CN116933447A - Method for evaluating reliability of damping structure of coated turbine blade - Google Patents
Method for evaluating reliability of damping structure of coated turbine blade Download PDFInfo
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- 238000013016 damping Methods 0.000 title claims abstract description 80
- 238000000034 method Methods 0.000 title claims abstract description 35
- 239000011248 coating agent Substances 0.000 claims abstract description 119
- 238000000576 coating method Methods 0.000 claims abstract description 119
- 239000000463 material Substances 0.000 claims description 21
- 238000004364 calculation method Methods 0.000 claims description 9
- 239000007921 spray Substances 0.000 claims description 3
- 230000007774 longterm Effects 0.000 abstract description 2
- 238000005299 abrasion Methods 0.000 description 4
- 238000011156 evaluation Methods 0.000 description 4
- 238000010586 diagram Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- PNEYBMLMFCGWSK-UHFFFAOYSA-N aluminium oxide Inorganic materials [O-2].[O-2].[O-2].[Al+3].[Al+3] PNEYBMLMFCGWSK-UHFFFAOYSA-N 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000012821 model calculation Methods 0.000 description 1
- 230000000750 progressive effect Effects 0.000 description 1
- 238000005507 spraying Methods 0.000 description 1
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- G06F2119/00—Details relating to the type or aim of the analysis or the optimisation
- G06F2119/02—Reliability analysis or reliability optimisation; Failure analysis, e.g. worst case scenario performance, failure mode and effects analysis [FMEA]
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Abstract
The application discloses a method for evaluating the reliability of a damping structure of a coated turbine blade, which comprises the following steps: stress analysis is firstly carried out on a turbine blade with a damping and coating structure by finite element software, and then the result of the finite element software is obtainedExtracting the contact stress of the coating structure at a fixed rotating speed from the file, evaluating the relation between the contact stress of the coating structure and the yield strength sigma of the coating, if the contact stress peak value of the coating structure is larger than the yield strength sigma of the coating, the reliability of the damping and the coating structure does not reach the standard, returning to redesign the damping structure, otherwise, calculating the equivalent normal contact stress M of the coating structure, and then comparing the equivalent normal contact stress M of the coating structure with the allowable strength S of the coating surface Permit of In contrast, if M>S Permit of The reliability of the damping and coating structure still does not reach the standard, if M is less than or equal to S Permit of The damping and coating structure reliability reaches the standard. The application can ensure the long-term high reliability of damping and coating structures, and has strong universality and high judgment accuracy.
Description
Technical Field
The application relates to the field of steam turbines, in particular to a method for evaluating reliability of a damping structure of a coated steam turbine blade.
Background
The damping structure design is the mainstream design of the current turbine blade, and the typical turbine blade damping structure comprises a shroud band, lacing wires and the like. The damping structures such as the shroud ring, the lacing wire and the like are generally sprayed with a coating on the working surface, and the surface abrasion resistance of the coating is far greater than that of the damping structure, so that the damping structure is used for protecting the shroud ring and the lacing wire main body structure to prevent abrasion. However, the yield strength of the coating is smaller than that of the damping structure, if the contact pressure of the damping structure is too large during operation, the coating can be damaged in a short time, and the abrasion-resistant protection of the damping structure by the coating is invalid, so that the damping structure is extremely easy to wear, crack and even break in the following work, and great potential safety hazard is caused. The reliability check of the damping structure of the turbine blade is an important component of the overall reliability check of the turbine blade, but in the prior art, the influence caused by the coating cannot be considered in the reliability check of the damping structure of the turbine blade, and whether the coating can protect the damping structure from abrasion for a long time or not cannot be estimated, so that potential safety hazards are caused.
Disclosure of Invention
In order to avoid potential safety hazards of a turbine blade damping and coating structure from a design source, the application provides a method for evaluating the reliability of the turbine blade damping structure with a coating. The application judges the blade damping and coating structure reaching the reliable standard, and can ensure that the blade damping and coating structure can be in a safe and stable working state for a long time.
