Gas turbine-oriented rotor and stator gap analysis method, device and equipment

Abstract

The invention relates to the technical field of gas turbines, and discloses a gas turbine-oriented rotor and stator gap analysis method, device and equipment, and the method comprises the steps: obtaining a rotor and stator model of a target gas turbine, and carrying out the preprocessing of the rotor and stator model, and obtaining a rotor and stator finite element model; performing deformation analysis on the rotor and stator finite element model, and determining whether rub-impact occurs between rotors and stators or not; if rub-impact does not occur between the rotors and the stators, node coordinates of the rotors and the stators are obtained based on a rotor and stator finite element model, and gaps between the rotors and the stators are determined according to the node coordinates of the rotors and the stators; and determining the minimum rotor-stator gap and the corresponding rotor-stator node coordinates according to the gaps between the rotors and the stators. According to the method, the rotor and stator finite element model is utilized to perform deformation analysis, the influence of the radial clearance and the axial clearance of the rotor is comprehensively considered, whether the gas turbine is rubbed or not is accurately judged, and the minimum rotor and stator clearance at each moment and the occurrence position are accurately calculated when rub-impact does not occur.

Description

Technical Field

[0001] The present invention relates to the technical field of gas turbines, and in particular to a rotor-stator clearance analysis method, device and equipment for gas turbines. Background Art

[0002] A gas turbine is an internal combustion power machine that uses a continuously flowing gas as a working fluid to drive a high-speed rotating impeller, converting the fuel's energy into useful work. It is a rotary impeller heat engine. Compared to internal combustion engines, gas turbines start quickly at low temperatures and can reach idle speed in minutes even in extremely cold conditions without heating. Gas turbines generally output power through a power turbine, resulting in excellent torque characteristics. Gas turbines also offer high speed, high power density, and low weight.

[0003] In a gas turbine, rotor-stator clearance generally refers to the radial or axial clearance between the rotor (rotating component) and the stator (stationary component). This clearance primarily refers to the gap between the rotor blade tip and the inner wall of the casing, the gap between the rotor blade and the guide vane, and the gap between the stator and the impeller. These clearances affect the efficiency of the compressor and turbine. In pursuit of high thrust-to-weight ratios and low fuel consumption, gas turbine speeds are increasing, while the rotor-stator clearance is decreasing, increasing the probability of rotor-stator rubbing failures. Once rotor-stator rubbing occurs, the clearance increases, reducing efficiency and, in severe cases, causing blade breakage. Furthermore, rotor-stator rubbing causes uncoordinated rotor precession, generating alternating stresses within the rotor and contributing to rotor fatigue failure.

[0004] Currently, there are two main approaches to studying gas turbine tip clearance: one involves experimentally measuring the tip clearance value during engine operation; the other involves analyzing the tip clearance using numerical calculations. Numerical tip clearance analysis methods have gained widespread application due to their cost-effectiveness and ability to provide guidance for subsequent work. Existing numerical tip clearance analysis methods focus on analyzing radial clearance variations. However, axial friction between the rotor and stator of a gas turbine can occur, and considering only radial clearance variations cannot accurately reflect the operating state of the gas turbine. Furthermore, they assume that the rotor axis remains unchanged. However, in actual operation, gas turbines are subject to high overload excitation, causing the rotor and stator to undergo combined bending and torsional deformation, resulting in bending and translation of the rotor axis. This assumption makes rotor-stator clearance analysis infeasible. Summary of the Invention

[0005] In view of this, the present invention provides a method, device and equipment for analyzing the rotor-stator clearance of a gas turbine to solve the problem of inaccurate calculation of the rotor-stator clearance analysis of the gas turbine.

[0006] In a first aspect, the present invention provides a method for analyzing rotor-stator clearance of a gas turbine, the method comprising:

[0007] Obtaining a rotor-stator model of a target gas turbine, and preprocessing the rotor-stator model to obtain a rotor-stator finite element model;

[0008] Conduct deformation analysis on the rotor-stator finite element model to determine whether friction occurs between the rotors and stators;

[0009] If no friction occurs between the rotors and stators, the node coordinates of each rotor and stator are obtained based on the rotor and stator finite element model, and the gap between the rotors and stators is determined according to the node coordinates of the rotor and stator;

[0010] The minimum rotor-stator gap and the corresponding rotor-stator node coordinates are determined according to the gaps between the rotors and stators.

[0011] The rotor-stator clearance analysis method for a gas turbine provided by the present invention uses a rotor-stator finite element model to perform deformation analysis, comprehensively considers the influence of the rotor radial clearance and axial clearance, accurately determines whether rubbing occurs in the gas turbine, and accurately calculates the minimum rotor-stator clearance and the position at each moment when rubbing does not occur. The method is suitable for situations where the axis of the gas turbine rotor is bent and translated, and is conducive to better guiding subsequent installation and adjustment work, optimization design, etc.

[0012] In an optional embodiment, the rotor-stator model is preprocessed to obtain a rotor-stator finite element model, including:

[0013] Perform geometric mesh division on the rotating stator model and discretize it into mesh units;

[0014] The excitation and boundary conditions of the rotor-stator model are set, and the corresponding material properties are set for each independent component of the rotor-stator to obtain the rotor-stator finite element model.

