CN104376157A - Shafting dynamic and static characteristic analysis calculating system of large steam turbine generator unit - Google Patents

Abstract

The invention relates to a shafting dynamic and static characteristic analysis calculating system of a large steam turbine generator unit to solve the problems that an existing computing system is low in computing result precision and working efficiency. The system comprises a modeling module used for establishing a rotor mechanical model; a bearing analysis module used for calling data of the rotor mechanical model of the modeling module and bearing loads and elevation data of a static analysis module, calculating steady state data and the dynamics coefficient of a bearing and storing the dynamics coefficient; a dynamic analysis module used for calling the data of the rotor mechanical model of the modeling module, the shaft load data of the static analysis module and the dynamics coefficient of the bearing analysis module and analyzing the critical rotating speed and the unbalanced response of a rotor and the rotor stability; the static analysis module used for calling the data of the rotor mechanical model of the modeling module and carrying out front calculation through the bearing analysis module and the dynamic analysis module. The shafting dynamic and static characteristic analysis calculating system is applied to the field of large turbines.

Description

Large turbine-generator set axle system static and dynamic performance analytical calculation system

Technical field

The present invention relates to steam-electric generating set shafting static and dynamic performance analytical calculation system.

Background technology

Prior art Problems existing: be still in blank about turbine shafting dynamical property analysis software field at home, main cause is: for simple rotor-support-foundation system greatly mainly with based on classical rotor dynamic theory, rotator model is simplified on a large scale, and therefore computational solution precision is lower; Because the program thread of computational analysis personnel is different, similar software lacks relevant industries standard, accuracy and counting yield uneven; In addition, software integration degree is lower, can only for a kind of type or a kind of compute type, and operation interface often more complicated is abstract, be difficult to realization and increase work efficiency and widespread adoption.For the rotor-support-foundation system of complexity, domesticly also lack corresponding computing method, the software of exploitation can not meet the dynamics calculation analysis of the type rotor-support-foundation system substantially, the technical support therefore usually will be correlated with by Abroad Turbine manufacturer or apply external business software and carry out computational analysis.Although the external business software such as ANSYS and SAMCEF ROTOR can the sound state dynamics of calculation of complex steam-electric generating set shafting, and computational accuracy and counting yield higher, but lack engineering parameter and the empirical parameter of Steam Turbine rotor axial system in the type software, and relevant interface and the loading mode of these parameters are not set, there is very large difficulty in secondary development, software lacks specific aim to turbine rotor, and lacks corresponding industry standard and pass judgment on result of calculation.

Summary of the invention

The present invention will solve lower, the ineffective problem of existing computing system computational solution precision, and provides large turbine-generator set axle system static and dynamic performance analytical calculation system.

Large turbine-generator set axle system static and dynamic performance analytical calculation system, it comprises:

For setting up the MBM of rotor dynamics model;

For bearing load and the elevation data of the rotor dynamics model data and static analysis module of calling MBM, then according to Reynolds equation calculation bearing at the steady state data waited in gentle alternating temperature situation and kinetic coefficient, and store the bearing analysis module of kinetic coefficient;

For calling the kinetic coefficient of the rotor dynamics model data of MBM, the axle load data of static analysis module and bearing analysis module, to the performance analysis module that the critical rotary speed of rotor, unbalance response and rotor stability are analyzed;

Rotor dynamics model data for calling MBM to carry out the static analysis module of preposition calculating by bearing analysis module and performance analysis module.

Invention effect:

RDC system is introduced substantially:

Large turbine-generator set axle system static and dynamic performance analytical calculation system full name Rotor Dynamics Calculation (RDC), be a single user single task rotor dynamics analytical calculation system run based on X86 platform general-purpose system, be mainly used in carrying out various operating characteristic calculating, checking and emulation to large turbine-generator set.RDC system has Graph Control interface and convenient, flexible mode of operation intuitively, can carry out global function computer sim-ulation on the various PC meeting system requirements.

This system can be carried out various based on linear, that Nonlinear Rotor Dynamics is theoretical numerical analysis for institute's Modling model, calculation result data both can be checked with the form such as figure, data form immediately, also can preserve by the form such as text and picture.The simulation result of native system is true and reliable, as the important evidence of actual production and design, can substantially go for the actual production design requirement of existing each enterprise.

(1) commercialization degree is high

First, the input data of software to user have made considered critical, and devise a large amount of fault tolerance and collapse to prevent software faults, fundamentally ensure the reliably complete of running software.Software performance, through strict test, the computer platform meeting service requirement normally can carry out simulation calculating completely.Preset development interface in software development process simultaneously, is convenient to the expansion of software subsequent upgrade, and provides abundant comprehensive help function, thus assisting users uses and learning software.

(2) software function is comprehensive

This software according to theoretical result be the ripe theoretical result that a large amount of practical proof has been passed through in rotor dynamics field, use for reference a large amount of engineering parameters of the international well-known turbine making business of Liao Xiwudeng at Balancing of Steam Turbine Shaft design aspect, simulation result is true and reliable, can as the important evidence of actual production and design.Simultaneously, the built-in numerous Steam Turbine rotor-bearing structure type of software modeling function, can carry out rapid modeling to various actual set structure; And software computing function contains the various calculating about unit important safety substantially, as static analysis, bearing analysis, performance analysis etc., there is the important calculation function concerning set steady such as critical rotary speed, unbalance response, stability analysis simultaneously, and devise special specific aim computing module for plain bearing bearing and tilting-pad bearing.Substantially the actual production design requirement of existing each enterprise is gone for.

(3) operation interface is friendly

This software relies on Qt development platform, draws the mature experience of similar software on software interface and Design Mode simultaneously.Relative to domestic similar software, this software has the operation interface of height hommization, and functional module divides rationally simultaneously, and menu area arrangement science, meets Human Engineering Principle.Redundant operation when substantially reducing the learning cycle of software users and decrease use, substantially increases running software and service efficiency.

Succeeding in developing of RDC software, has filled up the domestic blank waiting the software development of rotating machinery power design field in the calculating of turbine shafting dynamics and analysis.Along with the further genralrlization of RDC software application, the interpolation of software follow-up function and the development of correlation theory level, this software will play vital effect to improving the be correlated with design level of manufacturing enterprise and scientific research institution and research and development ability of steam turbine, and final in engineering reality in occupation of the status become more and more important.

Accompanying drawing explanation

Fig. 1 is the RDC system basic block diagram in embodiment one;

Fig. 2 is system module composition and data dependence relation figure in embodiment one;

Fig. 3 is structured flowchart and the intermodular data dependence schematic diagram of RDC system in embodiment one;

Fig. 4 calculates process control system process flow diagram in embodiment one;

Fig. 5 is MBM node region and corresponding state in embodiment two; Wherein, A is normal node, and B is the node revised, and C is the node of mouse-pointing, and D is the node chosen;

Fig. 6 is self-defined material classification editing interface figure in embodiment two;

Fig. 7 is static analysis functions of modules structural drawing in embodiment three;

Fig. 8 is gravity amount of deflection result of calculation in embodiment six;

Fig. 9 is single-span shaft part gravity sag curve figure in embodiment six;

Figure 10 is plus load computing function menu structure figure in embodiment six;

Figure 11 is embodiment six centre bearer analysis module functional structure chart;

Figure 12 arranges bearing analytical calculation speed diagram in embodiment seven;

Figure 13 is performance analysis functions of modules structural drawing in embodiment eight;

Figure 14 is critical rotary speed result data dependence graph in embodiment eight;

Figure 15 is unbalance response result data dependence graph in embodiment eight;

Figure 16 is unbalance responses parameter design surface chart in embodiment six;

Figure 17 is supplemental functionality and core calculations functional relationship figure in embodiment eight;

Figure 18 is software major interfaces block plan in embodiment eight.

