CN106777479A - Turbo blade Nonlinear creep analysis method based on beam theory - Google Patents
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Abstract
The invention discloses a kind of turbo blade Nonlinear creep analysis method based on beam theory, comprise the following steps：Material creep parameter at a, the multiple temperature for determining in turbo blade working range；B, the working time of turbo blade is divided into multiple time steps；C, the multiple sections for choosing turbo blade simultaneously divide grid division；D, based on beam theory, obtain the stress and lasting damage after each time step blade creep and creep relaxation；E, acquisition blade creep elongation and creep rupture are damaged.Consider the principal element of turbo blade creep, obtaining convenient, precision can meet Practical requirement, obtain efficiency and improve hundreds times, it is adaptable to which the comparative analysis of multi-scheme blade, life-cycle blade creep analysis and the online service life supervision of turbo blade, engineering practicability are more preferable.Analysis verification is carried out to many types of powering turbines blade creep elongation and creep rupture life, engine long test result shows that the data precision of acquisition can meet Practical requirement.
Description
Technical Field
The invention relates to the technical field of detection and calibration of turbine blades of aero-engines, in particular to a nonlinear creep analysis method of a turbine blade based on a beam theory.
Background
The turbine blade is the worst part of the working environment in the engine, the creep deformation and creep rupture of the turbine blade are important failure modes of the turbine blade, and the creep analysis of the turbine blade is important content of the engine design and the outfield monitoring. Creep is a non-linear deformation that increases with time, and blade creep is related to operating temperature, stress level, and duration.
The conventional blade creep analysis generally adopts a universal three-dimensional finite element method, creep is considered in a constitutive equation, and the creep of a structure is simulated through material creep parameters, discretized structural rigidity and application of corresponding boundary conditions. The three-dimensional finite element creep analysis is long in time consumption and low in efficiency, and is difficult to adapt to the requirements of blade design analysis and blade service life monitoring of multiple schemes, multiple working conditions and long service life.
Disclosure of Invention
The invention provides a turbine blade nonlinear creep analysis method based on a beam theory, and aims to solve the technical problems that the existing three-dimensional finite element creep analysis is long in time consumption and low in efficiency, and is difficult to adapt to multi-scheme, multi-working-condition and long-service-life blade design analysis and real-time monitoring of the service life of a blade.
The invention provides a turbine blade nonlinear creep analysis method based on a beam theory, which comprises the following steps of: a. determining material creep parameters at a plurality of temperatures within a turbine blade operating range; b. dividing the operating time of the turbine blade into a plurality of time steps; c. selecting a plurality of sections of the turbine blade and dividing and meshing the sections; d. acquiring the creep stress and the permanent damage of the blade at each time step after the creep and the creep relaxation based on a beam theory; e. and acquiring the creep elongation and creep lasting damage of the blade.
Further, the specific implementation steps of the step a are as follows: determining the material creep equation parameters of at least three temperatures in the working temperature range of the blade, wherein the material creep equation at the specific temperature is
c＝Aσmtp
Wherein A is a constant, m is a stress index, p is a temperature index, A, m, p are determined by a material creep test curve,cfor creep strain, σ is stress, and t is time; creep equations at different temperatures can be obtained according to creep tests at multiple temperatures; in the case of limited material creep test data, the creep test curves are constructed according to discrete material creep limits.
Further, the specific implementation steps of step c are as follows: cutting a radial cross section along a blade body of the turbine blade, and cutting a plurality of radial cross sections along an axial direction of the blade body; dividing each radial section into a plurality of section meshes composed of triangular mesh units; nodes are formed between the adjacent triangle mesh cell handoffs.
Further, the specific implementation steps of step d are as follows: according to the plane hypothesis of the radial section, the tensile stress and the bending stress of the turbine blade at each node position of the radial section at the initial moment are obtained by adopting a beam theory and a numerical method; selecting a joint j point on a hypothetical plane, wherein the stress at the initial moment is sigmaj(0) At the lapse of 1 st period of time Δ1After t, assume that the j points are all subjected to σ in this periodj(0) Obtaining delta according to creep equation of material under action of stress1Creep strain increment at time tConsidering creep strain delta from the radial cross-sectional plane assumptionObtaining j point total strain increment delta by adopting numerical method1 j。
Further, j point Δ1the stress increment at time t is:
wherein E isjThe modulus of elasticity at point j;
j point Δ1the stress at time t is:
σj(1)＝σj(0)+Δ1σj。
further, the stress σ according to the time i-1j(i-1) and creep equation of the material to obtain DeltaiCreep strain increment of j point corresponding to t timeConsidering creep strain delta from the radial cross-sectional plane assumptionObtaining j point total strain increment delta in a numerical modei j。
Further, Δithe j point stress increment corresponding to t is:
wherein E isjThe modulus of elasticity at point j;
the stress at time j at time i is:
σj(i)＝σj(i-1)+Δiσj。
further, acquiring the equivalent stress of a j point in the action time of the external load; acquiring creep endurance strength reserve of a j point in the action time of the external load; and acquiring creep endurance strength reserve of a j point under the combined action of a plurality of working conditions.