[0015] The rotor-stator clearance analysis method for gas turbines provided by the present invention adopts hexahedral grid to divide the rotor-stator model, which can significantly improve the grid quality and calculation accuracy, reduce numerical diffusion and pseudo-diffusion errors, independently set the excitation and boundary conditions of each rotor-stator component, and can truly simulate the interaction between components. Different components (such as rotor shaft and stator housing) are given real material properties (such as elastic modulus and density), making the model closer to the actual physical properties, ensuring the validity of results such as modal analysis and fatigue life prediction, and providing a scientific basis for structural optimization and fault diagnosis.

[0016] In an optional embodiment, performing deformation analysis on the rotor-stator finite element model to determine whether rubbing occurs between the rotor and the stator includes:

[0017] Set the contact property parameters, contact stress parameters and node coordinate parameters of each rotor-stator, and calculate the contact stress between each rotor-stator and the node coordinates of each rotor-stator;

[0018] If the contact stress between the rotors and stators is 0, there is no friction between the rotors and stators.

[0019] If at least one of the contact stresses between the rotors and stators is not zero, friction occurs between the rotors and stators.

[0020] The rotor-stator clearance analysis method for gas turbines provided by the present invention accurately captures the microscopic interaction between the rotor and the stator by setting contact properties and contact stress parameters and combining them with node coordinate data. The contact stress value directly reflects the intensity of collision or friction, and the change in node coordinates reveals the deformation trend, providing an objective quantitative basis for rubbing judgment. Based on the criterion of whether the contact stress is zero, it can quickly and accurately distinguish whether the rotor and the stator are rubbing, without the need for complex experiments. The method is suitable for dynamic operating condition analysis of high-speed rotating machinery and can provide early warning of potential faults.

[0021] In an optional embodiment, if friction occurs between the rotors and stators, the method further includes:

[0022] According to the calculation results of the contact stress, the coordinates of the rubbing node corresponding to the contact stress not being 0 are determined as the position of the rotor-stator node where the rubbing occurs.

[0023] The rotor-stator clearance analysis method for gas turbines provided by the present invention accurately locks the coordinates of the rubbing nodes through contact stress calculation, directly locates the specific position of abnormal contact between the rotor and stator, avoids the blindness of traditional troubleshooting, and quickly identifies the rubbing "hot spot" area in a data-driven manner, providing precise targets for structural improvement and reducing trial and error costs.

[0024] In an optional embodiment, obtaining the node coordinates of each rotor-stator based on the rotor-stator finite element model, and determining the gap between each rotor-stator according to the node coordinates of the rotor-stator includes:

[0025] Based on the deformation analysis of the rotor-stator finite element model, the node coordinates of each rotor-stator are obtained;

[0026] Obtain a target node of the target rotor, and determine a to-be-studied range and a stator node within the to-be-studied range according to the target node;

[0027] The straight-line distance between each stator node and the target node is calculated as the gap between the target rotor and each stator.

[0028] The rotor-stator clearance analysis method for gas turbines provided by the present invention obtains node coordinates and quantifies the clearance through deformation analysis, accurately depicts the spatial position relationship between the rotor and the stator, defines the research scope based on the target node and calculates the straight-line distance between the stator node and the target node within the research scope, converts the abstract clearance into a measurable physical quantity, and quickly locates the key clearance areas (such as blade tip clearance and shaft seal clearance), providing data support for evaluating assembly accuracy and the influence of thermal deformation.

[0029] In an optional embodiment, determining the minimum rotor-stator gap and the corresponding rotor-stator node coordinates according to the gaps between the rotors and stators includes:

[0030] Obtain node coordinate data of rotors at all levels within a preset time period according to a preset sampling period, and import the node coordinate data into the stator node array and the rotor node array;

[0031] For each level of target rotor, traverse each rotor node in the target rotor and calculate the minimum gap of the target nodes in the target rotor at the same sampling time;

[0032] Compare the minimum gaps of each target node in the target rotor, take the smallest minimum gap as the minimum rotor-stator gap of the target rotor, and the rotor node coordinates and stator node coordinates corresponding to the minimum rotor-stator gap are the corresponding rotor-stator node coordinates.

[0033] In an optional embodiment, the method further includes:

[0034] According to the minimum rotor-stator clearance of each target rotor at each sampling moment, a minimum rotor-stator clearance change curve of each target rotor within a preset time period is drawn;

[0035] The actual working state of the gas turbine is analyzed based on the minimum rotor-stator clearance change curve.

[0036] The proposed method for analyzing rotor-stator clearance for gas turbines achieves dynamic tracking and visualization of the minimum rotor-stator clearance through periodic data collection and precise calculation. By storing node data in a structured manner, the method efficiently traverses and calculates the minimum clearance, accurately locating hazardous areas. The minimum clearance variation curve intuitively reflects clearance fluctuations during gas turbine operation, enabling engineers to promptly identify operating conditions such as friction risks and abnormal vibrations. This provides strong data support for optimizing maintenance strategies, extending equipment life, and ensuring safe and stable unit operation.

[0037] In a second aspect, the present invention provides a rotor-stator clearance analysis device for a gas turbine, the device comprising:

[0038] A finite element model building module is used to obtain a rotor-stator model of a target gas turbine and preprocess the rotor-stator model to obtain a rotor-stator finite element model;

[0039] The friction judgment module is used to perform deformation analysis on the rotor-stator finite element model to determine whether friction occurs between the rotors and stators;

[0040] A gap calculation module is used to obtain the node coordinates of each rotor-stator based on the rotor-stator finite element model if no friction occurs between the rotors and stators, and determine the gap between the rotors and stators according to the node coordinates of the rotors and stators;

[0041] The minimum rotor-stator clearance analysis module is used to determine the minimum rotor-stator clearance and the corresponding rotor-stator node coordinates based on the clearances between the rotors and stators.

