CN116822299A - Rapid calculation method for thermal stress of aeroengine flame tube under service load course - Google Patents
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Abstract
The invention discloses a rapid calculation method of thermal stress of a flame tube of an aeroengine under the service load process, which divides the temperature change condition in the flame tube into a plurality of working states according to the rotation speed condition of the engine; dividing the flame tube wall into heating/cooling working conditions according to different overall temperature change trends to obtain temperature change trends of the wall surface of the flame tube under the two working conditions; calculating a temperature-time function according to the temperature-axial distance function and the temperature change trend of two adjacent working states of each wall surface of the flame tube; and (3) integrating the temperature-time function and the axial temperature distribution of the flame tube in the quasi-steady state to obtain a temperature expression, and calculating the transient thermal stress of the flame tube according to the temperature expression. The method can be used for rapidly calculating the transient thermal stress of the flame tube under the service load process, and solves the problem of huge calculation amount of the thermal stress of the flame tube under the service load process calculated by the traditional CFD method.
Description
Technical Field
The invention relates to the technical field of calculation of transient thermal stress of a flame tube of an aero-engine, in particular to a rapid calculation method of thermal stress of the flame tube of the aero-engine under the service load course.
Background
Aeroengines are evolving towards high boost ratios, high turbine inlet temperatures and high thrust-weight ratios, and the cooling technology of the flame tube is also continually improving, and the geometry is more and more complex. Therefore, the problem of temperature field and thermal stress of the flame tube becomes particularly prominent. To prevent the flame tube from being damaged and to improve the service life of the flame tube, accurate temperature field and thermal stress calculation must be performed on the flame tube.
The temperature indicating paint method is the most main technology for testing the structural temperature of the combustion chamber at present, but a certain difficulty exists in obtaining the temperature load of the wall surface of the combustion chamber through experiments. The numerical calculation method can better obtain the global temperature load of the wall surface of the combustion chamber, however, a great amount of calculation resources are required to obtain the accurate temperature load of the wall surface of the combustion chamber.
The assignment method can greatly shorten the calculation time, but the method is only suitable for calculating the quasi-steady-state temperature field and the thermal stress, and cannot be directly suitable for calculating the transient temperature field and the thermal stress.
Disclosure of Invention
In order to solve the problems, the invention provides a rapid calculation method for the thermal stress of an aeroengine flame tube under the service load course.
In order to achieve the above purpose, the present invention is realized by the following technical scheme:
the invention relates to a rapid calculation method of thermal stress of an aeroengine flame tube under service load process, which comprises the following operations:
establishing a finite element model of the flame tube, and carrying out numerical simulation on a quasi-steady-state temperature field of the flame tube;
acquiring a quasi-steady-state temperature field of each wall surface of each working state of the flame tube, and processing the quasi-steady-state temperature field of each wall surface of each working state of the flame tube to obtain a temperature-axial distance function of each wall surface of each working state of the flame tube;
according to the temperature-axial distance function of the flame tube in two adjacent working states of each wall surface, calculating according to the temperature change trend to obtain a temperature-time function, and integrating the axial temperature distribution and the temperature-time function of the flame tube in quasi-steady state in the temperature-axial distance function to obtain a temperature expression of each wall surface of the flame tube in the changing process of the two adjacent working states;
loading all temperature expressions as boundary conditions into a finite element model of the flame tube, setting constraint boundary conditions, and calculating transient temperature fields of the flame tube in the changing process of two adjacent working states in a simulation mode;
and carrying out thermal coupling analysis on the flame tube by utilizing an ANSYS thermal coupling analysis function based on the transient temperature field of the flame tube to obtain transient thermal stress and thermal strain of the flame tube.
The invention further improves that: the method for establishing the finite element model of the flame tube comprises the following specific steps of: and establishing a finite element model of the flame tube in modeling software, keeping the size consistent with that of an experiment or an actual product, dividing hexahedral grids of the flame tube, setting constraint conditions, assigning values to the corresponding flame tube wall surfaces by using the flame tube wall surface temperature measured by the experiment in a steady state, and performing simulation analysis on a quasi-steady state temperature field of the flame tube.