Further, for the nodes corresponding to the k section and the k +1 section of two adjacent radial sections, the creep elongation is as follows:
wherein,k+1is the creep amount of the corresponding point of the k +1 section,kthe amount of creep of the corresponding point of the k section, hk+1Leaf height, h, of the corresponding point of the k +1 sectionkThe leaf height of a corresponding point of the k section; the creep elongation for the overall leaf height was obtained as:
further, the specific implementation steps of step e are as follows: and d, repeating the step d to obtain the calculation results of the stress, the strength reserve and the creep elongation of each node of all the radial sections, and obtaining the lasting damage of each node of the turbine blade in the working time according to the accumulated damage principle.
The invention has the following beneficial effects:
the turbine blade nonlinear creep analysis method based on the beam theory considers the main factors of the turbine blade creep, is convenient to obtain, has the precision capable of meeting the practical engineering requirements, is higher in obtaining efficiency by hundreds of times compared with the existing three-dimensional finite element method, is suitable for multi-scheme blade comparison analysis, full-life blade creep analysis and online life monitoring of the turbine blade, and is better in engineering practicability. The creep elongation and the endurance life of the multi-type engine turbine blade are analyzed and verified by using the method, and engine long test results show that the acquired data precision can meet engineering practical requirements and the expected effect is achieved.
In addition to the objects, features and advantages described above, other objects, features and advantages of the present invention are also provided. The present invention will be described in further detail below with reference to the drawings.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of this application, illustrate embodiments of the invention and, together with the description, serve to explain the invention and not to limit the invention. In the drawings:
FIG. 1 is a flow chart illustrating the steps of a method for analyzing the nonlinear creep of a turbine blade based on the beam theory in accordance with a preferred embodiment of the present invention.
Detailed Description
The embodiments of the invention will be described in detail below with reference to the accompanying drawings, but the invention can be embodied in many different forms, which are defined and covered by the following description.
FIG. 1 is a flow chart illustrating the steps of a method for analyzing the nonlinear creep of a turbine blade based on the beam theory in accordance with a preferred embodiment of the present invention. As shown in FIG. 1, the method for analyzing the nonlinear creep of the turbine blade based on the beam theory of the embodiment comprises the following steps: a. determining material creep parameters at a plurality of temperatures within a turbine blade operating range; b. dividing the operating time of the turbine blade into a plurality of time steps; c. selecting a plurality of sections of the turbine blade and dividing and meshing the sections; d. acquiring the creep stress and the permanent damage of the blade at each time step after the creep and the creep relaxation based on a beam theory; e. and acquiring the creep elongation and creep lasting damage of the blade. Alternatively, the order of implementation of steps b and c may be reversed. The turbine blade nonlinear creep analysis method based on the beam theory considers the main factors of the turbine blade creep, is convenient to obtain, has the precision capable of meeting the practical engineering requirements, is higher in obtaining efficiency by hundreds of times compared with the existing three-dimensional finite element method, is suitable for multi-scheme blade comparison analysis, full-life blade creep analysis and online life monitoring of the turbine blade, and is better in engineering practicability. The creep elongation and the endurance life of the multi-type engine turbine blade are analyzed and verified by using the method, and engine long test results show that the acquired data precision can meet engineering practical requirements and the expected effect is achieved. The beam theory is to simplify the three-dimensional problem of the elasticity theory into a one-dimensional problem.
In this embodiment, the specific implementation steps of step a are as follows: determining the material creep equation parameters of at least three temperatures in the working temperature range of the blade, wherein the material creep equation at the specific temperature is
c＝Aσmtp
Wherein A is a constant, m is a stress index, p is a temperature index, A, m, p are determined by a material creep test curve,cfor creep strain, σ isForce, t is time; creep equations at different temperatures can be obtained according to creep tests at multiple temperatures; in the case of limited material creep test data, the creep test curves are constructed according to discrete material creep limits.
In this embodiment, the specific implementation steps of step c are as follows: cutting a radial cross section along a blade body of the turbine blade, and cutting a plurality of radial cross sections along an axial direction of the blade body; dividing each radial section into a plurality of section meshes composed of triangular mesh units; nodes are formed between the adjacent triangle mesh cell handoffs.
