CN115636090A - Method for predicting bearing capacity of casing, casing and aviation gas turbine engine - Google Patents
Method for predicting bearing capacity of casing, casing and aviation gas turbine engine Download PDFInfo
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Abstract
The invention provides a method for predicting the bearing capacity of a cartridge receiver, the cartridge receiver and an aviation gas turbine engine, wherein the prediction method comprises the following steps: after considering material nonlinearity and geometric nonlinearity, performing stress analysis on the case under the combined action of complex working loads by using an elastic-plastic finite element method, and when the load increases to reach a critical load, losing the capability of continuously bearing a certain bearing section of the case, wherein the critical load is the ultimate bearing capability of the case. By adopting the prediction method, the defect that the design process of the casing is thick and heavy due to the existing prediction method is overcome, and the prediction method can be used for accurately predicting and evaluating the bearing capacity of the casing with the advanced and complex structure made of metal materials, and further carrying out the work of weight optimization and the like.
Description
Technical Field
The invention belongs to the technical field of prediction of the bearing capacity of a cartridge receiver, and particularly relates to a prediction method of the bearing capacity of the cartridge receiver, the cartridge receiver and an aviation gas turbine engine.
Background
The existing method for evaluating the bearing capacity of the metallic aeroengine casing mainly adopts a conventional method or a finite element technologyObtaining maximum equivalent stress sigma of key part of casing under various load effects max Considering a certain reserve coefficient k, the tensile properties of the metal material, such as yield limit sigma 0.2 And intensity limit σ b And comparing to obtain a safety coefficient, and specifically adopting the following formula:
yield safety factor
Safety factor of damage
The cartridge load capacity evaluation method considers that: under various load effects, after considering the influence of processes such as casting, welding and the like on the tensile property of the casing material, the maximum equivalent stress of any local point in the metal casing structure is multiplied by the reserve coefficient k to exceed the material yield limit sigma 0.2 When the load continues to increase, the maximum equivalent stress of any local point in the metal material casing structure multiplied by the reserve coefficient k exceeds the material strength limit sigma b In time, the structure will break and no longer have the ability to continue bearing.
The existing method for evaluating the bearing capacity of the metal aeroengine casing considers that: when the maximum equivalent stress of any local point in the metal material casing structure is multiplied by the reserve coefficient k, the maximum equivalent stress exceeds the material strength limit sigma b When the pressure vessel is used, the structure is damaged, the continuous bearing capacity is not provided, the method can accurately predict and evaluate the bearing capacity of the pressure vessel for the cylindrical pressure vessel which has a simple structure, a single load and an unobvious stress concentration in a main bearing area, but along with the improvement of the function diversification and the structure integration requirements of the casing of the advanced aeroengine, the structure and the bearing capacity of the casing are more complex, various structures such as bolt holes, mounting seats and the like for assembly are frequently existed, and the inevitable obvious stress concentration phenomenon caused by geometrical mutation such as round holes, rounding and the like in a key area, such as a high stress area shown in figure 2, at the moment, even if the maximum equivalent stress of a local point exceeds the maximum equivalent stress of a material, the method can be used for predicting and evaluating the bearing capacity of the pressure vesselStrength limit σ b However, since the structure enters the yielding position in advance, stress redistribution occurs due to plastic flow, most of the adjacent part is not destroyed and even is in a linear elastic stage, and other areas of the main bearing section of the whole casing structure can continue to bear, so that the metal casing can not actually exceed the material strength limit sigma by the maximum equivalent stress of any one local point b The bearing capacity of the aero-engine case made of metal materials with complex structure and load is predicted and evaluated by the existing method, so that the engineering application requirements can be met, but the case is thicker due to higher margin, so that the weight of parts and the whole machine is influenced, and certain defects exist.
The bearing capacity of a metal material casing of an aero-engine is evaluated by the existing method, the schematic diagram of the local structure of the casing is shown in figure 1, the distribution of equivalent stress under the action of working load is shown in figure 2, the yield safety coefficient obtained by calculation is 1.23, the damage safety coefficient is 1.06, the static test result shows that the metal material casing is not damaged under the action of given load, and the bearing capacity evaluation by the existing method can basically meet the requirements of engineering application.