[0042] In a third aspect, the present invention provides a computer device comprising: a memory and a processor, the memory and the processor being communicatively connected to each other, the memory storing computer instructions, and the processor executing the method of the first aspect or any corresponding embodiment thereof by executing the computer instructions.

[0043] In a fourth aspect, the present invention provides a computer-readable storage medium having computer instructions stored thereon, the computer instructions being used to enable a computer to execute the method of the first aspect or any corresponding embodiment thereof. BRIEF DESCRIPTION OF THE DRAWINGS

[0044] In order to more clearly illustrate the specific embodiments of the present invention or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the specific embodiments or the description of the prior art. Obviously, the drawings described below are some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative work.

[0045] Figure 1 1 is a flow chart of a method for analyzing rotor-stator clearance of a gas turbine according to an embodiment of the present invention;

[0046] Figure 2 1 is a flow chart of deformation analysis and clearance calculation in a rotor-stator clearance analysis method for a gas turbine according to an embodiment of the present invention;

[0047] Figure 3 is a flow chart of another method for analyzing rotor-stator clearance of a gas turbine according to an embodiment of the present invention;

[0048] Figure 4 1 is a schematic diagram of a flow chart of calculating the minimum rotor-stator clearance in a rotor-stator clearance analysis method for a gas turbine according to an embodiment of the present invention;

[0049] Figure 5 2 is a block diagram of a rotor-stator clearance analysis device for a gas turbine according to an embodiment of the present invention;

[0050] Figure 6 Schematic diagram of the hardware structure of a computer device according to an embodiment of the present invention. DETAILED DESCRIPTION

[0051] To make the purpose, technical solutions, and advantages of the embodiments of the present invention more clear, the technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without making creative efforts shall fall within the scope of protection of the present invention.

[0052] An embodiment of the present invention provides a rotor-stator clearance analysis method for a gas turbine. By using a rotor-stator finite element model to perform deformation analysis, the influence of the rotor radial clearance and axial clearance is comprehensively considered to accurately determine whether rubbing occurs in the gas turbine, and when no rubbing occurs, accurately calculate the minimum rotor-stator clearance and the occurrence position at each moment.

[0053] According to an embodiment of the present invention, an embodiment of a rotor-stator clearance analysis method for a gas turbine is provided. It should be noted that the steps shown in the flowchart of the accompanying drawings can be executed in a computer system such as a set of computer executable instructions, and although a logical order is shown in the flowchart, in some cases, the steps shown or described can be executed in an order different from that shown here.

[0054] In this embodiment, a method for analyzing rotor-stator clearance of a gas turbine is provided, which can be used in the above-mentioned computer system. Figure 1 FIG. 1 is a flow chart of a method for analyzing rotor-stator clearance of a gas turbine according to an embodiment of the present invention. Figure 1 As shown, the process includes the following steps:

[0055] Step S101 : obtaining a rotor-stator model of a target gas turbine, and preprocessing the rotor-stator model to obtain a rotor-stator finite element model.

[0056] Specifically, in order to accurately analyze the deformation of the rotor and stator, the finite element method is used to model the rotor and stator of the target gas turbine, including but not limited to: obtaining the rotor and stator model of the target gas turbine, setting material properties, meshing the gas turbine, setting the excitation and boundary conditions of the gas turbine, etc., to obtain a finite element model of the rotor and stator. The modeling process can be implemented with the help of professional modeling software. The specific process can refer to the usage of the modeling software, which will not be repeated here.

[0057] Step S102: performing deformation analysis on the rotor-stator finite element model to determine whether friction occurs between the rotors and stators.

[0058] Specifically, the purpose of performing deformation analysis on the rotor-stator finite element model is to obtain the deformation data of the rotor-stator, and the deformation data includes but is not limited to: displacement deformation data, the deformation of the rotor (such as blades, discs) along the radial direction, which directly affects the rotor-stator clearance (such as the reduction of the radial clearance between the blade tip and the casing may cause rubbing), the radial expansion or contraction of the stator (such as the casing, partition), which is affected by the temperature field and airflow pressure (such as the radial expansion of the casing under high temperature may increase the blade tip clearance); strain data; stress data; contact state parameters; for example only, but not limited to this.

[0059] like Figure 2 The figure shows a flow chart of deformation analysis and clearance calculation for a gas turbine. By analyzing the deformation data, it is determined whether the rotor and stator have rubbed. If rubbed has occurred, the minimum rotor-stator clearance is 0.

[0060] Step S103 : if no rubbing occurs between the rotors and stators, the node coordinates of the rotors and stators are obtained based on the rotor-stator finite element model, and the gaps between the rotors and stators are determined according to the node coordinates of the rotors and stators.

[0061] Specifically, if Figure 2 As shown, if no friction occurs between the rotors and stators at all levels, then based on the deformation analysis results of the rotor-stator finite element model, the node coordinates of the rotor-stator at each moment are obtained, including but not limited to: rotor nodes (for example, blade tip nodes, blade root nodes, blade middle nodes, wheel edge nodes, shaft nodes, etc.), stator nodes (for example, casing inner surface nodes, casing support structure nodes, stator root nodes, bearing seat hole nodes, etc.), gap nodes, contact analysis nodes, etc. In this embodiment, the main gaps between the rotors and stators are analyzed, so the node coordinates where friction may occur can be selected for analysis to reduce the amount of calculation, for example only, but not limited to this. During the deformation analysis, each node will be automatically numbered, and the node numbering is used to distinguish each node, which is equivalent to a simplified representation of the node coordinates.

