Method and device for designing and loading crack propagation simulation part of typical stator part at hot end of aero-engine

Abstract

The invention discloses a method and a device for designing and loading a crack propagation simulation part of a typical stator part at a hot end of an aero-engine, and belongs to the technical field of aerospace engines. According to the method, alternation of a thermal load is simulated through alternation of a mechanical load, a load spectrum is obtained by performing static strength analysis on a simulation piece at the highest working temperature, the mechanical load is applied by synchronizing the thermal cycle period of a real structure in the test process through the load spectrum, and the mechanical behavior of the turbine guide vane under the complex load condition is reflected. According to the invention, conventional force loading is replaced by displacement loading, so that the problem of thermal mechanical coupling effect simulation distortion in the design of a typical hot-end stator part simulation part of an aero-engine is solved; a crack closing effect is considered, a stress intensity factor during crack opening is introduced and compared with a conventional stress intensity factor amplitude, an effective stress intensity factor range is comprehensively considered and determined, and the problem that a conventional crack propagation model cannot accurately reflect specific thermodynamic coupling characteristics of a typical hot-end stator part is solved.

Description

Technical Field

[0001] The present invention belongs to the technical field of aerospace engines, and in particular relates to a design and loading method and device for a crack propagation simulation component of a typical stator component at the hot end of an aerospace engine. Background Art

[0002] Among the high-temperature components of aircraft engines, typical hot-end stators such as turbine guide vanes and combustion chamber flame liner have failure behaviors that are significantly different from those of conventional stators (such as compressor guide vanes) and rotors (turbine moving blades) due to the extreme service conditions and unique load mechanisms. The load conditions of typical hot-end stators such as turbine guide vanes and combustion chamber flame liner are significantly different from those of conventional stators or rotors. Typical hot-end stators such as turbine guide vanes and combustion chamber flame liner are subject to the asymmetry of thermal-solid loads and the influence of high temperature on material properties. In addition, due to the phase mismatch of thermal-solid loads, the amplitude and stress ratio of the stress field show dynamic changes, that is, the stress ratio in the crack propagation stage is significantly different from that in the conventional stators or rotors. Unclear, stress ratio The unconventional characteristics of the hot end stator significantly affect the fatigue life prediction of the hot end stator structure, and further affect the damage tolerance design of the hot end stator structure.

[0003] The study of crack growth behavior driven primarily by thermal stress is crucial for the design of structural simulations for typical hot-end stator components. For example, turbine guide vanes, as critical components of aircraft engines, present significant challenges in design and life assessment due to their structural complexity and diverse load environments. Conventional crack growth simulations cannot fully reflect the crack growth patterns of real structures.

[0004] With the continuous development of structural strength design technology, some preliminary results have been achieved in the field of aircraft engine simulation component design, but the following problems still exist: (1) Focusing on conventional force loading, it is unable to truly reflect the deformation and stress distribution of typical hot end stator components under actual working conditions, which will lead to distortion of the simulation of thermomechanical coupling effects. (2) Only the amplitude of the stress intensity factor under conventional tensile load is considered. The effect of the stress intensity factor (difference between the maximum and minimum values of the crack tip stress intensity factor) on the crack growth rate is shown in the figure below: Using the crack closure effect of a typical hot-end stator component as the driving force for fatigue crack growth as a measure of crack growth rate under fatigue loading ignores the impact of crack closure on crack growth in typical hot-end stators. This crack closure effect reduces crack growth rate, causing predictions to deviate from the actual crack growth behavior of aeroengine hot-end components under complex thermodynamic cycles, making it unsuitable for simulation design of typical hot-end stators in aeroengines. Existing stator crack design methods fail to fully reflect the unique thermodynamic coupling characteristics of aeroengine high-temperature components. Summary of the Invention

[0005] In order to solve the above technical problems, the present invention adopts the following technical solutions:

[0006] A design and loading method for a crack propagation simulation component of a typical stator component at the hot end of an aircraft engine, comprising:

