CN103745030B - A kind of eccentric drum barrel aerodynamics evaluation method with labyrinth gas seals - Google Patents
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Abstract
The invention discloses a kind of eccentric drum barrel aerodynamics evaluation method with labyrinth gas seals belonging to rotor dynamics technical field. The method is: 1) integrated fluid calculates and structural analysis, sets up the three-dimensional drum barrel geometrical calculation model with labyrinth gas seals and three-dimensional drum barrel structural model; 2) utilize the three-dimensional geometry computation model in step 1), calculate drum surface static pressure under different offset; 3) in step 2) basis on, calculate the drum surface with labyrinth gas seals radially aerodynamic force and tangential aerodynamic force; 4) utilize the three-valued structures model in step 1), in step 2) basis on, the impact on drum barrel characteristic of the calculated gas flow exciting. The present invention is by calculating with the eccentric drum surface aerodynamic force of labyrinth gas seals and aerodynamic force the change about static characteristic of the drum barrel structure, combine the simple Airflow Exciting-Vibration Force calculating certain rotor structure and research structure mechanical characteristic under dynamic excitation affects, be suitable for the calculating of the cartridge type rotor of concrete size and structure.
Description
Technical field
The invention belongs to rotor dynamics technical field, particularly to a kind of eccentric drum barrel aerodynamics evaluation method with labyrinth gas seals.
Background technology
Turbomachinery (axial-flow compressor, turbogenerator and steam turbine) in large rotating machinery is the visual plant of power industry, aerospace industry. But it there is also many problems in manufacturing and designing, thus causing being in operation there is serious accident, causes heavy economic losses so that casualties.
Cause that the major reason of various serious accident is due to the vibration of large rotating machinery, unstability, and cause vibration, the principal element of unstability is the various exciting forces of system. Therefore, the research of exciting force suffered by rotor it will be seen that rotor exciting force mainly has Unbalance, air-flow periodical exciting force, sealing force etc. It addition, the exciting force that flex rotor causes due to bias (being called for short Alford power) is also one common in exciting force.
Drum barrel is to rotate above attachment structure common in Mechanic Rotor System, and the comb tooth on drum barrel has again the effect obturaged simultaneously, and its sealing property affects the overall performance of aero-engine. Due to problem or the out-of-balance force effect of manufacture process, turn stator and can produce relative eccentric so that turn stator circular gap uneven, and this uneven distribution to be as rotor rotationally-varying. Therefore, comb tooth space width of obturaging is uneven and turns stator bias and will necessarily produce aerodynamic force and unequal in drum barrel each position, and complicated flow-induced vibration can affect the dynamics of drum barrel structure. Model and reasonable computation that comb tooth drum barrel is obturaged can be set up, decide can the accurate analysis aerodynamic force kinetic effect to drum barrel structure, and determine pneumatic boundary condition.
Although the flow-induced vibration sealing structure has been carried out big quantity research by existing a lot of scholars both at home and abroad, mechanism of obturaging mainly around disc type comb tooth, from the aspect such as leakage rate, rotating speed, labyrinth gas seals characteristic carried out numerical simulation calculation, and the calculating for drum comb tooth is not enough.
Summary of the invention
In order to overcome the vacancy in above-mentioned prior art, the present invention proposes a kind of eccentric drum barrel aerodynamics evaluation method with labyrinth gas seals, it is characterised in that concretely comprising the following steps of these computational methods:
1) integrated fluid calculates and structural analysis, sets up the three-dimensional drum barrel geometrical calculation model with labyrinth gas seals and the three-dimensional drum barrel structural model with labyrinth gas seals;
2) utilize the three-dimensional geometry computation model in step 1), calculate drum surface static pressure under different offset;
3) in step 2) basis on, calculate the drum surface with labyrinth gas seals radially aerodynamic force and tangential aerodynamic force;
4) utilize the 3 d structure model in step 1), in step 2) basis on, the impact on drum barrel characteristic of the calculated gas flow exciting.
Described step 1) is set up the three-dimensional drum barrel geometrical calculation model with labyrinth gas seals and is specifically included:
11) simplify and omit will not the geometric detail that affects greatly of stream field structure;
12) for speed-up computation convergence, Multigrid Technique grid division is adopted;
The number of plies of multi grid is determined by lattice number, and lattice number meets:
∑2n+1(n≥2)
Wherein n represents reticulate layer;
The number of plies of multi grid is: min(n)+1;
13) calculate and set the ground floor mesh width of runner wall:
Wherein, ywallFor wall ground floor sizing grid, unit is m; VrefFor reference velocity, unit m/s; LrefFor reference length, unit is m; V is the kinematic viscosity of fluid, and unit is m2/ s; Y1 +For characteristic, corresponding different turbulence models, there is different spans.
Geometric detail in described step 11) refers to the profile of tooth of comb tooth and sets in runner concrete shape size between simulation blade.
Described step 1) sets up three-dimensional drum barrel structural model, it is necessary to divides the grid corresponding with three-dimensional drum barrel geometrical calculation model meshes, is primarily referred to as the grid number of circumference.