[0062] When rubbing occurs, the gap at the location where rubbing occurs is 0, that is, the minimum rotor-stator gap is 0; when no rubbing occurs, the distance between each rotor node and the corresponding stator node where rubbing may occur is calculated as the gap between each rotor and stator.

[0063] Step S104: determining the minimum rotor-stator gap and the corresponding rotor-stator node coordinates according to the gaps between the rotors and stators.

[0064] Specifically, the clearance between each rotor and stator is calculated to obtain the minimum rotor-stator clearance and its location. By calculating and counting the minimum rotor-stator clearance and the corresponding rotor-stator coordinates of each rotor at different sampling times within a preset time period under a certain working state, the influence of radial clearance and axial clearance is taken into account. This method is suitable for analyzing the rotor-stator clearance of a gas turbine under large overload excitation.

[0065] The coordinates of each node are in the global coordinate system, so when calculating the rotor-stator clearance, the global coordinate system is also used as the reference. The bending and translation of the rotor axis will not affect the calculation result of the rotor-stator clearance, so the calculation result of the minimum rotor-stator clearance is more accurate.

[0066] The rotor-stator clearance analysis method for a gas turbine provided in this embodiment uses a rotor-stator finite element model to perform deformation analysis, comprehensively considers the influence of the rotor radial clearance and axial clearance, accurately determines whether rubbing occurs in the gas turbine, and accurately calculates the minimum rotor-stator clearance and the position at each moment when rubbing does not occur. The method is applicable to situations where the axis of the gas turbine rotor is bent and translated, and is conducive to better guiding subsequent installation and adjustment work, optimization design, etc.

[0067] In this embodiment, a method for analyzing rotor-stator clearance of a gas turbine is provided, which can be used in the above-mentioned computer system. Figure 3 FIG. 1 is a flow chart of a method for analyzing rotor-stator clearance of a gas turbine according to an embodiment of the present invention. Figure 3 As shown, the process includes the following steps:

[0068] Step S201 : obtaining a rotor-stator model of a target gas turbine, and preprocessing the rotor-stator model to obtain a rotor-stator finite element model.

[0069] Specifically, the above step S201 includes:

[0070] Step S2011, performing geometric mesh division on the rotor-stator model and discretizing it into mesh units.

[0071] Specifically, a block partitioning technique can be used to discretize the rotor-stator model into multiple mesh elements, ensuring that the mesh is aligned along the structural curvature and force direction, improving computational accuracy, and making it suitable for curved structures such as thin-walled parts and blades. Hexahedrons are the primary mesh element type, and mesh refinement can be performed in contact areas and stress concentration areas, reducing the mesh size to less than 1 / 5 to 1 / 3 of the minimum contact feature size (e.g., gap value). This is for example only and is not intended to be limiting.

[0072] Step S2012, setting the excitation and boundary conditions of the rotor-stator model, setting corresponding material properties for each independent component of the rotor-stator, and obtaining a finite element model of the rotor-stator.

[0073] Specifically, the rotor and stator are treated as independent components, and the contact interface (e.g., rotor-stator mating surface) is defined to facilitate subsequent contact pair configuration. Setting material properties includes setting parameters such as elastic modulus, Poisson's ratio, density, and thermal expansion coefficient for the rotor (e.g., alloy steel) and stator (e.g., high-temperature alloy), respectively.

[0074] The excitation can be automatically set by setting the operating conditions of the gas turbine. For example, thermal expansion lag may cause initial friction excitation of the rotor and stator; the boundary conditions are equivalent to the initial state of the gas turbine, including the installation position and installation direction of the gas turbine, the definition of the gap between the rotor and the stator, the contact stiffness, the friction coefficient, etc., which are only used as examples, but are not limited to this.

[0075] The rotor-stator clearance analysis method for gas turbines provided in this embodiment uses hexahedral meshes to divide the rotor-stator model, which can significantly improve the mesh quality and calculation accuracy, reduce numerical diffusion and pseudo-diffusion errors, independently set the excitation and boundary conditions of each rotor-stator component, and truly simulate the interaction between components. Different components (such as rotor shaft and stator housing) are given real material properties (such as elastic modulus and density), making the model closer to actual physical properties, ensuring the validity of results such as modal analysis and fatigue life prediction, and providing a scientific basis for structural optimization and fault diagnosis.

[0076] Step S202 : performing deformation analysis on the rotor-stator finite element model to determine whether rubbing occurs between the rotors and stators.

[0077] Specifically, the above step S202 includes:

[0078] Step S2021 , setting the contact attribute parameters, contact stress parameters and node coordinate parameters of each rotor-stator, and calculating the contact stress between each rotor-stator and the node coordinates of each rotor-stator.

[0079] Specifically, the deformation analysis software sets the contact attribute parameters, contact stress parameters, and the node coordinate parameters of each rotor and stator. Through the deformation analysis software's automatic analysis, the corresponding values ​​of each parameter are directly calculated. The contact attribute parameters are used to identify pairs of rotor and stator nodes that may be in contact. By setting the contact attributes between the rotor and stator, the contact stress between them can be automatically calculated. This contact stress can then be used to determine whether friction between the rotor and stator occurs.

[0080] Step S2022: If the contact stress between the rotors and stators is 0, no friction occurs between the rotors and stators.