However, because the structure shape of the aircraft engine casing is complex, there are geometric sudden-change stress concentration structures such as a plurality of rounded circles and round holes formed by casting and machining, and the loads which the aircraft engine casing may bear include abnormal loads such as pneumatic load, inner cavity pressure load, temperature load, aircraft dynamic load, connecting piece load and blade loss. The invention provides a prediction method which can be used for accurately predicting and evaluating the bearing capacity of a metal material casing with an advanced complex structure so as to carry out weight optimization and other work.
Disclosure of Invention
Aiming at the problems, the invention provides a method for predicting the bearing capacity of a casing, which overcomes the defect that the existing prediction method causes thick and heavy design process of the casing, and can be used for accurately predicting and evaluating the bearing capacity of the casing with an advanced and complex structure made of metal materials, and further carrying out weight optimization and other work.
The invention specifically provides a method for predicting the bearing capacity of a casing, which comprises the following steps: after considering material nonlinearity and geometric nonlinearity, performing stress analysis on the case under the combined action of complex working loads by using an elastoplastic finite element method, and when the load increases to reach a critical load, losing the capacity of continuously bearing a certain bearing section of the case, wherein the critical load is the ultimate bearing capacity of the case.
Specifically, the prediction method comprises the following steps:
s1: after considering material nonlinearity and geometric nonlinearity, performing stress analysis on the case under the combined action of complex working loads by adopting an elastic-plastic finite element method;
s2: in the stress analysis process, the working load of the casing is continuously increased, so that the local structure of the casing is subjected to yielding;
s3: as the load is further increased, the region where the casing structure enters plastic yield will expand sharply;
s4: when the load reaches the critical load, the stress and strain of a certain bearing section of the casing reach the limit value of the material, the section loses the capability of continuously bearing, and then the casing fails, at the moment, any small load increase causes the strain to be sharply increased, and the critical load is the limit bearing capability of the casing.
Further, the judgment that any small load increase in S4 causes a sharp increase in strain is based on the fact that the rate of increase in strain of the casing is greater than a certain threshold value at any small load increase.
Still further, the threshold is 15%.
Furthermore, the method for calculating the strain growth rate of the casing comprises the following steps:
work load combination in a certain area
Maximum strain epsilon of receiver under action F Maximum strain ε after any infinitesimal load increment dF F+dF The strain growth rate d epsilon of the casing is d epsilon＝(ε F+dF -ε F )/ε F 。
Furthermore, in the finite element stress analysis process, the working load borne by the casing is continuously increased by a load step method, so that the calculated result is not converged under the action of a certain load due to the fact that the strain growth rate d epsilon of the casing structure is larger than the threshold value, and the corresponding working load is the ultimate bearing capacity of the casing.
Furthermore, the infinitely small load increment dF is obtained by setting an automatic time step to carry out dichotomy, if the strain increase rate under the dichotomy load increment meets the condition that the strain increase rate is larger than the threshold value, the automatic dichotomy is automatically carried out again until the dichotomy time of a certain load increment dF reaches the preset time, at the moment, the time step is small enough, and if the strain increase rate still meets the condition that the strain increase rate is larger than the threshold value, the calculation is stopped.
Further, the predetermined number of times is 25 times.
The invention further provides the casing, and the casing is evaluated and manufactured by adopting the casing bearing capacity prediction method.
The invention also provides an aviation gas turbine engine which is characterized by comprising the casing.
Compared with the prior art, the invention has the advantages that:
compared with the best prior art, the method considers the influence of factors such as a complex structure, a multi-load combination and a stress concentration structure on the prediction accuracy of the bearing capacity of the casing, effectively improves the prediction accuracy of the bearing capacity of the metal aeroengine casing, further reduces the weight of the casing and improves the economy.
The comparison precision of the bearing capacity of the casing predicted by the method and the test result is-4.4%, the precision is improved by about 21% compared with the best technical method in the prior art, and the metal material casing designed by the method is successfully applied to a certain advanced civil turboshaft engine.
Additional features and advantages of the invention will be set forth in the description which follows, and in part will be obvious from the description, or may be learned by the practice of the invention. The objectives and other advantages of the invention will be realized and attained by the structure particularly pointed out in the written description and claims hereof as well as the appended drawings.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the embodiments or the description of the prior art will be briefly described below, and it is obvious that the drawings in the following description are some embodiments of the present invention, and other drawings can be obtained by those skilled in the art without creative efforts.
