safety and lifespan of components.
Patent Information
- Application Number
- CN202310730622.9
- Authority / Receiving Office
- CN · China
- Patent Type
- Patents(China)
- Current Assignee / Owner
- Filing Date
- 2023-06-19
- Publication Date
- 2026-11-06
- Estimated Expiration
- 2043-06-19
AI Technical Summary
Existing technologies are insufficient to accurately evaluate the cooling performance of hot-end components of aero engines, especially in terms of assessment of local temperature gradients, cracks, and ablation, which makes it impossible to accurately predict the lifespan and failure modes of components.
This paper presents a method and apparatus for evaluating the cooling performance of hot-end components of aero-engines by obtaining the mesh temperature of hot-end components through simulation, calculating the temperature gradient and the area of the high-temperature region, and combining the temperature gradient and the area of the high-temperature region to assess the probability of cracks and ablation.
It enables accurate prediction of cracks and ablation in hot-end components, improves the accuracy of cooling performance evaluation, and ensures the safe and stable operation of components.
Smart Images
Figure CN116822182B_ABST
Abstract
Description
Technical Field
[0001] This application belongs to the field of engine design technology, specifically relating to a method and apparatus for evaluating the cooling performance of hot-end components of an aero-engine. Background Technology
[0002] Hot-end components are subjected to enormous heat loads during operation, and their working environment is the most severe among all aero-engine components. The lifespan of hot-end components directly determines the lifespan of the entire engine. Therefore, it is very important to reasonably and accurately evaluate the cooling performance of hot-end components during the design process to ensure their safe and stable operation.
[0003] The main failure modes of hot-end components are cracking and ablation. Existing technical solutions evaluate the cooling performance of hot-end components by calculating the temperature distribution, average wall temperature and maximum wall temperature of the hot-end components.
[0004] The main drawbacks of the existing solution are as follows:
[0005] 1. Cooling evaluation methods based on temperature distribution are difficult to quantitatively evaluate the cooling effect of hot-end components;
[0006] 2. The average wall temperature reflects the overall temperature level of the hot-end component, which is suitable for material selection, but its accuracy in evaluating component cooling performance is insufficient.
[0007] 3. Cracks on hot-end components are caused by large local thermal stress, which in turn is caused by large local temperature gradients. Neither the average temperature nor the maximum temperature data can reflect the local temperature gradient situation.
[0008] 4. The ablation on the hot end component is caused by excessively high temperature in a local area, while the highest temperature is the temperature of a certain point on the hot end component. The temperature of a single point cannot reflect the temperature level of an entire area. Summary of the Invention
[0009] To address the aforementioned issues, this application provides a method and apparatus for evaluating the cooling performance of hot-end components of an aero-engine, which uses temperature gradients to predict component crack generation and high-temperature zone area to predict component ablation.
[0010] The first aspect of this application provides a method for evaluating the cooling performance of hot-end components of an aero-engine, mainly including:
[0011] Step S1: Obtain the temperature of all meshes of the hot-end component through simulation;
[0012] Step S2: Traverse the temperature of all grids to obtain the location of the highest temperature;
[0013] Step S3: Using the location with the highest temperature as the origin, obtain the temperature of all other grids within a radius of 1 inch, and obtain the lowest temperature value from them;
[0014] Step S4: Use the difference between the highest and lowest values as the temperature gradient value at the location of the highest temperature;
[0015] Step S5: Subtract the set value from the highest temperature to form a new highest temperature. Repeat steps S2 to S4 until the calculated temperature gradient value is less than the allowable temperature gradient value.
[0016] Step S6: For the area of the hot end component marked with temperature gradient values, perform crack assessment on the hot end component according to the probability of crack generation in the hot end component corresponding to the magnitude of the temperature gradient value.
[0017] Preferably, step S3 further includes:
[0018] Step S31: Obtain the mesh size 'a' for the hot-end component during simulation;
[0019] Step S32: With radii of 1-0.5a and 1+0.5a respectively, form two concentric spheres with the highest temperature position as the origin. Traverse the grid temperature in the annular region between the two spheres to obtain the lowest temperature value.