Embodiment

Embodiment one: the RDC system basic block diagram of present embodiment as shown in Figure 1: large turbine-generator set axle system static and dynamic performance analytical calculation system, it comprises:

For setting up the MBM of rotor dynamics model;

For bearing load and the elevation data of the rotor dynamics model data and static analysis module of calling MBM, then according to Reynolds equation calculation bearing at the steady state data waited in gentle alternating temperature situation and kinetic coefficient, and store the bearing analysis module of kinetic coefficient;

For calling the kinetic coefficient of the rotor dynamics model data of MBM, the axle load data of static analysis module and bearing analysis module, to the performance analysis module that the critical rotary speed of rotor, unbalance response and rotor stability are analyzed;

Rotor dynamics model data for calling MBM to carry out the static analysis module of preposition calculating by bearing analysis module and performance analysis module.

First at user application layer, the architectural feature of rotor-support-foundation system is converted into mechanical model by software users, be input in computing machine by MBM, material properties by model attributes editing machine by the geometric properties of rotor-support-foundation system, the model data of input and attribute pass through running state monitoring device Real-time Feedback to software users; At data interaction layer, the data file transition in MBM and model attributes editing machine is binary data file by computing machine, form computerese, and to be stored into suffix is in the unit model file of .in; At core calculations layer, computing machine identifies unit model file, imports to nucleus module solver and carries out Mechanics Calculation, and store data result of calculation; Then get back to data interaction layer and calculation result data is compiled as decimal data by scale-of-two, be stored in .txt file; Finally turn back to user application layer .txt result of calculation file is imported in result of calculation reader, is supplied to software users;

RDC system reaches the target that the complex software programming techniques such as memory-mapped reach by binary data format, therefore this system adopts three-decker, be respectively user application layer, data interaction layer, core calculations layer three level, highly encapsulate between each level, only retain necessary interactive interface;

System module composition and data dependence relation figure be as shown in Figure 2: RDC system develop can for maximum by 1000 shaft parts, 20 bearing composition Large steam turbine wheel-bearing arrangements carry out Modelling and calculation, model file can repeatedly be edited by RDC program visualization editing interface and be revised parameters, because system algorithm exists front and back and data relationship, various functions module distribution and data dependence relation are as shown in Figure 2;

Certain data dependence relation is there is between each several part computing function in RDC program computation process, namely a kind of operation of computing result of calculation of needing another kind of computing to draw is as input data, therefore establish system cloud gray model order and the data dependence relation of complete set between whole system modules and function, each intermodule master data dependence as shown in Figure 3; What RDC system adopted is Interactive Visualization menu structure, all functions menu categories is also arranged in System menu structure, user can call arbitrarily a certain function, if therefore user calls computing function not in accordance with flow sequence, certainly will cause that calculating cannot be carried out, erroneous results or system crash.Therefore this system is built-in, and a set of process control system monitors computing flow process, and provides reasonable prompting to the illegal operation of user, thus instructs user according to the computing of reasonable operational scheme completion system, and this machine-processed operational flow diagram as shown in Figure 4;

(1) when user has computation requirement, computing function starts, if master mould file is not modified, then carries out selecting whether to carry out prefix operation, if revise master mould file, then resets all calculating, then carries out selecting whether to carry out prefix operation;

(2) prefix operation needs to vibrate concrete computing module, and such as calculating gravity deflection degree of disturbing then does not need preposition calculating, and other computing all needs to carry out prefix operation.If desired carry out prefix operation then will consider, whether this computing is carried out, if carry out, then enters next step flow process, if do not carry out, then operates according to prefix operation prompting, and enters next step flow process;

(3) after prefix operation, user starts to calculate according to demand, and first software can copy data and back up, and then calls bottom calculation procedure RDC.dll and calculate targetedly, net result copy backup is derived, terminates whole calculation process.

Embodiment two: present embodiment and embodiment one unlike: described rotor dynamics model is the rotor dynamics model by equivalent stiffness diameter and shaft part quality being carried out the method establishment of building block splicing.

After newly-built process starts, system provides one to give tacit consent to shaft part, and user is to give tacit consent to shaft part for starting point is by setting up complete rotor dynamics model with the operation adding new shaft part or bearing backward forward.

The modelling operability of RDC system rotor model completes alternately primarily of RDC system main INTERFACE MODEL editor viewing area, RDC system main interface property editing machine two parts.In modelling operability process, except above two regions, the basic operation for model shaft part also needs the operation on modeling tool hurdle in menu bar to coordinate.

Indicate the different conditions residing for it, thus indicating user completes modelling operability.Four kinds of shaft parts contrast with responsive state and refer to Fig. 5.

In rotator model modeling process, the material type of shaft part (or claim rotator model unit) be that MBM must support one of characteristic, therefore on the basis of shaft part attribute Editor, additionally develop again special material properties check editing interface, user can be called by software master menu hurdle, as shown in Figure 6.

This interface not only intuitively shows the various physical characteristicss of the Steam Turbine common used material that RDC software is supported, as elastic modulus, modulus of shearing, density etc., more supports user manually to input above physical characteristics thus adds new material and participate in calculating.User add new material and successfully preserve after, shaft part material just can be arranged to self-defined material by user in shaft part attribute Editor.

Other step and parameter identical with embodiment one.

Embodiment three: what present embodiment and embodiment one or two comprised equivalent model unlike: described MBM sets up submodule, load and boundary condition submodule and Data Format Transform submodule;

Described equivalent model set up submodule for the geometric model of rotor is carried out modelling with the form of each shaft part length of rotor and rigidity diameter, be converted into mechanical model, each shaft part is linked together by the form of being spliced by building block, build up whole roots rotor, and material properties is assigned to mechanical model and determines position of bearings and bearing size;

Wherein, the rigidity diameter in described equivalent model is applied 45 ° of methods and is calculated, and the concrete steps of the method are:

(1) the 45 ° lines tangent with leading circle are drawn at the variant positions of rotating shaft and impeller;

Article (2) two, it is a line segment that 45 ° of crossing line intersection points link with axisymmetric 45 ° of crossing line intersection points, if its length is DINT;

(3) arithmetic average diameter DAVE, formula is: DAVE1=(D1+DINT)/2, DAVE2=(D2+DINT)/2, in formula, DAVE1 is first paragraph mean diameter, DAVE2 is second segment mean diameter, and D1 represents impeller front rotary shaft diameter, rotating shaft diameter after D2 impeller;

(4) effective moment of inertia is calculated, formula: LEFF1=((I1+IINT)/2+IAVE1)/2, LEFF2=((I2+IINT)/2+IAVE2)/2, I1 represents impeller front rotary shaft moment of inertia, I2 represents rotating shaft moment of inertia after impeller, IINT represents 45 ° of intersection cross sectional moment of inertias, and IAVE1 represents mean diameter DAVE1 cross sectional moment of inertia, and IAVE2 represents mean diameter DAVE2 cross sectional moment of inertia;

(5) equivalent stiffness diameter is calculated: DEFF1=((64) (IEFF1)/π) ^0.25, DEFF2=((64) (IEFF2)/π) ^0.25;

The mechanical model of rotor utilizes transfer matrix method to form by a series of equivalent stiffness diameter and each section of shaft length;

Described load and boundary condition submodule are used for out-of-balance force and partial admission's load applying to determine bearing seat, bearing and the rotor boundary condition in axle journal position to certain or some shaft part positions;

Described Data Format Transform submodule is for storing the model data of the rotor of input and bearing, material properties, load and boundary condition with numerical tabular form and exporting, for browsing at any time and subsequent calculations analysis.