FIG. 1 is a schematic view of a certain casing structure;
FIG. 2 illustrates a local equivalent stress distribution map for a casing;
FIG. 3 shows a localized plastic strain profile for an aircraft engine case;
fig. 4 shows a schematic diagram of a real casing debris after a static test.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention. All other embodiments, which can be obtained by a person skilled in the art without making any creative effort based on the embodiments in the present invention, belong to the protection scope of the present invention.
The invention provides a prediction and evaluation method for the bearing capacity of a metal material aero-engine case based on elasto-plastic finite element analysis. For a metal material casing with a complex geometric structure, after considering material nonlinearity and geometric nonlinearity, a finite element method is adopted to perform stress analysis on the casing under the combined action of complex working loads, and in the stress analysis process, the local structure of the casing is enabled to be subjected to yielding by continuously increasing the working load of the casing. As the load is further increased, the region where the casing structure enters plastic yield will expand sharply; when the load reaches the critical load, the stress and strain of a certain bearing section of the casing reach the limit value of the material, the section loses the capability of continuously bearing, then the casing fails, any small load increase causes the strain to be sharply increased, and the critical load is the limit bearing capability of the casing.
A certain area has various working loads F n Wherein n is a positive integer. The work load combination of a certain area
Including but not limited to aerodynamic loads, cavity pressure loads, temperature loads, aircraft dynamic loads, attachment loads, blade loss, and other abnormal loads, in the form of a combination of forces including shear stress, radial forces, axial forces, torque, and the like.
Working load combination in certain area
Maximum strain epsilon of receiver under action F Maximum strain ε after any infinitesimal load increment dF F+dF When it comes to
dε＝(ε F+dF -ε F )/ε F ＞15％ (a)
At any small load increment, the strain growth rate of the casing is greater than 15%, and the casing is considered to lose its load-bearing capacity.
In the finite element stress analysis process, the working load borne by the casing is continuously increased by a load step method, so that the calculated result is not converged due to the fact that the strain growth rate of the casing structure meets the formula (a) under the action of a certain load, and the corresponding working load is the ultimate bearing capacity of the casing. If the strain growth rate under the two-component load increment satisfies the formula (a), automatically dividing the load increment into two again for calculation until the division times of a certain load increment dF are enough (more than 25 times), wherein the time step is small enough, and if the strain growth rate still satisfies the formula (a), the calculation is stopped.
In summary, according to the method for predicting the bearing capacity of the metal material casing based on the instability of the bearing section of the casing through the elastoplasticity analysis, after a sufficient number of times of the dichotomous load increment, the strain increase rate is still larger than 15%, and then the judgment criterion of the bearing capacity loss of the casing is considered.
Based on the prediction and evaluation method for the bearing capacity of the metal aeroengine case, the invention further provides the case, and the case is evaluated and manufactured by the prediction method for the bearing capacity of the case. Compared with the existing casing, the weight of the casing designed by the invention is further reduced, and the economy is improved.
Based on the casing, the invention further provides an aviation gas turbine engine, which is characterized by comprising the casing. The engine has lighter weight and lower cost on the premise of meeting the strength requirement.
In order to verify the effectiveness and the precision of the prediction and the evaluation of the bearing capacity of the metal material aeroengine case with complex structure and load, the invention carries out simulation and test verification on the bearing capacity of a certain real case, and the result is shown in the table 1.
TABLE 1 comparison of the prediction of the bearing capacity of a case of an aircraft engine and the results of the verification of the burst speed algorithm
The bearing capacity of a certain aeroengine casing predicted by the method is 0.86F, the simulation result of the local finite element of the casing under the critical load is shown in figure 3, and figure 3 shows the local plastic strain distribution diagram of the certain aeroengine casing simulated by the finite element. During the static test, when the load reaches 0.90F, the mounting bolt hole edge of the casing is cracked, for example, fig. 4 is a real casing remains after the static test, and fig. 4 shows the situation that the mounting bolt hole edge is cracked. The comparison precision of the bearing capacity of the casing predicted by the method and the test result is-4.4%, the precision is improved by about 21% compared with the best technical method in the prior art, and the metal material casing designed by the method is successfully applied to a certain advanced civil turboshaft engine.