In this embodiment, the specific implementation steps of step d are as follows: according to the plane hypothesis of the radial section, the tensile stress and the bending stress of the turbine blade at each node position of the radial section at the initial moment are obtained by adopting a beam theory and a numerical method; selecting a joint j point on a hypothetical plane, wherein the stress at the initial moment is sigmaj(0) At the lapse of 1 st period of time Δ1After t, assume that the j points are all subjected to σ in this periodj(0) Obtaining delta according to creep equation of material under action of stress1Creep strain increment at time tConsidering creep strain delta from the radial cross-sectional plane assumptionObtaining j point total strain increment delta by adopting numerical method1 j。
In this embodiment, j point Δ1the stress increment at time t is:
wherein E isjThe modulus of elasticity at point j;
j point Δ1the stress at time t is:
σj(1)＝σj(0)+Δ1σj。
in this embodiment, the stress σ at the time i-1j(i-1) and creep equation of the material to obtain DeltaiCreep strain increment of j point corresponding to t timeConsidering creep strain delta from the radial cross-sectional plane assumptionObtaining j point total strain increment delta in a numerical modei j。
In this example,. DELTA.ithe j point stress increment corresponding to t is:
wherein E isjThe modulus of elasticity at point j;
the stress at time j at time i is:
σj(i)＝σj(i-1)+Δiσj。
in the embodiment, the equivalent stress of the j point in the action time of the external load is obtained; acquiring creep endurance strength reserve of a j point in the action time of the external load; and acquiring creep endurance strength reserve of a j point under the combined action of a plurality of working conditions.
In this embodiment, for the nodes corresponding to the k section and the k +1 section of two adjacent radial sections, the creep elongation is:
wherein,k+1is the creep amount of the corresponding point of the k +1 section,kis k cutAmount of creep of the corresponding point, hk+1Leaf height, h, of the corresponding point of the k +1 sectionkThe leaf height of a corresponding point of the k section;
the creep elongation for the overall leaf height was obtained as:
in this embodiment, the specific implementation steps of step e are as follows: and d, repeating the step d to obtain the calculation results of the stress, the strength reserve and the creep elongation of each node of all the radial sections, and obtaining the lasting damage of each node of the turbine blade in the working time according to the accumulated damage principle.
In practice, a convenient method of turbine blade creep acquisition is provided. The main idea is as follows: dividing the working time into a plurality of time steps; acquiring the creep of the blade at each time step, stress after the creep is relaxed and permanent damage based on a beam theory; finally, the creep elongation and creep endurance damage of the blade are calculated. The method comprises the following specific steps:
(1) determining material creep equation parameters at least 3 temperatures within the working temperature range of the blade;
(2) dividing the working time into a plurality of time steps;
(3) selecting a plurality of sections of the blade and dividing the sections into grids;
(4) acquiring tensile and bending stresses of each node of the section;
(5) calculating creep strain of each node according to the temperature and the stress of the node and the time step length;
(6) acquiring node stress after creep relaxation, and acquiring creep endurance damage of a time step;
according to the steps (3) - (6), calculating creep, stress and permanent damage of each time step in the working time;
calculating the creep elongation of the blade, wherein the creep elongation is calculated according to the corresponding nodes of two adjacent sections
Creep elongation of the entire blade is
And according to the accumulated damage principle, calculating the permanent damage of each node of the blade in the working time.
The turbine blade nonlinear creep analysis method based on the beam theory is characterized in that the blade nonlinear creep based on the beam theory is obtained; acquiring a stress numerical value of the section with the irregular shape; obtaining the endurance life of the blade considering creep relaxation; acquiring creep elongation of the blade based on section strain; the foregoing calculation procedure. The method considers the main factors of blade creep, is convenient to obtain, has the precision capable of meeting the practical engineering requirements, improves the obtaining efficiency by hundreds of times compared with the existing three-dimensional finite element method, is suitable for multi-scheme blade comparative analysis, full-life blade creep analysis and online life monitoring of the turbine blade, and has better engineering practicability. By using the method, the creep elongation and the endurance life of the multi-type engine turbine blade can be obtained, and engine long-test results show that the obtained data precision can meet the practical engineering requirements, and the expected effect is achieved.
The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (10)
1. A turbine blade nonlinear creep analysis method based on a beam theory is characterized in that,
the method comprises the following steps:
a. determining material creep parameters at a plurality of temperatures within a turbine blade operating range;
b. dividing the operating time of the turbine blade into a plurality of time steps;
c. selecting a plurality of sections of the turbine blade and dividing and meshing the sections;
d. acquiring the creep stress and the permanent damage of the blade at each time step after the creep and the creep relaxation based on a beam theory;
e. and acquiring the creep elongation and creep lasting damage of the blade.