[0020] Preferably, in step S5, the set value is 3K.
[0021] Preferably, step S6 further includes:
[0022] Step S7: Traverse the temperature of all grids of the hot end component and determine the area of the region on the hot end component that exceeds the allowable temperature of the material;
[0023] Step S8: Evaluate the ablation range of the hot-end component based on the area of each region of the hot-end component.
[0024] Preferably, in step S7, the areas of each grid that exceeds the allowable temperature of the material are added together to obtain the area of the region.
[0025] The second aspect of this application provides a device for evaluating the cooling performance of hot-end components of an aero-engine, mainly comprising:
[0026] The temperature acquisition module is used to obtain the temperature of all meshes of the hot-end component through simulation.
[0027] The highest temperature acquisition module is used to traverse the temperatures of all grids and obtain the location of the highest temperature;
[0028] The lowest temperature acquisition module is used to acquire the temperature of all other grids within a 1-inch radius, with the highest temperature location as the origin, and then obtain the lowest temperature value from them.
[0029] The temperature gradient acquisition module is used to obtain the temperature gradient value at the location of the highest temperature by using the difference between the highest and lowest values.
[0030] The loop control module is used to subtract the set value from the highest temperature to form a new highest temperature, and then cyclically call the highest temperature acquisition module, the lowest temperature acquisition module, and the temperature gradient acquisition module until the calculated temperature gradient value is less than the allowable temperature gradient value.
[0031] The crack assessment module is used to assess the cracks in the hot-end component by marking the area with temperature gradient values and determining the probability of crack formation in the hot-end component based on the magnitude of the temperature gradient values.
[0032] Preferably, the minimum temperature acquisition module further includes:
[0033] The mesh size acquisition unit is used to acquire the mesh size 'a' of the hot-end component during simulation.
[0034] Concentric circle building elements are used to form two concentric spheres with radii of 1-0.5a and 1+0.5a respectively, and the highest temperature position as the origin. The grid temperature is traversed in the annular region between the two spheres to obtain the lowest temperature value.
[0035] Preferably, the set value is 3K.
[0036] Preferably, the device further includes:
[0037] The high-temperature region acquisition module is used to traverse the temperature of all grids of the hot-end component and determine the area of the region on the hot-end component that exceeds the allowable temperature of the material.
[0038] An ablation assessment module is used to assess the ablation range of the hot-end component based on the area of each region of the hot-end component corresponding to the ablation range of the hot-end component.
[0039] Preferably, the high-temperature region acquisition module includes a summation unit, which is used to add up the areas of each grid that exceeds the allowable temperature of the material to obtain the region area.
[0040] This application can calculate the temperature gradient value and its location of the hot-end component, thereby accurately predicting the location of crack initiation and accurately evaluating the cracking situation of the hot-end component. This application can also calculate the area and location of the region on the hot-end component that exceeds the material's allowable temperature, thereby accurately predicting the location and size of ablation and accurately evaluating the ablation situation of the hot-end component. Attached Figure Description
[0041] Figure 1 This is a flowchart of a preferred embodiment of the method for evaluating the cooling performance of hot-end components of an aero-engine according to this application.
[0042] Figure 2 This is a graph showing the distribution of grid nodes for the computational object.
[0043] Figure 3 This is a grid-filled map of the high-temperature region within area M. Detailed Implementation
[0044] To make the objectives, technical solutions, and advantages of this application clearer, the technical solutions in the embodiments of this application will be described in more detail below with reference to the accompanying drawings. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are only some, not all, of the embodiments of this application. The embodiments described below with reference to the accompanying drawings are exemplary and intended to explain this application, and should not be construed as limiting this application. All other embodiments obtained by those skilled in the art based on the embodiments of this application without creative effort are within the scope of protection of this application. The embodiments of this application will be described in detail below with reference to the accompanying drawings.