The invention further improves that: the method comprises the steps of obtaining a quasi-steady-state temperature field of each wall surface of each working state of the flame tube, and processing the quasi-steady-state temperature field of each wall surface of each working state of the flame tube to obtain a specific operation of a temperature-axial distance function of the flame tube, wherein the specific operation comprises the following steps: obtaining a quasi-steady-state temperature field of each wall surface of each working state of the flame tube, subtracting the quasi-steady-state temperature field of each wall surface of each working state from a temperature curve of an initial working state of the flame tube to obtain a corresponding change curve, and fitting each obtained change curve to obtain a temperature-axial distance function representing the change of the temperature of each wall surface of each working state along with the change of the axial distance.
The invention further improves that: the specific operation for obtaining the temperature expression of each wall surface of the flame tube in the changing process of two adjacent working states is as follows: and calculating a temperature-time function representing the time-dependent change rule of the temperature of the previous working state to the next working state in the temperature raising stage or the temperature lowering stage according to the two adjacent working states of each wall surface of the flame tube and the temperature change trend of the previous working state to the next working state of the corresponding wall surface by taking the previous working state of each wall surface as a reference, and synthesizing the quasi-steady-state time along the axial temperature distribution of the flame tube in the temperature-time function and the temperature-axial distance function to obtain the temperature expression of each wall surface of the flame tube in the change process of the two adjacent working states.
The invention further improves that: the temperature expression is:
T＝A′(z)*B(time)+C 0 ；
wherein A' (z) is the temperature distribution of the flame tube along the axial direction in the quasi-steady state, B (time) is the temperature-time function, C 0 And z is the axial distance of the wall surface at the temperature of the initial working state.
The invention further improves that: the temperature change trend from the former working state to the latter working state of the wall surface comprises a temperature rising stage or a temperature reducing stage, wherein the temperature rising stage is expressed as:
B′(time)＝1-(time/B 1 -1) 2 ；
the cooling stage is expressed as:
B′(time)＝1-(time/B 2 ) 2 ；
wherein B' (time) is the temperature change trend from the former working state to the latter working state, and time is the specific moment in the process of turning from the former working state to the latter working state, B 1 For duration of the heating-up phase, B 2 Is the duration of the cool down phase;
the temperature-time function of the warm-up phase is expressed as:
B(time)＝C 1 +C 2 *(1-(time/B 1 -1) 2 )；
the temperature-time function of the cool down phase is expressed as:
B(time)＝C 3 -C 4 *(1-(time/B 2 ) 2 )；
wherein C is 1 /C 3 The coefficient of the temperature-axial distance function of the previous working state, C 2 /C 4 A difference between the coefficient of the temperature-axial distance function for the former operating state and the coefficient of the temperature-axial distance function for the latter operating state; b (B) 1 /B 2 For the duration of the warm-up/cool-down phase.
The beneficial effects of the invention are as follows: according to the invention, the temperature expression is used as the first type boundary condition and is applied to the specific area, so that the temperature field in the area is not required to be accurately calculated, and the calculation speed of the temperature field can be obviously accelerated; the numerical simulation of the thermal coupling of the transient process of the flame tube can be realized, and the calculation efficiency of the temperature field is greatly improved, so that the calculation efficiency of the whole thermal stress field is improved. The obtained finite element model can accurately and intuitively reflect the evolution rule of thermal stress and thermal strain of the flame tube along with time, not only provides theoretical basis for researching the deformation mechanism of the flame tube in the transient process, but also can predict dangerous parts by utilizing a temperature field, and finally lays a foundation for establishing a method for finding dangerous points of the flame tube and predicting service life.
Drawings
FIG. 1 is a flow chart of an embodiment of the present invention;
FIG. 2 is a schematic diagram of a flame tube quasi-steady state temperature field in an embodiment of the invention;
FIG. 3 is a schematic diagram of a temperature-axial distance fit curve in an embodiment of the present invention;
FIG. 4 is a schematic view of a transient temperature field of a flame tube in an embodiment of the invention;
FIG. 5 is a schematic view of transient thermal stress of a flame tube in an embodiment of the invention.
Detailed Description
The present invention will be described in further detail with reference to the drawings and examples, in order to make the objects, technical solutions and advantages of the present invention more apparent. It should be understood that the specific embodiments described herein are for purposes of illustration only and are not intended to limit the scope of the invention. In addition, the technical features of the embodiments of the present invention described below may be combined with each other as long as they do not collide with each other.