Described equivalent model set up initial as system works of module, namely before doing various mechanical analysis, first by the module of setting up of equivalent model, external geometric model to be converted into computerese input; Load and boundary condition module are after establishing model, apply special process a certain of model or some position, the load that next equivalent rotor bears in Practical Project and boundary condition; Inputted data, when model building module and the work of load boundary condition module, synchronously transform and store by data layout conversion module.

That first will apply equivalent model sets up submodule to set up the mechanical model of rotor, then the load suffered by rotor and boundary condition are applied in rotor dynamics model by application load and boundary condition submodule, and rotor dynamics model, load and boundary condition are converted to data format file by last application data format conversion submodule.

In this module, the boundary condition of rotor is set to: cantilever end boundary condition is set to freedom, and namely free end bending and shearing is all 0; If the shaft part elastic bearing at bearing place, then boundary condition is set to spring-damping support, and namely the shearing of shaft part and bearing elastic counter-force balance, and moment and elastic reaction square balance; If the shaft part non-yielding prop at bearing place, then boundary condition is set to freely-supported, i.e. the amount of deflection of freely-supported place rotating shaft and moment of flexure are zero;

In this module, out-of-balance force is by amount of unbalance with load phase control, amount of unbalance=uneven value * apart from distance of shaft centers from, load phase place and represent the load angle of amount of unbalance at circumferencial direction;

The applying of partial admission's load and the applying of out-of-balance force similar, also be by the size of partial admission's load with load phase control, partial admission's load is divided into two parts, i.e. partial admission's tangential force and partial admission's rotating shaft moment of flexure, partial admission's tangential force is expressed as Ft, and computing formula is: Ft=BKW (2 (1-cos (a))) ^0.5/ (Ra), in formula, B represents proportionality constant, and KW represents governing stage power, and a represents opened variable valve angle, and R represents governing stage moving blade effective radius.Partial admission's rotating shaft moment of flexure is expressed as M, and computing formula is: M=P (D1 ³-D2 ³) (2 (1-cos (a))) ^0.5/ 24, in formula, D1 represents governing stage spinner blade overall diameter, and D2 represents packing diameter under nozzle, and P represents governing stage intake pressure difference;

Other step and parameter identical with embodiment one or two.

Embodiment four: one of present embodiment and embodiment one to three unlike: static analysis functions of modules structural drawing is as shown in Figure 7; Described static analysis module is the boundary condition according to rotor dynamics model bearing place, and application transfer matrix method calculates rotor gravity degree of disturbing, coupling gap, degree of misaligning, high cycle fatigue and external applied load, and stores bearing load and elevation data;

Static analysis module comprises gravity deflection degree of disturbing calculating sub module, coupling gap calculating sub module, degree of misaligning calculating sub module, external load calculation submodule and high cycle fatigue calculating sub module;

Described gravity deflection degree of disturbing calculating sub module comprises calculating gravity deflection module, drafting single-span gravity deflection module and selection and adjusts benchmark bearing module;

Described gravity deflection degree of disturbing computing module is responsible for calculating the rotor-support-foundation system bearing dynamical height of each block bearing position, support reaction and nominal pressure under gravity; Calculate rotor-support-foundation system under gravity each bearing across between the maximum deflection amount of deflection of corresponding shaft part and moment; Calculate the rotor-support-foundation system position of each shaft part, moment, shearing, displacement and gradient under gravity; In RDC system, simplify the angle design of user operation, RDC system is loaded into the rotator model established, and then can be called by gravity amount of deflection computing module, has calculated rear operation result and can unify to be presented at the result of calculation that system ejects and check in interface;

Wherein, the Method And Principle that described gravity deflection amount of deflection calculating adopts is:

Consider the n-th rotor shaft part, according to the balance equation of wind tunnel

$\frac{{\∂V}_x}{\∂z}=-\mathrm{\ρAg}---\left(1\right)$ $\frac{{\∂M}_x}{\text{\∂z}}=V_x---\left(2\right)$

V in formula _xfor shearing, z be axial location, ρ is density of material, A is rotating shaft area of section, M _xfor rotating shaft section turn moment; According to geometric relationship and flexure theory:

$\mathrm{\θ}=\frac{V_x}{\mathrm{\αGA}}+\frac{\∂x}{\∂z}---\left(3\right)$

$M_x=\mathrm{EI}\frac{\∂\mathrm{\θ}}{\∂z}---\left(4\right)$

In formula, θ is corner, α is Poisson ratio, G is modulus of shearing, x is bending direction displacement, E is elastic modulus, I is cross sectional moment of inertia;

According to equation (1) and (4) Lian Li can the differential equation of motion of this shaft part be:

$\frac{{\∂}^{4}x}{{\∂z}^4}+\frac{\mathrm{\ρAg}}{\mathrm{EI}}=0---\left(5\right)$

By solve an equation (5), the displacement function of this shaft part can be obtained:

$X+\frac{1}{24}\frac{\mathrm{\ρAg}}{\mathrm{EI}}{z}^4+\frac{1}{6}{C}_1{z}^3+\frac{1}{2}{C}_2{z}^2{+C}_{3}z+C_4=0---\left(6\right)$

Equation (6) is brought in (2) (3) (4), can M be obtained _x, V _xwith the expression formula of θ;

Because the boundary condition of rotor at bearing place is known, thus recursion can go out the constant C of each shaft part ₁, C ₂, C ₃and C ₄;

Undertaken programming by above method and can obtain the rotor-support-foundation system position of each shaft part, moment, shearing, displacement and gradient under gravity;

Bearing dynamical height pattern, when given associated gaps shaft part, radius, present position, is set to desirable bearing dynamical height by described coupling gap calculating sub module, can calculate joint gap, the desirable absolute altitude value of displacement and each bearing and actual elevation value; When bearing dynamical height pattern is set to actual elevation pattern, the shaft coupling that bearing is in actual elevation situation can be calculated and dehisce and dislocation value;

Wherein, the criterion adopted during the desirable bearing dynamical height of described calculating is in this absolute altitude situation, and the moment of flexure at axle journal place is 0, and therefore can guarantee that whole axle system curve is continuously differentiable state, the concrete principle of employing is:

(1) first fixing two initial bearing dynamical heights is 0 basic point;

(2) apply following equations calculate the 3rd bearing after the bearing dynamical height of (comprising the 3rd)

$Y_k=l_{k-1}\sin \left\{\underset{i=2}{\overset{2k-3}{\mathrm{\Σ}}}{\mathrm{\θ}}_i\right\}+Y_{k-1}$

$X_k=l_{k-1}\cos \left\{\underset{i=2}{\overset{2k-3}{\mathrm{\Σ}}}{\mathrm{\θ}}_i\right\}+X_{k-1}$