[0045] The first aspect of this application provides a method for evaluating the cooling performance of hot-end components of an aero-engine, such as... Figure 1 As shown, it mainly includes:
[0046] Step S1: Obtain the temperature of all meshes of the hot-end component through simulation;
[0047] Step S2: Traverse the temperature of all grids to obtain the location of the highest temperature;
[0048] Step S3: Using the location with the highest temperature as the origin, obtain the temperature of all other grids within a radius of 1 inch, and obtain the lowest temperature value from them;
[0049] Step S4: Use the difference between the highest and lowest values as the temperature gradient value at the location of the highest temperature;
[0050] Step S5: Subtract the set value from the highest temperature to form a new highest temperature. Repeat steps S2 to S4 until the calculated temperature gradient value is less than the allowable temperature gradient value.
[0051] Step S6: For the area of the hot end component marked with temperature gradient values, perform crack assessment on the hot end component according to the probability of crack generation in the hot end component corresponding to the magnitude of the temperature gradient value.
[0052] The temperature gradient *m* represents the maximum temperature difference per inch (*m* = *Tmax* - *Tmin*). Each material has an allowable temperature gradient *n*. Excessive temperature gradients can cause significant thermal stress, leading to cracking. Temperature gradient calculation involves finding the highest and lowest wall temperatures within a one-inch range. Step S2 describes the method for determining the highest temperature: using 3D numerical simulation, select the object to be calculated, such as the inner wall of the flame tube. Develop a program to retrieve the temperatures of all grids on the inner wall surface, finding the highest temperature value *Tmax* and its location (point A, which may exist in multiple locations). See [link to documentation]. Figure 2 Step S3 provides a method for determining the minimum temperature: draw a sphere with a radius of 1 inch, centered at point A, the location of the highest temperature, and determine the minimum temperature of all grids within the sphere.
[0053] It should be noted that, in order to improve the calculation speed, usually only the lowest temperature is extracted from the temperature of all the grids on the sphere. The sphere and the inner wall of the hot end component form an intersection line, and the lowest temperature value on the intersection line is found. However, since the temperature values on the wall are stored at the center of the surface grid, and there is a physical distance (grid size) between the centers of adjacent surface grids, if there is no surface grid center on the intersection line, there will be no data points on the intersection line, and the lowest temperature value cannot be found. Therefore, in some optional embodiments, step S3 further includes:
[0054] Step S31: Obtain the mesh size 'a' for the hot-end component during simulation;
[0055] Step S32: With radii of 1-0.5a and 1+0.5a respectively, form two concentric spheres with the highest temperature location as the origin. Traverse the grid temperature within the annular region between the two spheres to obtain the lowest temperature value. (Refer to the example of a flame tube.) Figure 2 Given that the grid size of the inner wall of the flame tube is a (a is less than 1 inch), with each point A as the center, draw spheres with radii of (1 inch - 0.5a) and (1 inch + 0.5a) respectively. The two spheres form two lines of intersection with the inner wall of the hot end component. Since the flame tube wall has a certain curvature, the distance between the lines of intersection is ≥ a. Therefore, there must be a grid center point in the area between the lines of intersection. Find the lowest temperature Tmin within the inner wall range between the two lines of intersection. Let m1 = Tmax - Tmin. The location of this temperature gradient is the coordinate of each point A (there may be multiple points A).
[0056] Then in step S5, (Tmax-Tdem) is taken as the highest temperature. A global search is performed to find the location B of this temperature (there may be multiple locations). The method for determining the lowest temperature is the same as above. The temperature gradient m2 is calculated. This process is repeated, and the highest temperature is reduced by Tdem in turn. Multiple temperature gradients are calculated until the calculated temperature gradient mi is less than or equal to the allowable temperature gradient n of the material. The calculation then terminates.
[0057] In some alternative implementations, in step S5, the set value Tdem is 3K.
[0058] In some alternative implementations, step S6 is further followed by:
[0059] Step S7: Traverse the temperature of all grids of the hot end component and determine the area of the region on the hot end component that exceeds the allowable temperature of the material;
[0060] Step S8: Evaluate the ablation range of the hot-end component based on the area of each region of the hot-end component.