In the description of the present invention, it is to be understood that the terms "center", "longitudinal", "lateral", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like, indicate orientations or positional relationships based on those shown in the drawings, and are used only for convenience in describing the present invention and for simplicity in description, and do not indicate or imply that the referenced devices or elements must have a particular orientation, be constructed and operated in a particular orientation, and thus, are not to be construed as limiting the present invention. Furthermore, the terms "first," "second," and the like are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or to implicitly indicate a number of the indicated technical features. Thus, a feature defined as "first," "second," etc. may explicitly or implicitly include one or more of that feature. In the description of the present invention, "a plurality" means two or more unless otherwise specified.
Although the present invention has been described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some technical features may be equivalently replaced; and such modifications or substitutions do not depart from the spirit and scope of the corresponding technical solutions of the embodiments of the present invention.
Claims (10)
1. A method for predicting the bearing capacity of a casing, the method comprising: after considering material nonlinearity and geometric nonlinearity, performing casing stress analysis under the combined action of complex working loads by adopting an elastic-plastic finite element method, gradually increasing the working load of the casing, and when the load increase reaches a critical load, losing the capability of continuously bearing a certain bearing section of the casing, wherein the critical load is the ultimate bearing capability of the casing.
2. The prediction method according to claim 1, characterized in that it comprises the steps of:
s1, considering material nonlinearity and geometric nonlinearity, and performing stress analysis on the case under the combined action of complex working loads by using an elastic-plastic finite element method;
s2, in the process of stress analysis, the local structure of the casing is enabled to be in yield by continuously increasing the working load of the casing;
s3, along with further increase of the load, the casing structure enters a plastic yield area to be sharply enlarged;
and S4, when the load reaches the critical load, the stress and the strain of a certain bearing section of the case reach the limit value of the material, the section loses the capability of continuously bearing, and then the case fails, at the moment, the strain growth rate of the case is sharply increased due to any small load increase, and the critical load is the limit bearing capability of the case.
3. The prediction method according to claim 2, wherein the judgment that any small load increase in S4 causes a sharp increase in the strain increase rate of the casing is based on the fact that the strain increase rate of the casing is greater than a certain threshold value at any small load increase.
4. The prediction method according to claim 3, characterized in that said threshold value is 15%.
5. The method of predicting according to claim 3, wherein the strain growth rate of the casing is calculated by:
work load combination in a certain area
Maximum strain epsilon of the casing under action F Maximum strain ε after any infinitesimal load increment dF F+dF The strain growth rate d epsilon of the casing is d epsilon = (epsilon) F+dF -ε F )/ε F 。
6. The prediction method as claimed in claim 3, wherein during the finite element stress analysis, the working load borne by the casing is continuously increased by the load step method, so that the calculated result is not converged due to the case structure meeting the requirement that the variable growth rate d epsilon is greater than the threshold under a certain load, and the corresponding working load is the ultimate bearing capacity of the casing.
7. The prediction method according to claim 3, wherein the infinitely small load increment dF is obtained by bisection method by setting an automatic time step, if the strain increase rate in the two-component load increment satisfies a condition larger than the threshold value, the calculation is automatically performed by bisection again until the bisection time for a certain load increment dF reaches a predetermined time, at which time the time step is small enough, and if the strain increase rate still satisfies a condition larger than the threshold value, the calculation is stopped.
8. The prediction method according to claim 7, wherein the predetermined number of times is 25 times.
9. A casing, characterized in that it is obtained by evaluation using the method for predicting the bearing capacity of a casing according to any one of the preceding claims.
10. An aircraft gas turbine engine, characterized in that the engine has a casing according to claim 9.
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| CN117150869A (en) * | 2023-10-31 | 2023-12-01 | 中国航发四川燃气涡轮研究院 | Design method for metal matrix composite blisk fracture simulation test |
| CN117150869B (en) * | 2023-10-31 | 2024-01-09 | 中国航发四川燃气涡轮研究院 | Design method for metal matrix composite blisk fracture simulation test |
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