Y in formula _krepresent the vertical direction coordinate of bearing, i.e. bearing dynamical height; X _krepresent bearing axial coordinate; θ _irepresent the corner of single-span rotor; Y _k-1and X _k-1represent vertical direction coordinate and the axial coordinate of previous bearing; L represents that the length of single-span rotor is containing cantilever end, and k represents a kth bearing, and k>=3;

Shaft coupling is dehisced and the Computing Principle of dislocation value is: the first two bearing in setting shaft system is 0 benchmark bearing, translation and rotation are carried out to bearing below and rotor, when reaching the bearing dynamical height value that previous calculations obtains, the angle between the shaft coupling obtained and shaft coupling centre distance are shaft coupling and dehisce and dislocation value;

Described degree of misaligning calculating sub module comprises the respond module of desirable absolute altitude change and calculates absolute altitude matrix module;

Wherein, described degree of misaligning calculating sub module is when calculating rotor misalignment degree, main contrast's bearing dynamical height is relative to the load change of bearing during desirable absolute altitude change, and result of calculation is described by 1mil matrix, the change that namely during certain bearing rising 1mil, each bearing load occurs;

Computing formula is identical with the computing formula of gravity deflection amount of deflection;

Described external load calculation module comprises calculating external applied load module, checks reaction of bearing object module, checks displacement result module and check moment object module;

Wherein, described external load calculation module mainly comprises two parts Computed-torque control, and namely amount of unbalance calculates and partial admission's LOAD FOR, and amount of unbalance is divided into the interpolation of unbalance residual content and self-defined amount of unbalance, and wherein the computing formula of unbalance residual content is:

in formula, W represents unbalance residual content, and unit is that LB-IN, m represent shaft part quality, and r represents the radius of inertia; Self-defined amount of unbalance freely can add according to the actual conditions of amount of unbalance;

Under described plus load calculating sub module is used for the state being applied in some self-defined shaft part load at the specific shaft part of model, the support reaction of calculation bearing, displacement and moment; Calculate the concentrated stress coefficient of each shaft part, peak stress, mode endurance strength and safety coefficient high cycle fatigue parameter, main containing a core calculations function and three relevant result look facilities; Computing function calculates plus load module, is used for calculating partial admission load; Three relevant look facilities are respectively: check bearing reaction result, check displacement result, check moment result, main function is that rotor is bearing under partial admission load condition, calculate bearing reaction bearing reaction, displacement and moment, and be stored as text formatting for checking at any time;

In system, described high cycle fatigue calculating sub module has completed that gravity deflection calculates, the RESPONSE CALCULATION of desirable absolute altitude change and plus load calculate the support reaction of calculation bearing, displacement and moment when participating in calculating as optional parameter; Calculate the concentrated stress coefficient of each shaft part, peak stress, mode endurance strength and safety coefficient high cycle fatigue parameter;

Wherein, the principle that described high cycle fatigue computing module adopts is: the synergy considering the steady load that rotor bears and oscillating load, and the octahedral shear stress suffered by a minute cells in rotor is:

${\mathrm{\τ}}_{\mathrm{\Ω}}=\frac{1}{3}\sqrt{{({\mathrm{\σ}}_x-{\mathrm{\σ}}_y)}^2+{({\mathrm{\σ}}_y-{\mathrm{\σ}}_z)}^2+{({\mathrm{\σ}}_z-{\mathrm{\σ}}_x)}^2+6({\mathrm{\τ}}_{\mathrm{xy}}^2+{\mathrm{\τ}}_{\mathrm{yz}}^2+{\mathrm{\τ}}_{\mathrm{zx}}^2)}$

In formula, σ represents the normal stress of all directions, and τ represents the shear stress of all directions;

Equivalent stress formula is:

Describedly before rotor axial system is analyzed, first by MBM, rotor geometric model to be converted into mechanical model, regulation position of bearings and effective width-diameter ratio, thus the mechanical relationship at each position of rotor can be described out, and load according to the load that reality is born, memory model data are that next step static analysis module is prepared;

Gravity amount of deflection result of calculation as shown in Figure 8; Described misalignment computing module is used for the absolute altitude change of calculation bearing desirable absolute altitude situation lower bearing, moment, support reaction and specific loading; And the moment of rotor each position, shearing, displacement and gradient; And mil bearing can be obtained and misalign bearing moment response in situation, bearing response and the response of bearing specific loading;

In Fig. 8, example is the size of each bearing, position model data and load, absolute altitude and specific pressure data result;

As shown in Figure 9, sag curve function is in order to more vivid and show each shaft part of the rotator model height of deformation extent and the function developed under gravity intuitively, conveniently curve sectional drawing can be stored in computing machine assigned address with conventional picture format;

Figure 10 is plus load computing function menu structure figure;

Under selection applies bearing load type (maximum bearing load, gravity deflection, practical bearing absolute altitude, imposed load, input misalign distribution, input support reaction) situation, calculate the dynamicss such as the load-bearing capacity of each bearing under different rotating speeds, minimum oil film thickness, flow of lubricant, friction loss, maximum Babbitt alloy temperature, lubricant oil film turbulence effect, viscosity change, the thermoelastic sag of each tile fragment, dynamic stiffness coefficient and ratio of damping.Whole bearing analysis module function menu structure as shown in figure 11.

Other step and parameter identical with one of embodiment one to three.

Embodiment five: one of present embodiment and embodiment one to four comprise unlike: described bearing analysis module to be selected lubricating oil submodule, select bearing load condition submodule, checks steady result submodule, checks that kinetic coefficient bears fruit module and technology bearing performance submodule;

The alternative lubricant type of selection lubricating oil submodule is: lightweight steam turbine oil, 2190T lubricating oil, and can according to the self-defined lubricant type of lubricating oil density, viscosity, specific heat capacity and conductivity;

The loaded condition selecting bearing loaded condition submodule to comprise comprises: desirable gravity amount of deflection, bearing maximum load, practical bearing absolute altitude, plus load situation, in addition also can according to rotor misalignment distribution or the self-defined bearing loaded condition of bearing reaction;

Check that the content can checked in steady result submodule comprises: bearing load, load angle, oil film minimum thickness, bearing oil flow, bearing loss and watt warm content;

Check that the content that kinetic coefficient submodule can be checked is: the level under different rotor speed conditions, vertically and intersect rigidity and ratio of damping;

Described selection lubricating oil submodule is used in the warm analysis of normal viscosity and thermoelasticity hydrodynamic analysis, the lubricant type that user's unrestricted choice is commonly used and the self-defined lubricant type with special character;

Described selection bearing load condition submodule comprises for the bearing load condition selected: bearing maximum load, desirable gravity disturbance, actual supporting absolute altitude, plus load, definition misalign distribution and input bearing reaction situation.

Described bearing performance computing module mainly comprises two large divisions, is respectively the warm analysis of normal viscosity and thermoelasticity hydrodynamic analysis; Conveniently user adopts in a special case and carries out ad hoc analysis with head bearing analysis subroutine to corresponding bearing, meanwhile also support that user is arranged in detail to the analysis type of each bearing in rotator model, can estimate temperature (Estimate of shaft temperature) according to average oil film temperature (Average oil film temperature) and main shaft.User sets respectively according to the required hypothesis situation to film viscosity of analysis, user can specify and analyze with default design rotating speed, also manually can inputting specific rotation speeds and carry out single rotating speed analysis, more can carry out labor by specifying the highest and minimum calculating rotating speed and rotating speed number of fragments for specifying rotating speed interval; As shown in figure 12;

Other step and parameter identical with one of embodiment one to four.