Described step 2) particularly as follows:
21) the different eccentric amount es of drum barrel comb tooth and stator are set, choose suitable import and export boundary condition;
22) calculating than Ω/ω according to different frequency of vortex motion and extract many groups static pressure, wherein Ω is off drum barrel eddy motion rotating speed, and ω is drum barrel rotor speed;
23) calculating on the basis of drum surface static pressure, obtaining the time dependent relation of drum surface static pressure p, transformation relation formula such as formula:
Wherein,For eccentric coordinate system circumference angle,For rotor coordinate circumference angle.
Described step 21) in import and export boundary condition refer to the pressure and temperature in import, exit.
Described step 22) in frequency of vortex motion ratio take 0,0.2 ,-0.5 ,-1.0.
Described step 3) particularly as follows:
31) in step 23) basis on, drum surface static pressure under different offsets is quadratured, solves radially aerodynamic force, tangential aerodynamic force, formula is
Wherein, FrFor radial direction aerodynamic force, FtFor tangential aerodynamic force, z is drum barrel axial coordinate, and r is radial direction radius, and L is axial length,For eccentric coordinate system circumference angle;
32) ignoring additional mass and inertia effects, when certain offset, solve aerodynamic stiffness coefficient and air damping coefficient, formula is
Wherein, Ω is off drum barrel eddy motion rotating speed, and e is offset, K, and C is Main rigidity coefficient and main damped coefficient respectively, k, and c is cross-couplings stiffness coefficient and cross-couplings damped coefficient.
Described step 32) in eccentric amount e=0.2mm.
Described step 4) is particularly as follows: according to known drum surface aerodynamic force, utilize the mode that linear interpolation loads by step 22) in the static pressure that obtains be loaded into drum surface and carry out loading and calculate, utilize finite element software to calculate drum barrel malformation and STRESS VARIATION.
The beneficial effect of the invention: the present invention is by calculating with the eccentric drum surface aerodynamic force of labyrinth gas seals structure and aerodynamic force the change about static characteristic of the drum barrel structure, more fully combine over the simple Airflow Exciting-Vibration Force calculating certain rotor structure and simple research structure mechanical characteristic under dynamic excitation affects, be suitable for the calculating of the cartridge type rotor of concrete size and structure.
Accompanying drawing explanation
Fig. 1 is a kind of eccentric drum barrel aerodynamics evaluation method flow diagram with labyrinth gas seals;
Fig. 2 is the simplification geometric model of labyrinth gas seals drum barrel runner-comb tooth cavity;
Fig. 3 is that labyrinth gas seals drum barrel runner-comb tooth cavity mould calculates computation model and stress and strain model;
Fig. 4 is certain type aerial engine fan rotor structure schematic diagram;
Fig. 5 is the 3 d structure model of labyrinth gas seals drum barrel;
Fig. 6 is that eccentric rotor axle makes precessional motion;
Fig. 7 is labyrinth gas seals bias drum surface static pressure distribution.
Detailed description of the invention
Below in conjunction with accompanying drawing, the present invention is further described.
The concrete size of the second level drum barrel structure in certain type aerial engine fan rotor combines and is illustrated in fig. 2 shown below, wherein, comb tooth tooth depth H=5.5mm, clearance C=the 2mm of comb tooth and stator, comb tooth addendum width T=0.3mm, the distance B1=2.7mm between first comb tooth and second comb tooth, the distance B2=59.7mm between second comb tooth and the 3rd comb tooth, profile of tooth angle a=5 °, elastic modulus E=1.15 × 1011Pa, density p=4.48 × 103kg/m3, Poisson's ratio μ=0.3, in the foundation for drum barrel geometrical calculation model three-dimensional in the method and three-dimensional drum barrel structural model of these data.
It is illustrated in figure 1 a kind of eccentric drum barrel aerodynamics evaluation method flow diagram with labyrinth gas seals of the present invention, then the specifically comprising the following steps that of the inventive method
1) integrated fluid calculates and structural analysis, sets up the three-dimensional drum barrel geometrical calculation model with labyrinth gas seals and the three-dimensional drum barrel structural model with labyrinth gas seals;
Step 1) is set up the three-dimensional drum barrel geometrical calculation model with labyrinth gas seals and is specifically included:
11) simplify and omit will not the geometric detail that affects greatly of stream field structure;
In comb tooth cavity, fluidal texture itself is complicated, if considering further, upstream and downstream blade arranges the imperfect flow caused, then the import and export boundary flowing of tooth cavity of combing is time dependent Unsteady Flow. Simulating the flowing in this type of comb tooth cavity exactly, need to comprise and arrange with comb tooth upstream and downstream blade, carry out unsteady numerical simulations, amount of calculation is quite huge. Reasonably simplify accordingly, it would be desirable to carry out some.