[0061] In some alternative implementations, in step S7, the areas of each grid that exceeds the allowable temperature of the material are summed to obtain the area of the region.
[0062] The high-temperature zone area refers to the area on a hot-end component that exceeds the material's allowable temperature. Because the shape of the high-temperature zone on a hot-end component is often highly irregular, and the component itself has numerous cooling film pores, geometrically calculating the area is extremely difficult. Figure 3 Taking the three high-temperature zones B, C, and D in region M of the mid-heat end component as an example, this paper illustrates the calculation method for the location and area of the high-temperature zones. Using three-dimensional numerical simulation, a fine-grained mesh is first created. (See...) Figure 3 The program retrieves the temperature on all the wall meshes of the hot-end components, marks the regions within a specific temperature range, thus obtaining three high-temperature regions: B, C, and D. It outputs the mesh coordinates and the area of each mesh within different temperature ranges. Because the surface mesh is a body-fitted mesh, it completely fits the surface of the hot-end components. By summing the areas of all meshes within the same temperature range and integrating the coordinates within the same temperature range, the areas and locations of the three high-temperature regions B, C, and D can be obtained. The ablation status of region M can be evaluated based on the high-temperature areas of regions B, C, and D.
[0063] The second aspect of this application provides a cooling performance evaluation device for hot-end components of an aero-engine, corresponding to the above-described method, mainly comprising:
[0064] The temperature acquisition module is used to obtain the temperature of all meshes of the hot-end component through simulation.
[0065] The highest temperature acquisition module is used to traverse the temperatures of all grids and obtain the location of the highest temperature;
[0066] The lowest temperature acquisition module is used to acquire the temperature of all other grids within a 1-inch radius, with the highest temperature location as the origin, and then obtain the lowest temperature value from them.
[0067] The temperature gradient acquisition module is used to obtain the temperature gradient value at the location of the highest temperature by using the difference between the highest and lowest values.
[0068] The loop control module is used to subtract the set value from the highest temperature to form a new highest temperature, and then cyclically call the highest temperature acquisition module, the lowest temperature acquisition module, and the temperature gradient acquisition module until the calculated temperature gradient value is less than the allowable temperature gradient value.
[0069] The crack assessment module is used to assess the cracks in the hot-end component by marking the area with temperature gradient values and determining the probability of crack formation in the hot-end component based on the magnitude of the temperature gradient values.
[0070] In some alternative implementations, the minimum temperature acquisition module further includes:
[0071] The mesh size acquisition unit is used to acquire the mesh size 'a' of the hot-end component during simulation.
[0072] Concentric circle building elements are used to form two concentric spheres with radii of 1-0.5a and 1+0.5a respectively, and the highest temperature position as the origin. The grid temperature is traversed in the annular region between the two spheres to obtain the lowest temperature value.
[0073] In some alternative implementations, the setting value is 3K.
[0074] In some alternative embodiments, the apparatus further includes:
[0075] The high-temperature region acquisition module is used to traverse the temperature of all grids of the hot-end component and determine the area of the region on the hot-end component that exceeds the allowable temperature of the material.
[0076] An ablation assessment module is used to assess the ablation range of the hot-end component based on the area of each region of the hot-end component corresponding to the ablation range of the hot-end component.
[0077] In some alternative implementations, the high-temperature region acquisition module includes a summation unit for summing the areas of each grid that exceeds the allowable temperature of the material to obtain the region area.
[0078] This application can calculate the temperature gradient value and its location of the hot-end component, thereby accurately predicting the location of crack initiation and accurately evaluating the cracking situation of the hot-end component. This application can also calculate the area and location of the region on the hot-end component that exceeds the material's allowable temperature, thereby accurately predicting the location and size of ablation and accurately evaluating the ablation situation of the hot-end component.
[0079] Although this application has been described in detail above with general descriptions and specific embodiments, some modifications or improvements can be made to it, which will be obvious to those skilled in the art. Therefore, such modifications or improvements made without departing from the spirit of this application are all within the scope of protection claimed in this application.