Embodiment six: described performance analysis module comprises horizontal critical Speed Calculation submodule, technological dynamism coefficient submodule, stability analysis submodule and unbalance response submodule;

Described horizontal critical Speed Calculation submodule is when selecting given various bearing rigidity data, calculates the natural frequency of axle system each rank mode; Calculation bearing and support stiffness change, rotor quality change, rotor rigidity change the sensitivity analysis to the natural frequency of each rank mode;

Described horizontal critical Speed Calculation submodule comprises input shaft bearing data module, calculating natural frequency module, sensitivity analysis module, frequency check module and draws condition shape module;

Wherein, the principle of described horizontal critical Speed Calculation submodule is: the differential equation of motion of i-th unit is:

$\left[\begin{array}{cc}{m}_{11}^i& m_{12}^i\\ m_{21}^i& m_{22}^i\end{array}\right]\left\{\begin{array}{c}{\stackrel{..}{x}}_i\\ {\stackrel{..}{x}}_{i+1}\end{array}\right\}+\left[\begin{array}{cc}{c}_{11}^i& c_{12}^i\\ c_{21}^i& c_{22}^i\end{array}\right]\left\{\begin{array}{c}{\stackrel{.}{x}}_i\\ {\stackrel{.}{x}}_{i+1}\end{array}\right\}+\left[\begin{array}{cc}{k}_{11}^i& k_{12}^i\\ k_{21}^i& k_{22}^i\end{array}\right]\left\{\begin{array}{c}{x}_i\\ x_{i+1}\end{array}\right\}=\left\{\begin{array}{c}{f_i}^R\\ f_{i+1}^L\end{array}\right\}---\left(1\right)$

M in formula ⁱrepresent the quality of i-th unit, c ⁱrepresent the damping of i-th unit, k ⁱrepresent the rigidity of i-th unit, x ⁱrepresent the generalized displacement of i-th unit, f ⁱthe vector of expression power;

Suppose that non trivial solution is:

Q _i＝{x _i}e ^jωt

(2)

F _i＝{f _i}e ^jωt

Here ω is rotor velocity, and t is time variable;

Formula (2) is brought in formula (1), can obtains:

${-\mathrm{\ω}}^2\left[\begin{array}{cc}{m}_{11}^i& m_{12}^i\\ m_{21}^i& m_{22}^i\end{array}\right]\left\{\begin{array}{c}{Q}_i\\ Q_{i+1}\end{array}\right\}+\mathrm{j\ω}\left[\begin{array}{cc}{c}_{11}^i& c_{12}^i\\ c_{21}^i& c_{22}^i\end{array}\right]\left\{\begin{array}{c}{Q}_i\\ Q_{i+1}\end{array}\right\}+\left[\begin{array}{cc}{k}_{11}^i& k_{12}^i\\ k_{21}^i& k_{22}^i\end{array}\right]\left\{\begin{array}{c}{Q}_i\\ Q_{i+1}\end{array}\right\}=\left\{\begin{array}{c}\left\{{F_i}^R\right\}\\ \left\{F_{i+1}^L\right\}\end{array}\right\}---\left(3\right)$

Other unit also have similar kinetics equation, can solve horizontal critical rotary speed and corresponding Mode Shape by above-mentioned flat rate equation;

Described sensitivity analysis module comprises that bearing/support stiffness affects module, rotor quality affects module and rotor rigidity affects module;

Wherein, the principle of described sensitivity analysis module is (3) middle Coefficient m, k, i.e. quality and rigidity in self-defined formula above, and then recalculates critical rotary speed and Mode Shape;

Described unbalance response submodule comprises calculating imbalance affects module, drawing option mod and editor's unbalanced data module; Described imbalance affect submodule namely in certain range of speeds, under different rotating speeds, calculate each bearing place, the displacement of shaft part, phase place and force-responsive, simultaneously in order to intuitively show displacement, phase place and stressed change, provide a large amount of graphics processing function, adopt general images outputting supplementary module that above text result of calculation is converted into picture directly perceived and export;

Wherein, the Computing Principle of described unbalance response module is:

Suppose that i-th node has following relation

$\left[S^i\right]Q_i=\{F_i^L-R_i\}---\left(1\right)$

[S in formula ⁱ] be RICCATI matrix, { R _ibe RICCATI vector, and S and R is known starting condition;

Equation (1) is brought into the result obtained in differential equation of motion is:

$\begin{array}{c}[a_{11}^i+S^i]Q_i+a_{12}^i{Q}_{i+1}={F_i}^L+{F_i}^R-R_i\\ a_{21}^i{Q}_i+a_{22}^i{Q}_{i+1}=F_{i+1}^L\end{array}---\left(2\right)$

Here $a_{11}^i=-{\mathrm{\ω}}^2{m}_{11}+j{\mathrm{\ωc}}_{11}+k_{11};$ Other unit and above-mentioned formula similar;

Can obtain:

$Q_i={[a_{11}^i+S^i]}^{-1}\{F_i-R_i\}-a_{12}^i{Q}_{i+1}---\left(3\right)$

Here F _i=F _i ^l+ F _i ^r, according to equation (2) and (3), can obtain

$[a_{21}^i{[a_{11}^i+S^i]}^{-1}(-a_{12}^i)+a_{22}^i]Q_{i+1}=-a_{21}^i{[a_{11}^i+S^i]}^{-1}\{F_i-R_i\}+F_{i+1}^L---\left(4\right)$

Equation (4) has identical form with equation (1);

In start element section, starting condition is known, therefore can calculate cell node below by transfer matrix; Therefore the remaining unbalance response of rotor axial system is calculated by this method;

Described technological dynamism coefficient submodule is as the major parameter customization function of whole performance analysis module, both can set for independent rotating speed, also can set for multiple rotating speed, kinetic coefficient desired parameters has rotating speed, stiffness coefficient, ratio of damping, user can be the kinetic parameter under index inputs some rotating speeds with rotating speed, when carrying out corresponding rotating speed computing and system set-up parameters is enabled, above parameter will participate in following dynamics calculation, and above parameter will be preserved with model file;

Described stability analysis submodule ties up to stability under different rotating speeds for calculating axle, under being included in different rotating speeds, and the logarithmic decrement of different modalities exponent number lower rotor part system and Q factor;

Wherein, the Computing Principle of described logarithmic decrement is: the ratio of adjacent two amplitudes is taken the logarithm and is logarithmic decrement; Q factor is also called factor of merit, and Computing Principle is: n in formula ₀represent rotating speed during resonance peak, N ₁and N ₂represent former and later two rotating speeds when amplitude is 0.707 peak value.

Described drawing option mod comprises the amplitude/phase module under different rotating speeds, the respond module under different rotating speeds, Nyquist module and rotor track distribution module;

As shown in figure 13, mainly comprise critical rotary speed, unbalance responses, the large computing function of stability analysis three, relevant parameter arranges in the unified shaft part attribute Editor be integrated in main interface and arranges performance analysis module.