[0081] Step S2023: If at least one of the contact stresses between the rotors and stators is not zero, friction occurs between the rotors and stators.

[0082] Specifically, when no rubbing occurs, the contact stress between the rotors and stators is zero. Therefore, if the contact stress between the rotors and stators is all zero, no rubbing occurs between the rotors and stators. If at least one of the contact stresses between the rotors and stators is not zero, rubbing occurs between the rotors and stators, causing a malfunction in the gas turbine and preventing normal operation.

[0083] The rotor-stator clearance analysis method for gas turbines provided in this embodiment accurately captures the microscopic interaction between the rotor and the stator by setting contact properties and contact stress parameters and combining node coordinate data. The contact stress value directly reflects the intensity of collision or friction, and the change in node coordinates reveals the deformation trend, providing an objective quantitative basis for rubbing judgment. Based on the criterion of whether the contact stress is zero, it can quickly and accurately distinguish whether the rotor and the stator are rubbing without the need for complex experiments. The method is suitable for dynamic operating condition analysis of high-speed rotating machinery and provides early warning of potential faults.

[0084] In some optional embodiments, if friction occurs between the rotors and stators, the method further includes:

[0085] According to the calculation results of the contact stress, the coordinates of the rubbing node corresponding to the contact stress not being 0 are determined as the position of the rotor-stator node where the rubbing occurs.

[0086] Specifically, if a friction collision occurs, the node number of the rotor-stator where the friction collision occurs is automatically output. By querying the node number of the rotor-stator where the friction collision occurs in the finite element software, the friction node coordinates of the rotor-stator friction collision can be intuitively observed, and the position of the rotor-stator node where the friction collision occurs can be accurately determined based on the friction node coordinates.

[0087] It should be noted that if Figure 4 The flowchart for judging the friction between the rotor and stator is shown in FIG. 4 . The friction between the rotor and stator can be determined by calculating all contact stresses between the rotor and stator and judging whether the maximum contact stress is 0. If the maximum contact stress is not 0, the gas turbine has friction. At this time, the minimum gap is 0 and the node number of the rotor and stator where the collision occurred is output; if the maximum contact stress is 0, the gas turbine has not friction.

[0088] The rotor-stator clearance analysis method for gas turbines provided in this embodiment accurately locks the coordinates of the rubbing nodes through contact stress calculation, directly locates the specific position of abnormal contact between the rotor and stator, avoids the blindness of traditional troubleshooting, and quickly identifies the rubbing "hot spot" area in a data-driven manner, providing precise targets for structural improvement and reducing trial and error costs.

[0089] Step S203 : if no rubbing occurs between the rotors and stators, the node coordinates of the rotors and stators are obtained based on the rotor-stator finite element model, and the gaps between the rotors and stators are determined according to the node coordinates of the rotors and stators.

[0090] Specifically, the above step S203 includes:

[0091] Step S2031 : performing deformation analysis on the rotor-stator finite element model to obtain the node coordinates of each rotor-stator.

[0092] Specifically, if no collisions occur between the rotors and stators, the nodal coordinates of each rotor and stator are obtained using finite element software. The nodal coordinates of each rotor and stator are the coordinates of each node in the global coordinate system. Eliminating the possibility of rotor-stator rubbing can avoid interference between the rotors and stators during the subsequent calculation of the rotor-stator clearance, allowing the data processing results to better reflect the operating status of the gas turbine, thereby better guiding subsequent installation and adjustment work or the design of vibration isolation devices.

[0093] Step S2032: Acquire the target node of the target rotor, and determine the range to be studied and the stator nodes within the range to be studied according to the target node.

[0094] Specifically, for each target node on the rotor, the scope to be studied and the stator nodes within the scope to be studied are determined according to the position of the target node. For example, the rotor blade tip is the target node, and the rotor blade tip at each level and the inner surface of the casing of the corresponding rotor with an axial width of three times are taken as the scope to be studied. The grid within the scope to be studied is encrypted. The local grid encryption makes the finite element analysis results more accurate, improves the accuracy of the subsequent rotor-stator clearance calculation, and avoids the waste of computing resources. Only the contact properties are set between the rotor blade tip nodes at each level and the stator nodes of the corresponding inner surface of the casing with an axial width of three times, and the contact stress and node coordinates of the corresponding nodes are output. Analyzing the inner surface of the casing with an axial width of three times the corresponding rotor at each level can ensure that the rotor-stator friction and the minimum rotor-stator clearance will not be lost, and at the same time, avoid the interference of redundant node data during data post-processing.

[0095] Step S2033: Calculate the straight-line distance between each stator node and the target node as the gap between the target rotor and each stator.

[0096] Specifically, the straight-line distance between the stator node and the target node of the rotor within the range to be studied is calculated as the gap between the target rotor and each stator. The calculation formula is as follows:

[0097]

[0098] Among them, (x1, y1, z1) represents the coordinates of the static node, (x2, y2, z2) represents the coordinates of the target node, and d represents the straight-line distance between the target node and the static node.

[0099] The rotor-stator clearance analysis method for gas turbines provided in this embodiment obtains node coordinates and quantifies the clearance through deformation analysis, accurately depicts the spatial position relationship between the rotor and the stator, defines the research scope based on the target node and calculates the straight-line distance between the stator node and the target node within the research scope, converts the abstract clearance into a measurable physical quantity, and quickly locates the key clearance areas (such as blade tip clearance and shaft seal clearance), providing data support for evaluating assembly accuracy and the influence of thermal deformation.