As shown in FIG. 1, the invention relates to a rapid calculation method for thermal stress of an aeroengine flame tube under service load process, which comprises the following operations:
step 1, establishing a finite element model of the flame tube, and carrying out numerical simulation on a quasi-steady-state temperature field of the flame tube to obtain a quasi-steady-state temperature field of each wall surface of each working state of the flame tube;
step 2, obtaining a quasi-steady-state temperature field of each wall surface of each working state of the flame tube, processing the quasi-steady-state temperature field of each wall surface of each working state of the flame tube to obtain a temperature-axial distance function of the flame tube of each wall surface of each working state, and storing the quasi-steady-state temperature field of each wall surface of each working state of the flame tube and the temperature-axial distance function of the flame tube of each wall surface of each working state into a database;
step 3, calculating according to the temperature-axial distance function of the flame tube in two adjacent working states of each wall surface obtained from the database, obtaining a temperature-time function according to the temperature change trend, and synthesizing the axial temperature distribution and the temperature-time function of the flame tube in the quasi-steady state in the temperature-axial distance function to obtain a temperature expression of each wall surface of the flame tube in the changing process of the two adjacent working states;
step 4, loading all temperature expressions into the finite element model of the flame tube as boundary conditions, setting constraint boundary conditions, and calculating the transient temperature field of the flame tube in a simulation manner; the constraint boundary conditions comprise axial distance constraint of the right end face of the flame tube and constraint of heat insulation surfaces on two sides of the flame tube;
and 5, performing thermal coupling analysis on the flame tube by utilizing an ANSYS thermal coupling analysis function based on the transient temperature field to obtain transient thermal stress and thermal strain of the flame tube.
The specific steps of the step 1 are as follows: and establishing a finite element model of the flame tube in modeling software, wherein the dimension of the finite element model is consistent with that of an experimental or actual product, dividing hexahedral grids of the flame tube, setting axial distance constraint of the right end face of the flame tube, assigning a value to the corresponding flame tube wall surface by using the flame tube wall surface temperature measured by a test in a steady state, and simulating and analyzing a quasi-steady state temperature field of the flame tube.
The specific steps of the step 2 are as follows:
processing the read temperature curves of the working state and the initial working state to obtain a temperature change curve of the flame tube in the process from the initial state to the read working state, fitting the curve to obtain a functional relation between the temperature of the flame tube and the axial distance z in a quasi-steady state under the current condition, namely a temperature-axial distance function:
A(z)＝C*A′(z)
A′(z)＝A 3 *z 3 +A 2 *z 2 +A 1 *z+A 0
wherein A' (z) is the temperature distribution of the flame tube along the axial direction in the quasi-steady state, C is the coefficient of the temperature-axial distance function of the current working state, A i The specific value i obtained from the fitted curve is the highest term index of the axial distance z, and the value of i is determined by the accuracy of the fitted curve, and may be 0 to 3, in this embodiment, i=3. Further, when i=2:
A′(z)＝A 2 *z 2 +A 1 *z+A 0 ；
when i=1:
A′(z)＝A 1 *z+A 0 ；
when i=0:
A′(z)＝A 0 。
the temperature change trend from the former working state to the latter working state of the wall surface comprises a temperature rising stage or a temperature reducing stage, wherein the temperature rising stage is expressed as:
B′(time)＝1-(time/B 1 -1) 2 ；
the cooling stage is expressed as:
B′(time)＝1-(time/B 2 ) 2 ；
wherein B' (time) isThe temperature change trend from the former working state to the latter working state, the time is a specific moment in the process of turning from the former working state to the latter working state, B 1 For duration of the heating-up phase, B 2 Is the duration of the cool down phase;
the temperature-time function of the warm-up phase is expressed as:
B(time)＝C 1 +C 2 *(1-(time/B 1 -1) 2 )；
the temperature-time function of the cool down phase is expressed as:
B(time)＝C 3 -C 4 *(1-(time/B 2 ) 2 )；
wherein C is 1 /C 3 The coefficient of the temperature-axial distance function of the previous working state, C 2 /C 4 A difference between the coefficient of the temperature-axial distance function for the former operating state and the coefficient of the temperature-axial distance function for the latter operating state; b (B) 1 /B 2 For the duration of the warm-up/cool-down phase.