[0007] Step 1: Obtain the geometric model, material performance parameters, typical operating conditions and failure modes of the turbine guide vane, obtain the magnitude and direction of the first principal stress of the turbine guide vane structure at different temperatures, determine the dangerous parts, and select the initial crack plane;

[0008] Step 2: Determine the key geometric dimensions that have a major impact on the stress intensity factor on the crack propagation path, and preliminarily determine the geometric shape and size of the crack propagation simulation component based on the determined key geometric dimensions;

[0009] Step 3: Preliminarily design the geometry of the crack propagation simulation component based on the key geometric dimensions obtained in Step 2. Then, perform a static strength analysis on the crack propagation simulation component with reference to the actual operating conditions of the turbine guide vane. Set the loading mode to displacement loading, and adjust the eccentricity of the crack propagation simulation component so that the first principal stress distribution of the crack propagation simulation component in the crack-free state is consistent with that of the actual structure.

[0010] Step 4: Using crack growth analysis software, insert an initial crack on the first principal stress plane of the dangerous part of the crack growth simulation component. Adjust the loading displacement as the crack length changes to obtain the relationship between the displacement loading size and the crack length, so that the stress intensity factor at different crack lengths is consistent with the actual structure.

[0011] Step 5: Using the variable displacement loading method, the crack extension simulation is used to reflect the deformation and stress distribution of the turbine guide blade under the actual working conditions. The stress intensity factor calculation model considering the crack closure effect is introduced. The stress intensity factor when the crack is open is used to calculate the stress intensity factor of the turbine guide blade under the actual working conditions. Quantify the crack closure effect, correct the load that actually drives crack growth, and comprehensively consider and quantify the change law of the stress intensity factor of a typical hot end stator during the heating and cooling process.

[0012] A design and loading device for a crack propagation simulation component of a typical stator component at the hot end of an aircraft engine, comprising:

[0013] The model and parameter acquisition module obtains the geometric model, material performance parameters, typical operating conditions and failure modes of the turbine guide vanes, obtains the magnitude and direction of the first principal stress of the turbine guide vane structure at different temperatures, identifies the dangerous parts, and selects the initial crack plane;

[0014] The simulation component determination module determines the key geometric dimensions that have a major impact on the stress intensity factor on the crack propagation path, and preliminarily determines the geometric shape and size of the crack propagation simulation component based on the determined key geometric dimensions;

[0015] The design module preliminarily designs the geometry of the crack propagation simulation component based on the key geometric dimensions obtained by the simulation component determination module. Subsequently, a static strength analysis of the crack propagation simulation component is performed with reference to the actual operating conditions of the turbine guide vanes. The loading method is set to displacement loading, and the eccentricity of the crack propagation simulation component is adjusted to ensure that the first principal stress distribution of the crack propagation simulation component in the crack-free state is consistent with that of the actual structure.

[0016] The adjustment module uses crack growth analysis software to insert an initial crack on the first principal stress plane of the dangerous part of the crack growth simulation component. The loading displacement is adjusted as the crack length changes to obtain the relationship between the displacement loading size and the crack length, so that the stress intensity factor at different crack lengths is consistent with the real structure.

[0017] The crack propagation model under the crack closure effect is considered. The variable amplitude displacement loading method is used to reflect the deformation and stress distribution of the turbine guide blade under the actual working condition through the crack propagation simulation. The stress intensity factor calculation model considering the crack closure effect is introduced. The stress intensity factor when the crack is open is used to calculate the stress intensity factor of the turbine guide blade under the actual working condition. Quantify the crack closure effect, correct the load that actually drives crack growth, and comprehensively consider and quantify the change law of the stress intensity factor of a typical hot end stator during the heating and cooling process.

[0018] An electronic device comprises a memory, a processor and a computer program stored in the memory and executable on the processor. When the processor executes the program, the steps of the design and loading method of a crack propagation simulation component of a typical static component of an aircraft engine hot end are realized.