[0100] Step S204: determining the minimum rotor-stator gap and the corresponding rotor-stator node coordinates according to the gaps between the rotors and stators.

[0101] Specifically, the above step S204 includes:

[0102] Step S2041 , obtaining node coordinate data of rotors at all levels within a preset time period according to a preset sampling period, and importing the node coordinate data into the stator node array and the rotor node array.

[0103] Specifically, the node coordinate data of each rotor stage is obtained according to a preset sampling period. The preset time period may be a period of time during which the gas turbine continuously operates under preset operating conditions. Acquiring data according to the operating conditions allows for targeted analysis of the characteristics of the rotor and stator.

[0104] The rotor node coordinate data obtained at the i-th sampling moment is imported into the rotor node array zhuanzi, and the stator node coordinate data obtained at the i-th sampling moment is imported into the stator node array jingzi.

[0105] Step S2042 , for each level of target rotors, traverse each rotor node in the target rotor, and calculate the minimum gap of the target nodes in the target rotor at the same sampling time.

[0106] Step S2043, compare the minimum gaps of the target nodes in the target rotor, take the smallest minimum gap as the minimum rotor-stator gap of the target rotor, and the rotor node coordinates and stator node coordinates corresponding to the minimum rotor-stator gap are the corresponding rotor-stator node coordinates.

[0107] Specifically, if Figure 4 In the process of calculating the rotor-stator clearance, for each target rotor level, the rotor node array is traversed and the minimum clearance between the target node and each stator node in the corresponding study range is calculated at the same sampling time. The minimum rotor-stator clearance and the corresponding rotor-stator node number of the j-th target rotor at the i-th sampling time are further compared.

[0108] Repeat the above steps S2042 to S2043 for each level of target rotors to obtain the minimum rotor-stator clearance and the corresponding rotor-stator node number of each level of target rotors at the i-th moment.

[0109] In some optional embodiments, the method further comprises:

[0110] Step S2044 , based on the minimum rotor-stator clearance of each target rotor at each sampling moment, a minimum rotor-stator clearance variation curve of each target rotor within a preset time period is drawn.

[0111] Specifically, for each level of target rotors, the minimum rotor-stator clearance at each sampling moment within a preset time period is calculated, and a minimum rotor-stator clearance change curve of the target rotor is drawn based on the sampling moment and the corresponding minimum rotor-stator clearance, with the horizontal axis being the sampling moment and the vertical axis being the minimum rotor-stator clearance corresponding to the target rotor.

[0112] Step S2045: Analyze the actual working state of the gas turbine according to the minimum rotor-stator clearance variation curve.

[0113] Specifically, the minimum rotor-stator clearance variation curve intuitively reflects the dynamic relationship between key components in the operation of the gas turbine, and its actual working status can be analyzed from the following dimensions, which is only used as an example but not limited to this.

[0114] (1) During the startup and shutdown phases, if the curve shows that the gap decreases rapidly and then rebounds, it may be due to asynchronous thermal expansion of the rotor and stator; if the gap fluctuates abnormally or is continuously lower than the safety threshold, it indicates the risk of rubbing, and the assembly accuracy or material thermal expansion coefficient setting needs to be checked.

[0115] (2) During steady-state operation, if the curve has periodic fluctuations, it may be caused by air flow pulsation, rotor imbalance or bearing vibration; if the gap continues to decrease, be alert to component creep, thermal deformation accumulation or foreign object damage, and the source of the fault can be located by combining vibration spectrum and temperature data.

[0116] (3) Under variable load conditions, the response delay or mutation of the clearance curve reflects the matching degree of the rotor-stator stiffness and thermal conductivity characteristics. For example, the response lag may be due to slow cooling of the casing, while the mutation may be caused by airflow excitation.

[0117] This embodiment provides a method for analyzing rotor-stator clearance for gas turbines. Through periodic data collection and precise calculation, it dynamically tracks and visualizes the minimum rotor-stator clearance. Node data is stored in a structured manner, allowing efficient traversal and calculation of minimum clearances, accurately locating hazardous areas. The minimum clearance variation curve intuitively reflects clearance fluctuations during gas turbine operation, enabling engineers to promptly identify operating conditions such as friction risks and abnormal vibrations. This provides strong data support for optimizing maintenance strategies, extending equipment life, and ensuring safe and stable unit operation.

[0118] This embodiment also provides a rotor-stator clearance analysis device for a gas turbine. This device is used to implement the above-mentioned embodiments and preferred implementations. Details already described will not be repeated here. As used below, the term "module" may refer to a combination of software and / or hardware that implements a predetermined function. Although the devices described in the following embodiments are preferably implemented in software, implementation using hardware, or a combination of software and hardware, is also possible and contemplated.

[0119] This embodiment provides a rotor-stator clearance analysis device for a gas turbine, such as Figure 5 As shown, including:

[0120] The finite element model building module 501 is used to obtain a rotor-stator model of a target gas turbine and preprocess the rotor-stator model to obtain a rotor-stator finite element model.

[0121] The rubbing judgment module 502 is used to perform deformation analysis on the rotor-stator finite element model to determine whether rubbing occurs between the rotors and stators.

[0122] The gap calculation module 503 is used to obtain the node coordinates of each rotor-stator based on the rotor-stator finite element model if no friction occurs between the rotors and stators, and determine the gap between the rotors and stators according to the node coordinates of the rotors and stators.

[0123] The minimum rotor-stator clearance analysis module 504 is used to determine the minimum rotor-stator clearance and the corresponding rotor-stator node coordinates according to the clearances between the rotors and stators.