The aim of the application is achieved by the following technical scheme:
a method of evaluating the reliability of a coated turbine blade damping structure, the method comprising the steps of:
step one: stress analysis is carried out on the turbine blade with the damping and coating structure by using finite element software, wherein the material properties of the coating structure are different from those of the blade, and the material properties are respectively and independently set;
step two: extracting the contact stress of the coating structures of the adjacent blades in the result file at a fixed rotating speed, comparing the relation between the contact stress of the coating structures and the coating yield strength sigma, if the peak value of the contact stress of the coating structures is larger than the coating yield strength sigma, the reliability of the damping and coating structures does not reach the standard, returning to redesign the damping structure, otherwise, executing the step III;
step three: according to the normal contact pressure stress of the contact surface of the coating structure of the adjacent blade in the result file at a fixed rotating speed, calculating to obtain the equivalent normal contact pressure stress M of the coating structure, and then combining the equivalent normal contact pressure stress M of the coating structure with the allowable intensity S of the coating surface Permit of In contrast, if M>S Permit of The reliability of the damping and coating structure still does not reach the standard, the damping structure is redesigned, if M is less than or equal to S Permit of The damping and coating structure reliability reaches the standard.
Further, the calculation method of the equivalent normal contact pressure stress M of the coating structure is as follows:
M=（s 0 *Mavg 0 + s 1 *Mavg 1 +…+s i *Mavg i +…+ s n *Mavg n ）*sinα/（s 0 *p 0 + s 1 *p 1 +…+s i *p i +…+ s n *p n ），1≤i≤n；
wherein n is the total number of units with the contact surface contact pressure stress of more than 0 Mpa; s is(s) i Ith in cell with contact pressure stress greater than 0MpaCell area of cell, p i For the ratio of the contact pressure stress of the ith unit to the area of the unit area of more than 0Mpa, mavg i And the normal contact pressure stress mean value of the node contained in the ith unit is the angle between the contact surface and the circumferential direction of the blade.
Further, in the step one, when the stress analysis is performed, the grid of the coating structure of the blade is a hexahedral structured grid.
Further, when the coating structure in the first step has no real material property, the calculation is performed by the following formula:
modulus of elasticity E' =e (1- η)
Density ρ' =ρ (1- η)
Poisson ratio μ' =μ
Wherein E, ρ and μ are the elastic modulus, density and Poisson's ratio of the coating material, E ', ρ ', μ ' are the elastic modulus, density and Poisson's ratio of the coating structure, and η is the spray porosity.
In the second step, the contact stress of the coating structure includes a normal contact stress and a tangential contact stress, the normal contact stress peak value and the tangential contact stress peak value are respectively compared with the coating yield strength sigma, and when the normal contact stress peak value and the tangential contact stress peak value are not greater than the coating yield strength sigma, the third step is executed; otherwise, the reliability of the damping and coating structure does not reach the standard, and the damping structure is redesigned.
Further, the method of redesigning the damping structure includes increasing the initial gap between adjacent blades, increasing the working surface area of the damping structure.
The beneficial effects of the application are as follows:
according to the method for evaluating the reliability of the damping structure of the coated turbine blade, the analysis and calculation are carried out based on finite element software, when the turbine blade is modeled, the damping structure and the coating structure are used as a community for modeling, the influence caused by the coating structure, such as different material properties, is fully considered during calculation, and the accuracy of a model calculation result is high; in the evaluation indexes, the performance indexes of the coating materials are used for replacing the performance indexes of the blade materials in the traditional method to serve as evaluation values, namely, the yield strength and the surface allowable strength of the coating structure are respectively used as evaluation indexes, the calculation results are checked in a progressive mode, the judgment indexes and the method are reasonable and clear, and the judgment accuracy is high. As the spray coating has corresponding process standards, if the reliability of the damping structure with the coating is evaluated to be not up to the standard, the damping structure of the turbine blade must be improved, and the common improvement method is to increase the initial gap between adjacent blades, increase the working surface area of the damping structure and the like, so as to further perfect the design of the damping structure of the turbine blade. The method can ensure long-term high reliability of the damping and coating structure of the turbine blade, and the assessment method is high in universality and high in judgment accuracy.