[0019] A non-transitory computer-readable storage medium stores a computer program, which, when executed by a processor, implements the steps of the design and loading method of a crack propagation simulation component for a typical stator component at the hot end of an aero-engine.

[0020] The present invention has the following beneficial effects:

[0021] The present invention replaces conventional force loading with displacement loading, solving the problem of simulation distortion of thermomechanical coupling effect in the design of typical hot end stator simulation parts of aircraft engines. The present invention considers the crack closure effect and introduces the stress intensity factor when the crack opens. , and the conventional stress intensity factor amplitude For comparison, the effective stress intensity factor range was determined by comprehensive consideration , which solves the problem that conventional crack propagation models cannot accurately reflect the unique thermodynamic coupling characteristics of typical hot-end stators. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] Figure 1 This is a flow chart of the design and loading method of a crack propagation simulation component for a typical stator component of an aircraft engine hot end according to the present invention;

[0023] Figure 2 Schematic diagram of variable amplitude displacement loading method for crack extension simulation component;

[0024] Figure 3 This is a schematic diagram of the appearance of the crack extension simulation component;

[0025] Figure 4 This is a diagram showing the variation of stress intensity factor of the real structure and crack extension simulation component with crack extension under variable amplitude displacement loading. DETAILED DESCRIPTION

[0026] In order to make the objectives, technical solutions and advantages of the present invention more clearly understood, the present invention is further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are only intended to illustrate the present invention and are not intended to limit the present invention. In addition, the technical features involved in the various embodiments of the present invention described below may be combined with each other as long as they do not conflict with each other.

[0027] The following further describes the design and loading method of the crack propagation simulation component of a typical stator component of an aircraft engine hot end in conjunction with the accompanying drawings. Figure 1 As shown, the present invention specifically includes the following steps:

[0028] Step 1: Obtain the geometric model, material performance parameters, typical operating conditions and failure modes of the turbine guide vane. Based on the thermal-solid coupling load characteristics of the turbine guide vane, conduct real structural static strength analysis at different operating temperatures of the turbine guide vane, obtain the magnitude and direction of the first principal stress of the turbine guide vane structure at different temperatures, determine the location with the maximum first principal stress as the dangerous location, and select the plane perpendicular to the first principal stress as the initial crack plane.

[0029] Step 2: Use crack propagation analysis software to set initial cracks at dangerous locations, give the crack propagation model parameters of the given material, extract the change law of the stress intensity factor on the crack propagation path, determine the key geometric dimensions that have a major impact on the stress intensity factor on the crack propagation path, and preliminarily determine the geometric shape and size of the simulation part based on the determined key geometric dimensions.

[0030] In step 3, the geometry of the crack propagation simulation component is preliminarily designed based on the key geometric dimensions obtained in step 2. Next, a static strength analysis is performed on the crack propagation simulation component, referring to the actual operating conditions of the turbine guide vane. The loading method is set to displacement loading, and the eccentricity of the crack propagation simulation component is adjusted to ensure that the first principal stress distribution of the crack propagation simulation component in the crack-free state is consistent with that of the actual structure.

[0031] like Figure 3 As shown in the figure, in order to ensure that the key geometric dimensions remain unchanged and better simulate the actual loading conditions of the turbine guide vane tension-bending coupling, the crack propagation simulation part is designed to be an I-shaped uniaxial eccentric tensile part, and the supporting section is a pin hole.

[0032] Step 4: Using crack propagation analysis software, insert an initial crack in the first principal stress plane of the dangerous part of the crack propagation simulation component. Adjust the loading displacement as the crack length changes to obtain the law between the displacement loading size and the crack length, so that the stress intensity factor under different crack lengths is consistent with the real structure.