Calculation on Natural Frequency as shown in figure 14;

Unbalance response result data dependence as shown in figure 15;

Described RDC system utilizes a series of supplemental functionality to carry out modeling for assisting, parameter editor and result output function, wherein the data correlation of each supplemental functionality and core calculations function as shown in figure 17, in the main interface of system, subsidiary function structure mainly contains following four part compositions, be respectively: menu bar comprises toolbar, running state information hurdle, model editing viewing area, model attributes editing area, as shown in figure 18, shaft part attribute Editor is mainly used in coordinating each attribute of model editing area to shaft part each in set up rotator model and bearing modify and edit, not only can revise basic geometry and the mechanical attribute of shaft part and bearing, also various special construction parameter can be added according to unit actual composition structure, these special construction parameters within the system all unification be integrated in this interface,

Result output module is divided into text output and images outputting module, is that conveniently user checks that the text of every calculating and graphic result are developed specially.RDC system development dedicated computing result look facility, unifies the view procedure of result of calculation and preservation process, imparts again the function of result of calculation being carried out to simple editing operation while making two kinds of operations concentrate in same interface.

RDC software provides response and arranges interface so that user inputs relevant parameter, and system, by the specified range of speeds is carried out segmentation finally draws corresponding result of calculation automatically, arranges interface as shown in figure 16;

After computing completes, user can call accordingly result output function and check operation result, carries out dynamic analysis by according to the input that user is calculating Custom Interface for specific rotation speeds.

Other step and parameter identical with one of embodiment one to five.

Embodiment seven: present embodiment and embodiment one to six unlike: described preposition calculating specifically comprises: the result of calculation that bearing analysis module needs the rotor external applied load in static analysis module, rotor bow, bending and shearing, bearing support reaction, absolute altitude and shaft coupling to dehisce to misplace;

Performance analysis module need the rotor external applied load in static analysis module, rotor bow, bending and shearing, bearing support reaction, absolute altitude and shaft coupling dehisce misplace result of calculation and bearing analysis module in bearing stable state coefficient and kinetic coefficient result of calculation.Other step and parameter identical with one of embodiment one to six.

Claims (7)

1. large turbine-generator set axle system static and dynamic performance analytical calculation system, is characterized in that it comprises:

For setting up the MBM of rotor dynamics model;

For bearing load and the elevation data of the rotor dynamics model data and static analysis module of calling MBM, then according to Reynolds equation calculation bearing at the steady state data waited in gentle alternating temperature situation and kinetic coefficient, and store the bearing analysis module of kinetic coefficient;

For calling the kinetic coefficient of the rotor dynamics model data of MBM, the axle load data of static analysis module and bearing analysis module, to the performance analysis module that the critical rotary speed of rotor, unbalance response and rotor stability are analyzed;

Rotor dynamics model data for calling MBM to carry out the static analysis module of preposition calculating by bearing analysis module and performance analysis module.

2. large turbine-generator set axle system according to claim 1 static and dynamic performance analytical calculation system, is characterized in that described rotor dynamics model is the rotor dynamics model by equivalent stiffness diameter and shaft part quality being carried out the method establishment of building block splicing.

3. large turbine-generator set axle system according to claim 2 static and dynamic performance analytical calculation system, what it is characterized in that described MBM comprises equivalent model sets up submodule, load and boundary condition submodule and Data Format Transform submodule;

Described equivalent model set up submodule for the geometric model of rotor is carried out modelling with the form of each shaft part length of rotor and rigidity diameter, be converted into mechanical model, each shaft part is linked together by the form of being spliced by building block, build up whole roots rotor, and material properties is assigned to mechanical model and determines position of bearings and bearing size;

Wherein, the rigidity diameter in described equivalent model is applied 45 ° of methods and is calculated, and the concrete steps of the method are:

(1) the 45 ° lines tangent with leading circle are drawn at the variant positions of rotating shaft and impeller;

Article (2) two, it is a line segment that 45 ° of crossing line intersection points link with axisymmetric 45 ° of crossing line intersection points, if its length is DINT;

(3) arithmetic average diameter DAVE, formula is: DAVE1=(D1+DINT)/2, DAVE2=(D2+DINT)/2, in formula, DAVE1 is first paragraph mean diameter, DAVE2 is second segment mean diameter, and D1 represents impeller front rotary shaft diameter, rotating shaft diameter after D2 impeller;

(4) effective moment of inertia is calculated, formula: LEFF1=((I1+IINT)/2+IAVE1)/2, LEFF2=((I2+IINT)/2+IAVE2)/2, I1 represents impeller front rotary shaft moment of inertia, I2 represents rotating shaft moment of inertia after impeller, IINT represents 45 ° of intersection cross sectional moment of inertias, and IAVE1 represents mean diameter DAVE1 cross sectional moment of inertia, and IAVE2 represents mean diameter DAVE2 cross sectional moment of inertia;

(5) equivalent stiffness diameter is calculated: DEFF1=((64) (IEFF1)/π) ^0.25, DEFF2=((64) (IEFF2)/π) ^0.25;

The mechanical model of rotor utilizes transfer matrix method to form by a series of equivalent stiffness diameter and each section of shaft length;

Described load and boundary condition submodule are used for out-of-balance force and partial admission's load applying to determine bearing seat, bearing and the rotor boundary condition in axle journal position to certain or some shaft part positions;

Described Data Format Transform submodule is for storing the model data of the rotor of input and bearing, material properties, load and boundary condition with numerical tabular form and exporting, for browsing at any time and subsequent calculations analysis.

4. large turbine-generator set axle system according to claim 3 static and dynamic performance analytical calculation system, it is characterized in that described static analysis module is the boundary condition according to rotor dynamics model bearing place, application transfer matrix method calculates rotor gravity degree of disturbing, coupling gap, degree of misaligning, high cycle fatigue and external applied load, and stores bearing load and elevation data;

Static analysis module comprises gravity deflection degree of disturbing calculating sub module, coupling gap calculating sub module, degree of misaligning calculating sub module, external load calculation submodule and high cycle fatigue calculating sub module;

Described gravity deflection degree of disturbing calculating sub module comprises calculating gravity deflection module, drafting single-span gravity deflection module and selection and adjusts benchmark bearing module;

Described gravity deflection degree of disturbing computing module is responsible for calculating the rotor-support-foundation system bearing dynamical height of each block bearing position, support reaction and nominal pressure under gravity; Calculate rotor-support-foundation system under gravity each bearing across between the maximum deflection amount of deflection of corresponding shaft part and moment; Calculate the rotor-support-foundation system position of each shaft part, moment, shearing, displacement and gradient under gravity; In RDC system, simplify the angle design of user operation, RDC system is loaded into the rotator model established, and then can be called by gravity amount of deflection computing module, has calculated rear operation result and can unify to be presented at the result of calculation that system ejects and check in interface;

Wherein, the Method And Principle that described gravity deflection amount of deflection calculating adopts is:

Consider the n-th rotor shaft part, according to the balance equation of wind tunnel

$\frac{\∂V_x}{\∂z}=-\mathrm{\ρAg}---\left(1\right)$

$\frac{\∂M_x}{\∂z}=V_x---\left(2\right)$

V in formula _xfor shearing, z be axial location, ρ is density of material, A is rotating shaft area of section, M _xfor rotating shaft section turn moment;

According to geometric relationship and flexure theory:

$\mathrm{\θ}=\frac{V_x}{\mathrm{\αGA}}+\frac{\∂x}{\∂z}---\left(3\right)$

$M_x=\mathrm{EI}\frac{\∂\mathrm{\θ}}{\∂z}---\left(4\right)$

In formula, θ is corner, α is Poisson ratio, G is modulus of shearing, x is bending direction displacement, E is elastic modulus, I is cross sectional moment of inertia;