2. The method of beam theory based turbine blade nonlinear creep analysis of claim 1,
the specific implementation steps of the step a are as follows:
determining material creep equation parameters at least three temperatures within the blade operating temperature range,
the creep equation of a material at a specific temperature is
c＝Aσmtp
Wherein A is a constant, m is a stress index, p is a temperature index, A, m, p are determined by a material creep test curve,cfor creep strain, σ is stress, and t is time; creep equations at different temperatures can be obtained according to creep tests at multiple temperatures;
in the case of limited material creep test data, the creep test curves are constructed according to discrete material creep limits.
3. The method of beam theory based turbine blade nonlinear creep analysis of claim 2,
the specific implementation steps of the step c are as follows:
cutting a radial cross section along a blade body of the turbine blade, and cutting a plurality of radial cross sections along an axial direction of the blade body;
dividing each radial section into a plurality of section meshes composed of triangular mesh units;
nodes are formed between the adjacent triangle mesh cell handoffs.
4. The method of beam theory based turbine blade nonlinear creep analysis of claim 3,
the specific implementation steps of the step d are as follows:
according to the plane hypothesis of the radial section, the tensile stress and the bending stress of the turbine blade at each node position of the radial section at the initial moment are obtained by adopting a beam theory and a numerical method;
selecting a joint j point on a hypothetical plane, wherein the stress at the initial moment is sigmaj(0) At the lapse of 1 st period of time Δ1After t, assume that the j points are all subjected to σ in this periodj(0) Obtaining delta according to creep equation of material under action of stress1Creep strain increment at time t
Considering creep strain delta from the radial cross-sectional plane assumptionObtaining j point total strain increment delta by adopting numerical method1 j。
5. The method of beam theory based turbine blade nonlinear creep analysis of claim 4,
j point Δ1the stress increment at time t is:
wherein E isjThe modulus of elasticity at point j;
j point Δ1the stress at time t is:
σj(1)＝σj(0)+Δ1σj。
6. the method of beam theory based turbine blade nonlinear creep analysis of claim 5,
stress σ according to time i-1j(i-1) and creep equation of the material to obtain DeltaiCreep strain increment of j point corresponding to t time
Considering creep strain delta from the radial cross-sectional plane assumptionObtaining j point total strain increment delta in a numerical modei j。
7. The method of beam theory based turbine blade nonlinear creep analysis of claim 6,
Δithe j point stress increment corresponding to t is:
wherein E isjThe modulus of elasticity at point j;
the stress at time j at time i is:
σj(i)＝σj(i-1)+Δiσj。
8. the method of beam theory based turbine blade nonlinear creep analysis of claim 7,
acquiring the equivalent stress of a j point in the action time of the external load;
acquiring creep endurance strength reserve of a j point in the action time of the external load;
and acquiring creep endurance strength reserve of a j point under the combined action of a plurality of working conditions.
9. The method of beam theory based turbine blade nonlinear creep analysis of claim 8,
for the nodes corresponding to the k section and the k +1 section of two adjacent radial sections, the creep elongation is as follows:
wherein,k+1is the creep amount of the corresponding point of the k +1 section,kthe amount of creep of the corresponding point of the k section, hk+1Leaf height, h, of the corresponding point of the k +1 sectionkThe leaf height of a corresponding point of the k section;
the creep elongation for the overall leaf height was obtained as:
10. the method of beam theory based turbine blade nonlinear creep analysis of claim 9,
the concrete implementation steps of the step e are as follows:
repeating the step d to obtain the calculation results of the stress, the strength reserve and the creep elongation of each node of all the radial sections,
and obtaining the lasting damage of each node of the turbine blade in the working time according to the accumulated damage principle.
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| CN112630045A (en) * | 2020-11-19 | 2021-04-09 | 西北工业大学 | Creep life prediction method of nickel-based single crystal alloy based on real blade sample |
| CN112945495A (en) * | 2021-02-05 | 2021-06-11 | 中国航发沈阳发动机研究所 | Fatigue strength testing method for blades of aircraft engine in batch production |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN110245394A (en) * | 2019-05-28 | 2019-09-17 | 西北工业大学 | The creep of nickel-based monocrystal turbine cooling blade solid matter air film hole is equivalent and simplifies method |
| CN112630045A (en) * | 2020-11-19 | 2021-04-09 | 西北工业大学 | Creep life prediction method of nickel-based single crystal alloy based on real blade sample |
| CN112630045B (en) * | 2020-11-19 | 2024-04-12 | 西北工业大学 | Creep life prediction method of nickel-based single crystal alloy based on real blade sample |
| CN112945495A (en) * | 2021-02-05 | 2021-06-11 | 中国航发沈阳发动机研究所 | Fatigue strength testing method for blades of aircraft engine in batch production |
| CN112945495B (en) * | 2021-02-05 | 2022-06-03 | 中国航发沈阳发动机研究所 | Method for testing fatigue strength of blades of aero-engine in batch |
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