[0033] Step 5: Using the variable displacement loading method, the crack extension simulation is used to reflect the deformation and stress distribution of the turbine guide blade under the actual working conditions. The stress intensity factor calculation model considering the crack closure effect is introduced. The stress intensity factor when the crack is open is used to calculate the stress intensity factor of the turbine guide blade under the actual working conditions. To quantify the crack closure effect, correct the load that actually drives crack propagation, and comprehensively consider and quantify the change law of the stress intensity factor of a typical hot end stator during the heating and cooling process, the introduced model is:

[0034] ;

[0035] in, is the effective stress intensity factor range, is the stress intensity factor when the crack opens, is the maximum value of the stress intensity factor at the crack tip, is the minimum value of the stress intensity factor at the crack tip, = .

[0036] In step 1, the material performance parameters include the material's density, elastic modulus, Poisson's ratio, linear expansion coefficient, and thermal conductivity.

[0037] In step 2, the key geometric dimensions include the geometric dimensions and geometric shape of the turbine guide vane edge plate. The transition angle radius of the upper and lower edge plates must be consistent with the actual component. At the same time, according to the engineering detectable crack length standard, the linear crack length is 0.76mm and the corner crack length is 0.38mm.

[0038] The specific steps of step 3 include: adjusting the size of the displacement load applied to the simulation part so that the first principal stress distribution of the simulation part is consistent with the real structure, and by adjusting the eccentricity of the simulation part, the first principal stress gradient of the simulation part can be controlled to be consistent with the real component.

[0039] Step 5 specifically includes: at the highest operating temperature of the turbine guide vane, during the load loading process, using a variable amplitude displacement loading method (such as Figure 2 As shown in the figure), mechanical load is used instead of thermal load, which greatly reduces the test cycle and cost. For conventional hot end stators, the calculation model of stress intensity factor needs to consider the crack closure effect. However, under the coupling effect of crack closure effect and displacement boundary conditions, the stress intensity factor may be negative, so the Quantify the crack closure effect, correct the load that actually drives crack growth, and comprehensively consider and quantify the change law of the stress intensity factor of a typical hot end stator during the heating and cooling process. Figure 4 This is a diagram showing the variation of stress intensity factor of the real structure and crack extension simulation component with crack extension under variable amplitude displacement loading.

[0040] Those skilled in the art will appreciate that embodiments of the present invention may be provided as methods, systems, or computer program products. Thus, the present invention may take the form of an entirely hardware embodiment, an entirely software embodiment, or an embodiment combining software and hardware aspects. Furthermore, the present invention may take the form of a computer program product implemented on one or more computer-usable storage media (including but not limited to disk drives, CD-ROMs, optical storage devices, etc.) containing computer-usable program code. The solutions in the embodiments of the present invention may be implemented using various computer languages, such as the object-oriented programming language Java and the interpreted scripting language JavaScript.

[0041] The present invention is described with reference to flowcharts and / or block diagrams of methods, devices (systems), and computer program products according to embodiments of the present invention. It should be understood that each process and / or block in the flowcharts and / or block diagrams, as well as combinations of processes and / or blocks in the flowcharts and / or block diagrams, can be implemented by computer program instructions. These computer program instructions can be provided to a processor of a general-purpose computer, a special-purpose computer, an embedded processor, or other programmable data processing device to produce a machine, so that the instructions executed by the processor of the computer or other programmable data processing device generate instructions for implementing the processes in the flowcharts and / or block diagrams. Figure 1 a process or multiple processes and / or boxes Figure 1 A device that provides the functions specified in a block or multiple blocks.

[0042] These computer program instructions may also be stored in a computer readable memory that can direct a computer or other programmable data processing device to work in a specific manner, so that the instructions stored in the computer readable memory produce an article of manufacture comprising an instruction device, which implements the process Figure 1 a process or multiple processes and / or boxes Figure 1 The function specified in one or more boxes.

[0043] These computer program instructions can also be loaded onto a computer or other programmable data processing device so that a series of operational steps are executed on the computer or other programmable device to produce a computer-implemented process, thereby providing the instructions executed on the computer or other programmable device for implementing the process. Figure 1 a process or multiple processes and / or boxes Figure 1 A step that specifies a function in one or more boxes.