Claims
1. A method for evaluating the cooling performance of hot-end components of an aero-engine, characterized in that, include: Step S1: Obtain the temperature of all meshes of the hot-end component through simulation; Step S2: Traverse the temperature of all grids to obtain the location of the highest temperature; Step S3: Using the location with the highest temperature as the origin, obtain the temperature of all other grids within a radius of 1 inch, and obtain the lowest temperature value from them; Step S4: Use the difference between the highest and lowest values as the temperature gradient value at the location of the highest temperature; Step S5: Subtract the set value from the highest temperature to form a new highest temperature. Repeat steps S2 to S4 until the calculated temperature gradient value is less than the allowable temperature gradient value. Step S6: For the area of the hot end component marked with temperature gradient values, perform crack assessment on the hot end component according to the probability of crack generation in the hot end component corresponding to the magnitude of the temperature gradient value. Step S3 further includes: Step S31: Obtain the mesh size 'a' for the hot-end component during simulation; Step S32: With radii of 1 inch - 0.5a and 1 inch + 0.5a respectively, form two concentric spheres with the highest temperature position as the origin. Traverse the grid temperature in the annular area between the two spheres to obtain the lowest temperature value. In step S5, the set value is 3K.
2. The method for evaluating the cooling performance of hot-end components of an aero-engine as described in claim 1, characterized in that, Step S6 further includes: Step S7: Traverse the temperature of all grids of the hot end component and determine the area of the region on the hot end component that exceeds the allowable temperature of the material; Step S8: Evaluate the ablation range of the hot-end component based on the area of each region of the hot-end component.
3. The method for evaluating the cooling performance of hot-end components of an aero-engine as described in claim 2, characterized in that, In step S7, the areas of each grid that exceeds the allowable temperature of the material are summed to obtain the area of the region.
4. A device for evaluating the cooling performance of hot-end components of an aero-engine, characterized in that, include: The temperature acquisition module is used to obtain the temperature of all meshes of the hot-end component through simulation. The highest temperature acquisition module is used to traverse the temperatures of all grids and obtain the location of the highest temperature; The lowest temperature acquisition module is used to acquire the temperature of all other grids within a 1-inch radius, with the highest temperature location as the origin, and then obtain the lowest temperature value from them. The temperature gradient acquisition module is used to obtain the temperature gradient value at the location of the highest temperature by using the difference between the highest and lowest values. The loop control module is used to subtract the set value from the highest temperature to form a new highest temperature, and then cyclically call the highest temperature acquisition module, the lowest temperature acquisition module, and the temperature gradient acquisition module until the calculated temperature gradient value is less than the allowable temperature gradient value. The crack assessment module is used to assess the cracks in the hot-end component by marking the area with temperature gradient values and by assessing the probability of crack formation in the hot-end component based on the magnitude of the temperature gradient values. The minimum temperature acquisition module further includes: The mesh size acquisition unit is used to acquire the mesh size 'a' of the hot-end component during simulation. Concentric circle building units are used to form two concentric spheres with radii of 1 inch - 0.5a and 1 inch + 0.5a, respectively, with the highest temperature position as the origin. The grid temperature is traversed in the annular region between the two spheres to obtain the lowest temperature value. The set value is 3K.
5. The cooling performance evaluation device for hot-end components of an aero-engine as described in claim 4, characterized in that, The device further includes: The high-temperature region acquisition module is used to traverse the temperature of all grids of the hot-end component and determine the area of the region on the hot-end component that exceeds the allowable temperature of the material. An ablation assessment module is used to assess the ablation range of the hot-end component based on the area of each region of the hot-end component corresponding to the ablation range of the hot-end component.
6. The cooling performance evaluation device for hot-end components of an aero-engine as described in claim 5, characterized in that, The high-temperature region acquisition module includes a summation unit, which is used to add up the areas of each grid that exceeds the allowable temperature of the material to obtain the region area.