Analyzing the temperature change trend of the flame tube, setting the law of the change of the flame tube along with time, and comprehensively synthesizing the axial temperature distribution and the temperature-time function of the flame tube in a quasi-steady state as a temperature-time function to obtain a temperature expression of the flame tube, wherein the temperature expression is as follows:
T＝A′(z)*B(time)+C 0 wherein A' (z) is the temperature distribution of the flame tube along the axial direction in the quasi-steady state, B (time) is the temperature-time function, C 0 The temperature at the initial operating state, i.e. the temperature at start-up, z is the axial distance.
The whole flame tube in the embodiment is divided into an upper section and a lower section (an outer ring and an inner ring) according to a geometric structure, the outer ring (the inner ring) can be divided into an inner wall (contacted with combustion air flow) and an outer wall (contacted with air), and is axially divided into three sections (a first section, a second section and a third section) in front, middle and back, namely 12 wall surfaces in total, and twelve temperature expressions can be obtained in any two adjacent working state changing processes.
Taking the starting stage as an example, the temperature expression of the first section of the inner wall of the upper section of the flame tube is as follows:
T＝(A 3 *z 3 +A 2 *z 2 +A 1 *z+A 0 )*(C 1 +C 2 *(1-(time/B 1 -1) 2 ))+C 0 wherein B is 1 For the duration of the warming phase.
In this example, taking the wall axial distance z as a variable of the temperature-distance function, taking a certain process of the inner wall of the upper section as an example, the quasi-steady state temperature distribution of the flame tube along the axial direction of the temperature-distance function of the first section, the second section and the third section of the inner wall of the upper section is expressed as:
wherein, the axial distance z of the first section wall surface of the upper section inner wall is more than or equal to 15 and less than 90; the axial distance z of the second section wall surface of the upper section inner wall is more than or equal to 90 and less than 170; the axial distance z of the third section wall surface of the upper section inner wall is more than or equal to 170.
The temperature-time function takes a specific time in the process of turning from a previous working state to a next working state as a variable, and applies different change rules to the flame tube according to the heating/cooling process, wherein the specific time in the process of turning from the previous working state to the next working state is expressed as s, deltaT >0 represents the heating process, deltaT <0 represents the cooling process, and the specific expression is as follows:
all parts of the flame tube in all working states can be provided with temperature expressions according to the method.
It will be understood by those skilled in the art that, unless otherwise defined, all terms (including technical and scientific terms) used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this invention belongs. It will be further understood that terms, such as those defined in commonly used dictionaries, should be interpreted as having a meaning that is consistent with their meaning in the context of the prior art and will not be interpreted in an idealized or overly formal sense unless expressly so defined herein.
While the foregoing is directed to embodiments of the present invention, other and further details of the invention may be had by the present invention, it should be understood that the foregoing description is merely illustrative of the present invention and that no limitations are intended to the scope of the invention, except insofar as modifications, equivalents, improvements or modifications are within the spirit and principles of the invention.
Claims (6)
1. A rapid calculation method for thermal stress of an aeroengine flame tube under service load course is characterized by comprising the following steps: the method comprises the following operations:
establishing a finite element model of the flame tube, and carrying out numerical simulation on a quasi-steady-state temperature field of the flame tube;
acquiring a quasi-steady-state temperature field of each wall surface of each working state of the flame tube, and processing the quasi-steady-state temperature field of each wall surface of each working state of the flame tube to obtain a temperature-axial distance function of each wall surface of each working state of the flame tube;
according to the temperature-axial distance function of the flame tube in two adjacent working states of each wall surface, calculating according to the temperature change trend to obtain a temperature-time function, and integrating the axial temperature distribution and the temperature-time function of the flame tube in quasi-steady state in the temperature-axial distance function to obtain a temperature expression of each wall surface of the flame tube in the changing process of the two adjacent working states;
loading a temperature expression of each wall surface of the flame tube in the two adjacent working state change processes into a flame tube finite element model as a boundary condition, setting constraint boundary conditions, and calculating transient temperature fields of the flame tube in the two adjacent working state change processes in a simulation manner;
and carrying out thermal coupling analysis on the flame tube by utilizing an ANSYS thermal coupling analysis function based on the transient temperature field of the flame tube to obtain transient thermal stress and thermal strain of the flame tube.