[0044] Although the preferred embodiments of the present invention have been described, those skilled in the art may make additional changes and modifications to these embodiments once they have learned the basic creative concept. Therefore, the appended claims are intended to be interpreted as including the preferred embodiments and all changes and modifications that fall within the scope of the present invention.

[0045] Obviously, those skilled in the art may make various changes and modifications to the present invention without departing from the spirit and scope of the present invention. Thus, if such changes and modifications fall within the scope of the claims and their equivalents, the present invention is intended to include such changes and modifications.

[0046] The above descriptions are merely embodiments of the present invention and are not intended to limit the scope of the present invention. Any equivalent structure or equivalent process transformation made using the contents of the present invention description and drawings, or directly or indirectly applied to other related system fields, are also included in the scope of protection of the present invention.

[0047] The contents not described in detail in the specification of the present invention belong to the prior art known to those skilled in the art.

Claims

1. A design and loading method for a crack propagation simulation component of a typical stator component at the hot end of an aircraft engine, characterized in that: include: Step 1: Obtain the geometric model, material performance parameters, typical operating conditions and failure modes of the turbine guide vane, obtain the magnitude and direction of the first principal stress of the turbine guide vane structure at different temperatures, determine the dangerous parts, and select the initial crack plane; Step 2: Determine the key geometric dimensions that have a major impact on the stress intensity factor on the crack propagation path, and preliminarily determine the geometric shape and size of the crack propagation simulation component based on the determined key geometric dimensions; Step 3: Preliminarily design the geometry of the crack propagation simulation component based on the key geometric dimensions obtained in Step 2. Then, perform a static strength analysis on the crack propagation simulation component with reference to the actual operating conditions of the turbine guide vane. Set the loading mode to displacement loading, and adjust the eccentricity of the crack propagation simulation component so that the first principal stress distribution of the crack propagation simulation component in the crack-free state is consistent with that of the actual structure. Step 4: Using crack growth analysis software, insert an initial crack on the first principal stress plane of the dangerous part of the crack growth simulation component. Adjust the loading displacement as the crack length changes to obtain the relationship between the displacement loading size and the crack length, so that the stress intensity factor at different crack lengths is consistent with the actual structure. Step 5: Using the variable displacement loading method, the crack extension simulation is used to reflect the deformation and stress distribution of the turbine guide blade under the actual working conditions. The stress intensity factor calculation model considering the crack closure effect is introduced. The stress intensity factor when the crack is open is used to calculate the stress intensity factor of the turbine guide blade under the actual working conditions. Quantify the crack closure effect, correct the load that actually drives crack growth, and comprehensively consider and quantify the change law of the stress intensity factor of a typical hot end stator during the heating and cooling process.

2. The design and loading method of a crack propagation simulation component for a typical stator component at the hot end of an aircraft engine according to claim 1 is characterized in that: In step 1, the material performance parameters include the material's density, elastic modulus, Poisson's ratio, linear expansion coefficient, and thermal conductivity.

3. The design and loading method of a crack propagation simulation component for a typical stator component at the hot end of an aircraft engine according to claim 1, characterized in that: In step 1, based on the thermal-solid coupling load characteristics of the turbine guide vane, a real structural static strength analysis is carried out at different operating temperatures of the turbine guide vane to obtain the magnitude and direction of the first principal stress of the turbine guide vane structure at different temperatures, determine the location of the maximum first principal stress as the dangerous location, and select the plane perpendicular to the first principal stress as the initial crack plane.

4. The design and loading method of a crack propagation simulation component for a typical stator component at the hot end of an aircraft engine according to claim 1, characterized in that: In step 2, crack propagation analysis software is used to set initial cracks at dangerous locations. The crack propagation model parameters of the given material are used to extract the variation law of the stress intensity factor on the crack propagation path, and determine the key geometric dimensions that have a major impact on the stress intensity factor on the crack propagation path.