According to equation (1) and (4) Lian Li can the differential equation of motion of this shaft part be:

$\frac{{\∂}^{4}x}{\∂z^4}+\frac{\mathrm{\ρAg}}{\mathrm{EI}}=0---\left(5\right)$

By solve an equation (5), the displacement function of this shaft part can be obtained:

$X+\frac{1}{24}\frac{\mathrm{\ρAg}}{\mathrm{EI}}{z}^4+\frac{1}{6}{C}_1{z}^3+\frac{1}{2}{C}_2{z}^2+C_{3}z+C_4=0---\left(6\right)$

Equation (6) is brought in (2) (3) (4), can M be obtained _x, V _xwith the expression formula of θ;

Because the boundary condition of rotor at bearing place is known, thus recursion can go out the constant C of each shaft part ₁, C ₂, C ₃and C ₄; Undertaken programming by above method and can obtain the rotor-support-foundation system position of each shaft part, moment, shearing, displacement and gradient under gravity;

Bearing dynamical height pattern, when given associated gaps shaft part, radius, present position, is set to desirable bearing dynamical height by described coupling gap calculating sub module, can calculate joint gap, the desirable absolute altitude value of displacement and each bearing and actual elevation value; When bearing dynamical height pattern is set to actual elevation pattern, the shaft coupling that bearing is in actual elevation situation can be calculated and dehisce and dislocation value;

Wherein, the criterion adopted during the desirable bearing dynamical height of described calculating is in this absolute altitude situation, and the moment of flexure at axle journal place is 0, and therefore can guarantee that whole axle system curve is continuously differentiable state, the concrete principle of employing is:

(1) first fixing two initial bearing dynamical heights is 0 basic point;

(2) apply following equations calculate the 3rd bearing after the bearing dynamical height of (comprising the 3rd)

$Y_k=l_{k-1}\sin \left\{\underset{i=2}{\overset{2k-3}{\mathrm{\Σ}}}{\mathrm{\θ}}_i\right\}+Y_{k-1}$

$X_k=l_{k-1}\cos \left\{\underset{i=2}{\overset{2k-3}{\mathrm{\Σ}}}{\mathrm{\θ}}_i\right\}+X_{k-1}$

Y in formula _krepresent the vertical direction coordinate of bearing, i.e. bearing dynamical height; X _krepresent bearing axial coordinate; θ _irepresent the corner of single-span rotor; Y _k-1and X _k-1represent vertical direction coordinate and the axial coordinate of previous bearing; L represents that the length of single-span rotor is containing cantilever end, and k represents a kth bearing, and k>=3;

Shaft coupling is dehisced and the Computing Principle of dislocation value is: the first two bearing in setting shaft system is 0 benchmark bearing, translation and rotation are carried out to bearing below and rotor, when reaching the bearing dynamical height value that previous calculations obtains, the angle between the shaft coupling obtained and shaft coupling centre distance are shaft coupling and dehisce and dislocation value;

Described degree of misaligning calculating sub module comprises the respond module of desirable absolute altitude change and calculates absolute altitude matrix module;

Wherein, described degree of misaligning calculating sub module is when calculating rotor misalignment degree, main contrast's bearing dynamical height is relative to the load change of bearing during desirable absolute altitude change, and result of calculation is described by 1mil matrix, the change that namely during certain bearing rising 1mil, each bearing load occurs;

Computing formula is identical with the computing formula of gravity deflection amount of deflection;

Described external load calculation module comprises calculating external applied load module, checks reaction of bearing object module, checks displacement result module and check moment object module;

Wherein, described external load calculation module mainly comprises two parts Computed-torque control, and namely amount of unbalance calculates and partial admission's LOAD FOR, and amount of unbalance is divided into the interpolation of unbalance residual content and self-defined amount of unbalance, and wherein the computing formula of unbalance residual content is:

in formula, W represents unbalance residual content, and unit is that LB-IN, m represent shaft part quality, and r represents the radius of inertia; Self-defined amount of unbalance freely can add according to the actual conditions of amount of unbalance;

Under described plus load calculating sub module is used for the state being applied in some self-defined shaft part load at the specific shaft part of model, the support reaction of calculation bearing, displacement and moment; Calculate the concentrated stress coefficient of each shaft part, peak stress, mode endurance strength and safety coefficient high cycle fatigue parameter, main containing a core calculations function and three relevant result look facilities; Computing function calculates plus load module, is used for calculating partial admission load; Three relevant look facilities are respectively: check bearing reaction result, check displacement result, check moment result, main function is that rotor is bearing under partial admission load condition, calculate bearing reaction bearing reaction, displacement and moment, and be stored as text formatting for checking at any time;

In system, described high cycle fatigue calculating sub module has completed that gravity deflection calculates, the RESPONSE CALCULATION of desirable absolute altitude change and plus load calculate the support reaction of calculation bearing, displacement and moment when participating in calculating as optional parameter; Calculate the concentrated stress coefficient of each shaft part, peak stress, mode endurance strength and safety coefficient high cycle fatigue parameter;

Wherein, the principle that described high cycle fatigue computing module adopts is: the synergy considering the steady load that rotor bears and oscillating load, and the octahedral shear stress suffered by a minute cells in rotor is:

${\mathrm{\τ}}_{\mathrm{\Ω}}=\frac{1}{3}\sqrt{{({\mathrm{\σ}}_x-{\mathrm{\σ}}_y)}^2+{({\mathrm{\σ}}_y-{\mathrm{\σ}}_z)}^2+{({\mathrm{\σ}}_z-{\mathrm{\σ}}_x)}^2+6({\mathrm{\τ}}_{\mathrm{xy}}^2+{\mathrm{\τ}}_{\mathrm{yz}}^2+{\mathrm{\τ}}_{\mathrm{zx}}^2)}$

In formula, σ represents the normal stress of all directions, and τ represents the shear stress of all directions;

Equivalent stress formula is: ${\mathrm{\σ}}_{\mathrm{\θ}}=\frac{3}{\sqrt{2}}{\mathrm{\τ}}_{\mathrm{\Ω}}.$

5. large turbine-generator set axle system according to claim 4 static and dynamic performance analytical calculation system, is characterized in that described bearing analysis module comprises and selects lubricating oil submodule, selects bearing load condition submodule, checks steady result submodule, checks that kinetic coefficient bears fruit module and technology bearing performance submodule;

The alternative lubricant type of selection lubricating oil submodule is: lightweight steam turbine oil, 2190T lubricating oil, and can according to the self-defined lubricant type of lubricating oil density, viscosity, specific heat capacity and conductivity;

The loaded condition selecting bearing loaded condition submodule to comprise comprises: desirable gravity amount of deflection, bearing maximum load, practical bearing absolute altitude, plus load situation, in addition also can according to rotor misalignment distribution or the self-defined bearing loaded condition of bearing reaction;

Check that the content can checked in steady result submodule comprises: bearing load, load angle, oil film minimum thickness, bearing oil flow, bearing loss and watt warm content;

Check that the content that kinetic coefficient submodule can be checked is: the level under different rotor speed conditions, vertically and intersect rigidity and ratio of damping;

Described selection lubricating oil submodule is used in the warm analysis of normal viscosity and thermoelasticity hydrodynamic analysis, the lubricant type that user's unrestricted choice is commonly used and the self-defined lubricant type with special character;

Described selection bearing load condition submodule comprises for the bearing load condition selected: bearing maximum load, desirable gravity disturbance, actual supporting absolute altitude, plus load, definition misalign distribution and input bearing reaction situation.