2. The method for rapidly calculating the thermal stress of the flame tube of the aeroengine under the service load course according to claim 1, which is characterized in that: the method for establishing the finite element model of the flame tube comprises the following specific steps of: and establishing a finite element model of the flame tube in modeling software, keeping the size consistent with that of an experiment or an actual product, dividing hexahedral grids of the flame tube, setting constraint conditions, assigning values to the corresponding flame tube wall surfaces by using the flame tube wall surface temperature measured by the experiment in a steady state, and performing simulation analysis on a quasi-steady state temperature field of the flame tube.
3. The method for rapidly calculating the thermal stress of the flame tube of the aeroengine under the service load course according to claim 1, which is characterized in that: the method comprises the steps of obtaining a quasi-steady-state temperature field of each wall surface of each working state of the flame tube, and processing the quasi-steady-state temperature field of each wall surface of each working state of the flame tube to obtain a specific operation of a temperature-axial distance function of the flame tube, wherein the specific operation comprises the following steps: obtaining a quasi-steady-state temperature field of each wall surface of each working state of the flame tube, subtracting the quasi-steady-state temperature field of each wall surface of each working state from a temperature curve of an initial working state of the flame tube to obtain a corresponding change curve, and fitting each obtained change curve to obtain a temperature-axial distance function representing the change of the temperature of each wall surface of each working state along with the change of the axial distance.
4. The method for rapidly calculating the thermal stress of the flame tube of the aeroengine under the service load course according to claim 1, which is characterized in that: the specific operation for obtaining the temperature expression of each wall surface of the flame tube in the changing process of two adjacent working states is as follows: and calculating a temperature-time function representing the change rule of the temperature of the previous working state to the next working state in the temperature raising stage or the temperature lowering stage along time according to the temperature-axial distance function of the two adjacent working states of each wall surface of the flame tube and the temperature change trend of the corresponding previous working state to the next working state of the wall surface by taking the previous working state of each wall surface as a reference, and obtaining the temperature expression of each wall surface of the flame tube in the change process of the two adjacent working states by integrating the temperature-time function and the quasi-steady-state temperature distribution of the flame tube in the temperature-axial distance function.
5. The method for rapidly calculating the thermal stress of the flame tube of the aeroengine under the service load course according to claim 4, wherein the method comprises the following steps: the temperature expression is:
T＝A′(z)*B(time)+C 0 ；
wherein A' (z) is the temperature distribution of the flame tube along the axial direction in the quasi-steady state, B (time) is the temperature-time function, C 0 And z is the axial distance of the wall surface at the temperature of the initial working state.
6. The method for rapidly calculating the thermal stress of the flame tube of the aeroengine under the service load course according to claim 5, wherein the method comprises the following steps: the temperature change trend from the former working state to the latter working state of the wall surface comprises a temperature rising stage or a temperature reducing stage, wherein the temperature rising stage is expressed as:
B′(time)＝1-(time/B 1 -1) 2 ；
the cooling stage is expressed as:
B′(time)＝1-(time/B 2 ) 2 ；
wherein B' (time) is the temperature change trend from the former working state to the latter working state, and time is the specific moment in the process of turning from the former working state to the latter working state, B 1 For duration of the heating-up phase, B 2 Is the duration of the cool down phase;
the temperature-time function of the warm-up phase is expressed as:
B(time)＝C 1 +C 2 *(1-(time/B 1 -1) 2 )；
the temperature-time function of the cool down phase is expressed as:
B(time)＝C 3 -C 4 *(1-(time/B 2 ) 2 )；
in the method, in the process of the invention,C 1 /C 3 the coefficient of the temperature-axial distance function of the previous working state, C 2 /C 4 A difference between the coefficient of the temperature-axial distance function for the former operating state and the coefficient of the temperature-axial distance function for the latter operating state; b (B) 1 /B 2 For the duration of the warm-up/cool-down phase.
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| 李彬;吉洪湖;江义军;赵清杰;: "浮动壁火焰筒壁温试验和计算分析", 南京航空航天大学学报, no. 06, pages 771 - 774 * |
| 程明;扈鹏飞;万斌;常峰;: "基于Gambit前处理的气膜冷却火焰筒壁温分析", 航空发动机, no. 02, pages 6 - 9 * |
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