[0124] In some optional implementations, the finite element model building module 501 includes:

[0125] The mesh division unit is used to perform geometric mesh division on the rotor-stator model and discretize it into mesh units.

[0126] The model parameter setting unit is used to set the excitation and boundary conditions of the rotor-stator model, set the corresponding material properties for each independent component of the rotor-stator, and obtain the rotor-stator finite element model.

[0127] In some optional implementations, the rubbing determination module 502 includes:

[0128] The parameter setting and calculation unit is used to set the contact property parameters, contact stress parameters and node coordinate parameters of each rotor-stator, and calculate the contact stress between each rotor-stator and the node coordinates of each rotor-stator.

[0129] The first rubbing judgment unit is configured to determine that no rubbing occurs between the rotors and stators if the contact stresses between the rotors and stators are both 0.

[0130] The second rubbing judgment unit is configured to determine that rubbing occurs between the rotors and stators if at least one of the contact stresses between the rotors and stators is not zero.

[0131] In some optional implementations, the gap calculation module 503 includes:

[0132] The node coordinate determining unit is used to obtain the node coordinates of each rotor and stator based on deformation analysis of the rotor and stator finite element model.

[0133] The research target determination unit is used to obtain the target node of the target rotor and determine the range to be studied and the stator node within the range to be studied according to the target node.

[0134] The gap calculation unit is used to calculate the straight-line distance between each stator node and the target node as the gap between the target rotor and each stator.

[0135] In some optional implementations, the minimum rotor-stator clearance analysis module 504 includes:

[0136] The node coordinate acquisition unit is used to obtain the node coordinate data of each level of rotor within a preset time period according to a preset sampling period, and import the node coordinate data into the stator node array and the rotor node array.

[0137] The minimum gap determination unit is used to traverse each rotor node in the target rotor for each level of target rotor and calculate the minimum gap of the target node in the target rotor at the same sampling time.

[0138] The minimum rotor-stator clearance determination unit is used to compare the minimum clearances of each target node in the target rotor, take the smallest minimum clearance as the minimum rotor-stator clearance of the target rotor, and the rotor node coordinates and stator node coordinates corresponding to the minimum rotor-stator clearance are the corresponding rotor-stator node coordinates.

[0139] In some optional embodiments, the method further comprises:

[0140] The curve drawing unit is used to draw the minimum rotor-stator clearance change curve of each target rotor in a preset time period according to the minimum rotor-stator clearance of each target rotor at each sampling moment.

[0141] The state analysis unit is used to analyze the actual working state of the gas turbine according to the minimum rotor-stator clearance change curve.

[0142] The further functional description of each of the above modules and units is the same as that of the above corresponding embodiments and will not be repeated here.

[0143] The rotor-stator clearance analysis device for gas turbines in this embodiment is presented in the form of a functional unit, where the unit refers to an ASIC (Application Specific Integrated Circuit) circuit, a processor and memory that executes one or more software or fixed programs, and / or other devices that can provide the above functions.

[0144] The embodiment of the present invention also provides a computer device having the above Figure 5 The rotor-stator clearance analysis device for a gas turbine is shown.

[0145] See also Figure 6 , Figure 6 is a structural diagram of a computer device provided by an optional embodiment of the present invention, such as Figure 6 As shown, the computer device includes: one or more processors 10, memory 20, and interfaces for connecting various components, including high-speed interfaces and low-speed interfaces. Various components utilize different buses to communicate with each other and can be installed on a common mainboard or installed in other ways as needed. The processor can process the instructions executed in the computer device, including instructions stored in the memory or on the memory to display the graphical information of the GUI on an external input / output device (such as, a display device coupled to the interface). In some optional embodiments, if necessary, multiple processors and / or multiple buses can be used together with multiple memories and multiple memories. Equally, multiple computer devices can be connected, and each device provides part of the necessary operations (for example, as a server array, a group of blade servers, or a multi-processor system). Figure 6 A processor 10 is taken as an example.

[0146] The processor 10 may be a central processing unit, a network processor, or a combination thereof. The processor 10 may further include a hardware chip. The hardware chip may be an application-specific integrated circuit, a programmable logic device, or a combination thereof. The programmable logic device may be a complex programmable logic device, a field programmable gate array, a general purpose array logic, or any combination thereof.

[0147] The memory 20 stores instructions that can be executed by at least one processor 10, so that the at least one processor 10 executes the method shown in the above embodiment.

[0148] The memory 20 may include a program storage area and a data storage area, wherein the program storage area may store an operating system and application programs required for at least one function; the data storage area may store data created based on the use of the computer device, etc. In addition, the memory 20 may include a high-speed random access memory, and may also include a non-transient memory, such as at least one disk storage device, a flash memory device, or other non-transient solid-state storage device. In some optional embodiments, the memory 20 may optionally include a memory remotely located relative to the processor 10, and these remote memories may be connected to the computer device via a network. Examples of the above-mentioned network include, but are not limited to, the Internet, an intranet, a local area network, a mobile communication network, and combinations thereof.

[0149] The memory 20 may include a volatile memory, such as a random access memory; the memory may also include a non-volatile memory, such as a flash memory, a hard disk or a solid-state drive; the memory 20 may also include a combination of the above types of memory.

[0150] The computer device further includes a communication interface 30 for the computer device to communicate with other devices or a communication network.