6. large turbine-generator set axle system according to claim 5 static and dynamic performance analytical calculation system, is characterized in that described performance analysis module comprises horizontal critical Speed Calculation submodule, technological dynamism coefficient submodule, stability analysis submodule and unbalance response submodule;

Described horizontal critical Speed Calculation submodule is when selecting given various bearing rigidity data, calculates the natural frequency of axle system each rank mode; Calculation bearing and support stiffness change, rotor quality change, rotor rigidity change the sensitivity analysis to the natural frequency of each rank mode;

Described horizontal critical Speed Calculation submodule comprises input shaft bearing data module, calculating natural frequency module, sensitivity analysis module, frequency check module and draws condition shape module;

Wherein, the principle of described horizontal critical Speed Calculation submodule is: the differential equation of motion of i-th unit is:

$\left[\begin{array}{cc}{m}_{11}^i& m_{12}^i\\ m_{21}^i& m_{22}^i\end{array}\right]\left\{\begin{array}{c}{\stackrel{\·\·}{x}}_i\\ {\stackrel{\·\·}{x}}_{i+1}\end{array}\right\}+\left[\begin{array}{cc}{c}_{11}^i& c_{12}^i\\ c_{21}^i& c_{22}^i\end{array}\right]\left\{\begin{array}{c}{\stackrel{\·}{x}}_i\\ {\stackrel{\·}{x}}_{i+1}\end{array}\right\}+\left[\begin{array}{cc}{k}_{11}^i& k_{12}^i\\ k_{21}^i& k_{22}^i\end{array}\right]\left\{\begin{array}{c}{x}_i\\ x_{i+1}\end{array}\right\}=\left\{\begin{array}{c}{f_i}^R\\ f_{i+1}^L\end{array}\right\}---\left(1\right)$

M in formula ⁱrepresent the quality of i-th unit, c ⁱrepresent the damping of i-th unit, k ⁱrepresent the rigidity of i-th unit, x ⁱrepresent the generalized displacement of i-th unit, f ⁱthe vector of expression power;

Suppose that non trivial solution is:

Q _i＝{x _i}e ^jωt(2)

F _i＝{f _i}e ^jωt

Here ω is rotor velocity, and t is time variable;

Formula (2) is brought in formula (1), can obtains:

$-{\mathrm{\ω}}^2\left[\begin{array}{cc}{m}_{11}^i& m_{12}^i\\ m_{21}^i& m_{22}^i\end{array}\right]\left\{\begin{array}{c}{Q}_i\\ Q_{i+1}\end{array}\right\}+\mathrm{j\ω}\left[\begin{array}{cc}{c}_{11}^i& c_{12}^i\\ c_{21}^i& c_{22}^i\end{array}\right]\left\{\begin{array}{c}{Q}_i\\ Q_{i+1}\end{array}\right\}+\left[\begin{array}{cc}{k}_{11}^i& k_{12}^i\\ k_{21}^i& k_{22}^i\end{array}\right]\left\{\begin{array}{c}{Q}_i\\ Q_{i+1}\end{array}\right\}=\left\{\begin{array}{c}\left\{{F_i}^R\right\}\\ \left\{F_{i+1}^L\right\}\end{array}\right\}---\left(3\right)$

Other unit also have similar kinetics equation, can solve horizontal critical rotary speed and corresponding Mode Shape by above-mentioned flat rate equation;

Described sensitivity analysis module comprises that bearing/support stiffness affects module, rotor quality affects module and rotor rigidity affects module;

Wherein, the principle of described sensitivity analysis module is (3) middle Coefficient m, k, i.e. quality and rigidity in self-defined formula above, and then recalculates critical rotary speed and Mode Shape;

Described unbalance response submodule comprises calculating imbalance affects module, drawing option mod and editor's unbalanced data module; Described imbalance affect submodule namely in certain range of speeds, under different rotating speeds, calculate each bearing place, the displacement of shaft part, phase place and force-responsive, simultaneously in order to intuitively show displacement, phase place and stressed change, provide a large amount of graphics processing function, adopt general images outputting supplementary module that above text result of calculation is converted into picture directly perceived and export;

Wherein, the Computing Principle of described unbalance response module is:

Suppose that i-th node has following relation

[S ⁱ]Q _i＝{F _i ^L-R _i} (1)

[S in formula ⁱ] be RICCATI matrix, { R _ibe RICCATI vector, and S and R is known starting condition;

Equation (1) is brought into the result obtained in differential equation of motion is:

$[a_{11}^i+S^i]Q_i+a_{12}^i{Q}_{i+1}={F_i}^L+{F_i}^R-R_i$ (2)

$a_{21}^i{Q}_i+a_{22}^i{Q}_{i+1}=F_{i+1}^L$

Here $a_{11}^i=-{\mathrm{\ω}}^2{m}_{11}+\mathrm{j\ω}{c}_{11}+k_{11};$ Other unit and above-mentioned formula similar;

Can obtain:

$Q_i={[a_{11}^i+S^i]}^{-1}\{F_i-R_i\}-a_{12}^i{Q}_{i+1}---\left(3\right)$

Here F _i=F _i ^l+ F _i ^r, according to equation (2) and (3), can obtain

$[a_{21}^i{[a_{11}^i+S^i]}^{-1}(-a_{12}^i)+a_{22}^i]Q_{i+1}=-a_{21}^i{[a_{11}^i+S^i]}^{-1}\{F_i-R_i\}+F_{i+1}^L---\left(4\right)$

Equation (4) has identical form with equation (1);

In start element section, starting condition is known, therefore can calculate cell node below by transfer matrix;

Therefore the remaining unbalance response of rotor axial system is calculated by this method;

Described technological dynamism coefficient submodule is as the major parameter customization function of whole performance analysis module, both can set for independent rotating speed, also can set for multiple rotating speed, kinetic coefficient desired parameters has rotating speed, stiffness coefficient, ratio of damping, user can be the kinetic parameter under index inputs some rotating speeds with rotating speed, when carrying out corresponding rotating speed computing and system set-up parameters is enabled, above parameter will participate in following dynamics calculation, and above parameter will be preserved with model file;

Described stability analysis submodule ties up to stability under different rotating speeds for calculating axle, under being included in different rotating speeds, and the logarithmic decrement of different modalities exponent number lower rotor part system and Q factor;

Wherein, the Computing Principle of described logarithmic decrement is: the ratio of adjacent two amplitudes is taken the logarithm and is logarithmic decrement;

Q factor is also called factor of merit, and Computing Principle is: n in formula ₀represent rotating speed during resonance peak, N ₁and N ₂represent former and later two rotating speeds when amplitude is 0.707 peak value.

7. large turbine-generator set axle system according to claim 6 static and dynamic performance analytical calculation system, is characterized in that described preposition calculating specifically comprises: the result of calculation that bearing analysis module needs the rotor external applied load in static analysis module, rotor bow, bending and shearing, bearing support reaction, absolute altitude and shaft coupling to dehisce to misplace;

Performance analysis module need the rotor external applied load in static analysis module, rotor bow, bending and shearing, bearing support reaction, absolute altitude and shaft coupling dehisce misplace result of calculation and bearing analysis module in bearing stable state coefficient and kinetic coefficient result of calculation.