Drawings
The block diagrams depicted in the figures are merely functional entities and do not necessarily correspond to physically separate entities. That is, the functional entities may be implemented in software, or in one or more hardware modules or integrated circuits, or in different networks and/or processor devices and/or microcontroller devices.
The flow diagrams depicted in the figures are exemplary only, and do not necessarily include all of the elements and operations/steps, nor must they be performed in the order described. For example, some operations/steps may be decomposed, and some operations/steps may be combined or partially combined, so that the order of actual execution may be changed according to actual situations.
FIG. 1 is a flow chart of a method for evaluating the reliability of a coated turbine blade damping structure in accordance with an embodiment of the present application.
FIG. 2 is a schematic view of a damping structure and a coating structure for a turbine blade according to an embodiment of the present application.
Detailed Description
Reference will now be made in detail to exemplary embodiments, examples of which are illustrated in the accompanying drawings. When the following description refers to the accompanying drawings, the same numbers in different drawings refer to the same or similar elements, unless otherwise indicated. The implementations described in the following exemplary examples do not represent all implementations consistent with the application. Rather, they are merely examples of apparatus and methods consistent with aspects of the application as detailed in the accompanying claims.
The terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of the application. As used in this specification and the appended claims, the singular forms "a," "an," and "the" are intended to include the plural forms as well, unless the context clearly indicates otherwise. It should also be understood that the term "and/or" as used herein refers to and encompasses any or all possible combinations of one or more of the associated listed items.
It should be understood that although the terms first, second, third, etc. may be used herein to describe various information, these information should not be limited by these terms. These terms are only used to distinguish one type of information from another. For example, first information may also be referred to as second information, and similarly, second information may also be referred to as first information, without departing from the scope of the application. The word "if" as used herein may be interpreted as "at … …" or "at … …" or "responsive to a determination", depending on the context.
As shown in fig. 1, a method for evaluating reliability of a coated turbine blade damping structure according to an embodiment of the present application includes the steps of:
s1: and (3) carrying out stress analysis on the turbine blade with the damping and coating structure by using finite element software.
The method comprises the steps of firstly carrying out pretreatment setting before finite element analysis on the turbine blade with the damping and coating structure, wherein the pretreatment setting comprises the steps of importing a blade geometric model and dividing grids (or directly importing the grid model), defining unit types, defining material parameters, defining loads and boundary conditions, defining analysis setting and the like. The overall grid needs to be verified by grid independence to obtain reasonable grid division density; preferably, the mesh of the coating structure should be guaranteed to be a hexahedral structured mesh. In addition, the material properties of the coating structure are required to be distinguished from the blade, and the material properties of the coating structure can be replaced according to the following method if the material properties of the coating structure are not true: elastic modulus E '=e (1- η), density ρ' =ρ (1- η), poisson ratio μ '=μ, wherein the material properties of the coating material are E, ρ, μ, the material properties of the coating structure are E', ρ ', μ', η are spray porosity. .
S2: after the finite element calculation is completed, the contact stress of the coating structure of the adjacent blade at a fixed rotating speed is displayed in a result file, the relation between the contact stress of the coating structure and the yield strength sigma of the coating is compared, if the contact stress of the coating structure is larger than the yield strength sigma of the coating, the reliability of the damping and the coating structure does not reach the standard, and the damping structure needs to be redesigned. The method of redesigning the damping structure is to increase the initial gap between adjacent blades, increase the working surface area of the damping structure, etc., otherwise proceed to S3. The contact stress comprises normal contact stress and tangential contact stress, the peak values of the normal contact stress and the tangential contact stress are respectively compared with the yield strength sigma of the coating, if the peak values of the normal contact stress and the tangential contact stress are smaller than the yield strength sigma of the coating, S3 is entered, otherwise, the redesigned damping structure is returned.