[0151] The embodiment of the present invention also provides a computer-readable storage medium. The above-mentioned method according to the embodiment of the present invention can be implemented in hardware, firmware, or implemented as a computer code that can be recorded in a storage medium, or implemented as a computer code that is originally stored in a remote storage medium or a non-temporary machine-readable storage medium and downloaded through a network and will be stored in a local storage medium, so that the method described herein can be stored in such software processing on a storage medium using a general-purpose computer, a dedicated processor, or programmable or dedicated hardware. Among them, the storage medium can be a magnetic disk, an optical disk, a read-only storage memory, a random access memory, a flash memory, a hard disk or a solid-state drive, etc.; further, the storage medium can also include a combination of the above-mentioned types of memory. It can be understood that a computer, a processor, a microprocessor controller or programmable hardware includes a storage component that can store or receive software or computer code. When the software or computer code is accessed and executed by a computer, a processor or hardware, the method shown in the above embodiment is implemented.

[0152] Although the embodiments of the present invention have been described with reference to the accompanying drawings, those skilled in the art may make various modifications and variations without departing from the spirit and scope of the present invention. Such modifications and variations are all within the scope defined by the appended claims.

Claims

1. A method for analyzing rotor-stator clearance of a gas turbine, characterized in that: The method comprises: Obtaining a rotor-stator model of a target gas turbine, and preprocessing the rotor-stator model to obtain a rotor-stator finite element model; Performing deformation analysis on the rotor-stator finite element model to determine whether friction occurs between the rotors and stators; If no friction occurs between the rotors and stators, obtaining the node coordinates of each rotor and stator based on the rotor and stator finite element model, and determining the gap between the rotor and stator according to the node coordinates of the rotor and stator; The minimum rotor-stator gap and the corresponding rotor-stator node coordinates are determined according to the gaps between the rotors and stators.

2. The method according to claim 1, characterized in that The rotor-stator model is preprocessed to obtain a rotor-stator finite element model, including: Performing geometric mesh division on the rotor-stator model to discretize into mesh units; The excitation and boundary conditions of the rotor-stator model are set, and corresponding material properties are set for each independent component of the rotor-stator to obtain a rotor-stator finite element model.

3. The method according to claim 1, characterized in that Performing deformation analysis on the rotor-stator finite element model to determine whether rubbing occurs between the rotor and the stator includes: Set the contact property parameters, contact stress parameters and node coordinate parameters of each rotor-stator, and calculate the contact stress between each rotor-stator and the node coordinates of each rotor-stator; If the contact stress between the rotors and stators is 0, there is no friction between the rotors and stators. If at least one of the contact stresses between the rotors and stators is not zero, friction occurs between the rotors and stators.

4. The method according to claim 3, characterized in that If friction occurs between the rotors and stators, the method further includes: According to the calculation results of the contact stress, the coordinates of the rubbing node corresponding to the contact stress not being 0 are determined as the position of the rotor-stator node where the rubbing occurs.

5. The method according to claim 1, wherein Acquiring the node coordinates of each rotor-stator based on the rotor-stator finite element model, and determining the gap between each rotor-stator according to the node coordinates of the rotor-stator, including: Based on the deformation analysis of the rotor-stator finite element model, the node coordinates of each rotor-stator are obtained; Obtaining a target node of a target rotor, and determining a to-be-studied range and a stator node within the to-be-studied range according to the target node; The straight-line distance between each stator node and the target node is calculated as the gap between the target rotor and each stator.

6. The method according to claim 1, characterized in that The minimum rotor-stator gap and the corresponding rotor-stator node coordinates are determined according to the gaps between the rotors and stators, including: Acquire node coordinate data of rotors at all levels within a preset time period according to a preset sampling period, and import the node coordinate data into the stator node array and the rotor node array; For each level of target rotor, traverse each rotor node in the target rotor and calculate the minimum gap of the target nodes in the target rotor at the same sampling time; Compare the minimum gaps of each target node in the target rotor, take the smallest minimum gap as the minimum rotor-stator gap of the target rotor, and the rotor node coordinates and stator node coordinates corresponding to the minimum rotor-stator gap are the corresponding rotor-stator node coordinates.

7. The method according to claim 6, characterized in that The method further comprises: According to the minimum rotor-stator clearance of each target rotor at each sampling moment, a minimum rotor-stator clearance change curve of each target rotor within a preset time period is drawn; The actual working state of the gas turbine is analyzed according to the minimum rotor-stator clearance variation curve.

8. A rotor-stator clearance analysis device for a gas turbine, characterized in that: The device comprises: a finite element model building module, configured to obtain a rotor-stator model of a target gas turbine and preprocess the rotor-stator model to obtain a rotor-stator finite element model; a rubbing judgment module, configured to perform deformation analysis on the rotor-stator finite element model to determine whether rubbing occurs between the rotors and stators; a gap calculation module for obtaining the node coordinates of each rotor-stator based on the rotor-stator finite element model if no friction occurs between the rotor-stator and determining the gap between the rotor-stator according to the node coordinates of the rotor-stator; The minimum rotor-stator clearance analysis module is used to determine the minimum rotor-stator clearance and the corresponding rotor-stator node coordinates based on the clearances between the rotors and stators.

9. A computer device, characterized in that: include: A memory and a processor, wherein the memory and the processor are communicatively connected to each other, the memory stores computer instructions, and the processor executes the method according to any one of claims 1 to 7 by executing the computer instructions.

10. A computer-readable storage medium, characterized in that The computer-readable storage medium stores computer instructions, and the computer instructions are used to enable a computer to execute the method according to any one of claims 1 to 7.

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