5. The design and loading method of a crack propagation simulation component for a typical stator component at the hot end of an aircraft engine according to claim 1, characterized in that: In step 2, the key geometric dimensions include the geometric dimensions and geometric shape of the turbine guide vane edge plate. The transition angle radius of the upper and lower edge plates must be consistent with the actual component. At the same time, according to the engineering detectable crack length standard, the linear crack length is 0.76mm and the corner crack length is 0.38mm.

6. The design and loading method of a crack propagation simulation component for a typical stator component at the hot end of an aircraft engine according to claim 1, characterized in that: In step 3, the geometric shape of the crack propagation simulation part is designed to be an I-shaped uniaxial eccentric tensile part, and the supporting section is a pin hole.

7. The design and loading method of a crack propagation simulation component for a typical stator component at the hot end of an aircraft engine according to claim 1, characterized in that: Step 3 includes: adjusting the size of the displacement load applied to the simulation part so that the first principal stress distribution of the simulation part is consistent with the real structure, and by adjusting the eccentricity of the simulation part, the first principal stress gradient of the simulation part can be controlled to be consistent with the real component.

8. The design and loading method of a crack propagation simulation component for a typical stator component at the hot end of an aircraft engine according to claim 1, characterized in that: In step 5, the model introduced is: ； in, is the effective stress intensity factor range, is the stress intensity factor when the crack opens, is the maximum value of the stress intensity factor at the crack tip, is the minimum value of the stress intensity factor at the crack tip, = .

9. A design and loading device for a crack propagation simulation component of a typical stator component at the hot end of an aircraft engine, characterized in that: include: The model and parameter acquisition module obtains the geometric model, material performance parameters, typical operating conditions and failure modes of the turbine guide vanes, obtains the magnitude and direction of the first principal stress of the turbine guide vane structure at different temperatures, identifies the dangerous parts, and selects the initial crack plane; The simulation component determination module determines the key geometric dimensions that have a major impact on the stress intensity factor on the crack propagation path, and preliminarily determines the geometric shape and size of the crack propagation simulation component based on the determined key geometric dimensions; The design module preliminarily designs the geometry of the crack propagation simulation component based on the key geometric dimensions obtained by the simulation component determination module. Subsequently, a static strength analysis of the crack propagation simulation component is performed with reference to the actual operating conditions of the turbine guide vanes. The loading method is set to displacement loading, and the eccentricity of the crack propagation simulation component is adjusted to ensure that the first principal stress distribution of the crack propagation simulation component in the crack-free state is consistent with that of the actual structure. The adjustment module uses crack growth analysis software to insert an initial crack on the first principal stress plane of the dangerous part of the crack growth simulation component. The loading displacement is adjusted as the crack length changes to obtain the relationship between the displacement loading size and the crack length, so that the stress intensity factor at different crack lengths is consistent with the real structure. The crack propagation model under the crack closure effect is considered. The variable amplitude displacement loading method is used to reflect the deformation and stress distribution of the turbine guide blade under the actual working condition through the crack propagation simulation. The stress intensity factor calculation model considering the crack closure effect is introduced. The stress intensity factor when the crack is open is used to calculate the stress intensity factor of the turbine guide blade under the actual working condition. Quantify the crack closure effect, correct the load that actually drives crack growth, and comprehensively consider and quantify the change law of the stress intensity factor of a typical hot end stator during the heating and cooling process.

10. An electronic device comprising a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein: When the processor executes the program, the steps of the method for designing and loading a crack propagation simulation component of a typical stator component of an aircraft engine hot end according to any one of claims 1 to 8 are implemented.

11. A non-transitory computer-readable storage medium having a computer program stored thereon, characterized in that: When the computer program is executed by a processor, the steps of the method for designing and loading a crack propagation simulation component of a typical stator component of an aircraft engine hot end as described in any one of claims 1 to 8 are implemented.

Images