S3: the method for calculating the normal contact stress of the contact surface of the coating structure of the adjacent blade in the result file of the finite element software under the fixed rotating speed for the second time to obtain the equivalent normal contact stress M of the coating structure comprises the following steps: counting the total number n of the units with normal contact stress of the contact surface being more than 0Mpa, wherein the unit area of the ith unit is s i The ratio of the area of the unit normal contact stress larger than 0Mpa to the unit area is p i The normal contact stress average value of the nodes contained in the unit is Mavg i The contact surface forms an angle alpha, M=(s) with the circumferential direction of the blade 0 *Mavg 0 + s 1 *Mavg 1 +…+s i *Mavg i +…+ s n *Mavg n ）*sinα/（s 0 *p 0 + s 1 *p 1 +…+s i *p i +…+ s n *p n ) I is more than or equal to 1 and n is more than or equal to n. Then equivalent normal contact stress M of the coating structure and allowable intensity S of the coating surface Permit of In contrast, if M>S Permit of Resistance is thenThe reliability of the damping and coating structures still does not reach the standard, and the damping structure needs to be redesigned, and the method for redesigning the damping structure is to increase the initial gap between adjacent blades, increase the working surface area of the damping structure and the like. If M is less than or equal to S Permit of The damping and coating structure reliability reaches the standard.
The method and apparatus of the present application are further described below as applied to the evaluation of damping and coating structure reliability of a turbine blade.
Step one: the pretreatment setting of stress analysis of a certain turbine blade with a damping and coating structure is carried out by using finite element software ABAQUS: including importing a mesh model, defining cell types, defining material parameters, defining loads and boundary conditions, defining calculation steps, defining analysis settings. And driving finite element software ABAQUS to solve after the setting is completed.
Wherein, the overall grid needs to be verified by grid independence first to obtain reasonable grid division density; the mesh of the coating structure should be guaranteed to be a hexahedral structured mesh. The blade number material parameters were set as follows: modulus of elasticity 2.1 xe 5 Mpa, density 7.8 xe -9 t/mm 3 Poisson's ratio 0.28; the coating structure material is alumina, and the parameters are set as follows: modulus of elasticity 3.5 xe 5 Mpa, density 3.5 xe -9 t/mm 3 Poisson's ratio 0.2. The load is a single centrifugal force load, i.e. the set rotational speed w=3000 rpm=314 rad/s.
Step two: after the finite element calculation is completed, the contact stress of the coating structure at a fixed rotating speed is displayed in a result file, the relation between the contact stress of the coating structure and the yield strength sigma of the coating is compared, if the contact stress of the coating structure is larger than the yield strength sigma of the coating, the reliability of the damping and the coating structure does not reach the standard, the damping structure is required to be redesigned, and otherwise, the step three is entered.
The normal contact stress peak value of the blade shroud coating is 294Mpa, the tangential contact stress peak value is 66Mpa, the normal contact stress peak value of the lacing wire coating is 185Mpa, the tangential contact stress peak value is 197Mpa, and the normal contact stress peak value and the tangential contact stress peak value are respectively smaller than the yield strength sigma=300 Mpa of the coating, and the step III is entered.
Step three: the method for calculating the normal contact stress of the contact surface of the coating structure in the result file of the finite element software under the fixed rotating speed for the second time to obtain the equivalent normal contact stress M of the coating structure comprises the following steps: counting the total number n of the units with normal contact stress of the contact surface being more than 0Mpa, wherein the unit area of the ith unit is s i The ratio of the area of the unit normal contact stress larger than 0Mpa to the unit area is p i The normal contact stress average value of the nodes contained in the unit is Mavg i The contact surface forms an angle alpha, M=(s) with the circumferential direction of the blade 0 *Mavg 0 + s 1 *Mavg 1 +…+s i *Mavg i +…+ s n *Mavg n ）*sinα/（s 0 *p 0 + s 1 *p 1 +…+s i *p i +…+ s n *p n ），1≤i≤n。
Wherein, the equivalent normal contact stress M of the blade shroud coating is calculated Enclosure band Equivalent normal contact stress M of blade lacing wire coating of 68Mpa Lacing wire 61Mpa, allowable intensity S with coating surface Permit of Compared with 70Mpa, the equivalent normal contact stress of the shroud ring and the lacing wire coating is smaller than the allowable strength S of the surface of the coating Permit of Therefore, the reliability of the damping and coating structure of the turbine blade is evaluated to reach the standard by the method.
It will be appreciated by persons skilled in the art that the foregoing description is a preferred embodiment of the application, and is not intended to limit the application, but rather to limit the application to the specific embodiments described, and that modifications may be made to the technical solutions described in the foregoing embodiments, or equivalents may be substituted for elements thereof, for the purposes of those skilled in the art. Modifications, equivalents, and alternatives falling within the spirit and principles of the application are intended to be included within the scope of the application.
Claims (6)
1. A method of evaluating the reliability of a coated turbine blade damping structure, the method comprising the steps of:
step one: stress analysis is carried out on the turbine blade with the damping and coating structure by using finite element software, wherein the material properties of the coating structure are different from those of the blade, and the material properties are respectively and independently set;
step two: extracting the contact stress of the coating structure of the adjacent blade at a fixed rotating speed, comparing the relation between the contact stress of the coating structure and the coating yield strength sigma, if the peak value of the contact stress of the coating structure is larger than the coating yield strength sigma, the reliability of the damping and coating structure does not reach the standard, returning to redesign the damping structure, otherwise, executing the step III;
step three: according to the normal contact pressure stress of the contact surface of the coating structure of the adjacent blade in the result file at a fixed rotating speed, calculating to obtain the equivalent normal contact pressure stress M of the coating structure, and then combining the equivalent normal contact pressure stress M of the coating structure with the allowable intensity S of the coating surface Permit of In contrast, if M>S Permit of The reliability of the damping and coating structure still does not reach the standard, the damping structure is redesigned, if M is less than or equal to S Permit of The damping and coating structure reliability reaches the standard.
2. The method of evaluating the reliability of a coated turbine blade damping structure according to claim 1, wherein the method of calculating the equivalent normal contact compressive stress M of the coated structure is as follows:
M=（s 0 *Mavg 0 + s 1 *Mavg 1 +…+s i *Mavg i +…+ s n *Mavg n ）*sinα/（s 0 *p 0 + s 1 *p 1 +…+s i *p i +…+ s n *p n ），1≤i≤n；
wherein n is the total number of units with the contact surface contact pressure stress of more than 0 Mpa; s is(s) i For contacting the cell area, p, of the ith cell of cells having a compressive stress greater than 0MPa i For the ratio of the contact pressure stress of the ith unit to the area of the unit area of more than 0Mpa, mavg i And the normal contact stress mean value of the node contained in the ith unit is the normal contact stress mean value, and alpha is the included angle between the contact surface and the circumferential direction of the blade.
3. The method of evaluating the reliability of a damping structure of a coated turbine blade according to claim 1, wherein the grid of the coating structure of the blade is a hexahedral structured grid when the stress analysis is performed in the first step.
4. The method of evaluating the reliability of a coated turbine blade damping structure according to claim 1, wherein when the coating structure in step one has no real material properties, the calculation is performed by the following formula:
modulus of elasticity E' =e (1- η)
Density ρ' =ρ (1- η)
Poisson ratio μ' =μ
Wherein E, ρ and μ are the elastic modulus, density and Poisson's ratio of the coating material, E ', ρ ', μ ' are the elastic modulus, density and Poisson's ratio of the coating structure, and η is the spray porosity.
5. The method of evaluating the reliability of a coated turbine blade damping structure according to claim 1, wherein in the second step, the contact stress of the coating structure comprises a normal contact stress and a tangential contact stress, the normal contact stress peak and the tangential contact stress peak are compared with the coating yield strength σ, respectively, and when the normal contact stress peak and the tangential contact stress peak are not greater than the coating yield strength σ, the third step is performed; otherwise, the reliability of the damping and coating structure does not reach the standard, and the damping structure is redesigned.
6. The method of assessing the reliability of a damping structure of a coated turbine blade of claim 5 wherein the method of redesigning the damping structure includes increasing the initial gap between adjacent blades, increasing the working surface area of the damping structure.
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