First, analyze that drum barrel vibrate by comb tooth aerodynamic force when affecting, it is not necessary to the Flow details in consideration blade path, and only need to give the comb tooth cavity import and export border close with actual flow state. Hence setting up three-dimensional drum barrel geometrical calculation model simplification figure, referring to accompanying drawing 3, the impact of adjacent blades can be passed through to import and export border reflection. Secondly, when not having large scale inlet distortion or stall disturbance, gas compressor circumferential flow field is with the number of blade for the cycle, approximate in cyclically-varying, therefore, generally when Flow Field Calculation, only analyze single vane sector, and assume that rest blade passage flow field is identical with this sector. So, the runner-comb tooth cavity model being sector with individual blade passage circumferential span may finally be reduced to.
As shown in Figure 4, one-level movable vane 1 and 2, two grades of movable vanes 3 of one-level stator blade and 4, three grades of movable vanes 5 of two grades of stator blades and afterwards space between three grades of stator blades are not the rectangular shape of specification in fact, it is the space of plane approximation parallelogram, is simplified to the shape of specification cuboid herein for convenience of calculation.
So-called geometric detail, concrete shape size between simulation blade in the profile of tooth of the tooth of combing exactly referred to and setting runner.
12) for speed-up computation convergence, Multigrid Technique grid division is adopted;
The number of plies of multi grid is determined by lattice number, and lattice number meets:
∑2n+1(n≥2)
Wherein n represents reticulate layer;
The number of plies of multi grid is: min(n)+1;
As: 17=24+ 1, min (n)=4, namely meet 5 weight multi grids;
61=25+24+23+22+ 1, min(n)=2, namely meet 3 weight multi grids.
13) calculate and set the ground floor mesh width of runner wall:
Wherein, ywallFor wall ground floor sizing grid, unit is m; VrefFor reference velocity, unit m/s; LrefFor reference length, unit is m; V is the kinematic viscosity of fluid, and unit is m2/ s; Y1 +For characteristic, corresponding different turbulence models, there is different spans.
When utilizing NUMECA computed in software, it is necessary to ground floor mesh width determined by the model according to calculating, and software automatically generates ensuing mesh width according to ground floor width. So needing the setting ground floor mesh width later of calculating.
Step 1) utilizes finite element software to set up the structural model of three-dimensional drum barrel, referring to accompanying drawing 5. Drum barrel outer surface circumference grid divides corresponding with fluid passage model meshes. Select 8 Nodes Three-dimensional solid element solid45 that drum barrel is modeled. This drum barrel model includes 7314 unit altogether, 10764 nodes.
2) utilize the three-dimensional geometry computation model in step 1), calculate drum surface static pressure under different offset.
Step 2) particularly as follows:
21) arranging the different eccentric amount es of drum barrel comb tooth and stator, choose suitable import and export boundary condition, this step analyzes the different offset impact on Airflow Exciting-Vibration Force qualitatively.
Arranging the eccentric amount e of the drum barrel comb flank of tooth and stator, eccentric drum barrel motor process is referring to accompanying drawing 6. Considering that the airflow direction in flow process, speed and pressure distribution are uneven etc., turbulence model adopts the most commonly used Spalart-Allmaras turbulence model, and unsteady computation adopts dual-time scale centered difference to carry out Pneumatic Calculation. During calculating, wall is all set to adiabatic boundary, and gas adopts without slip boundary condition with wall. Import gives stagnation temperature 393K, and two import stagnation pressures are 287KPA, 280KPA, two exit static pressure successively is 220KPa, 240KPa successively. Owing to stator imports and exports air-flow and non axial, so on inlet boundary, given corresponding air-flow axial velocity component, i.e. pre-swirl angle, is 56 ° respectively, 30 °. Mainly take offset is that several situation of 0mm, 0.2mm, 0.5mm, 1.0mm, 1.9mm goes to calculate drum surface static pressure herein, launches namely to be referred to accompanying drawing 7 by each for surface position static pressure.
22) calculating than Ω/ω according to different frequency of vortex motion and extract many groups static pressure, wherein Ω is off drum barrel eddy motion rotating speed, and ω is drum barrel rotor speed. Frequency of vortex motion takes 0 than mainly herein, and 0.2 ,-0.5 ,-1.0. This step calculates whirling motion ratio except affecting except qualitative analysis whirling motion, or needs during for step 3) calculated rigidity and damping, because there being four unknown numbers, so needing to organize solution more. By the static pressure of NUMECA computed in software drum surface, these static pressures can take out, and is then applied directly in step 4) to go the static characteristics calculating drum barrel.
23) calculating on the basis of drum surface static pressure, obtaining the time dependent relation of pressure, transformation relation formula such as formula:
Wherein,For eccentric coordinate system circumference angle,For rotor coordinate circumference angle. This step calculates radial force for next step and tangential force explains. Because calculated static pressure is numerical solution, determine concrete numerical value by each coordinate. But these numerical value cannot be updated in the computing formula of radial force and tangential force, therefore to be fitted to this transformation relation formula, thus can be calculated.
3) in step 2) basis on, calculate the drum surface with labyrinth gas seals radially aerodynamic force and tangential aerodynamic force;
Step 3) particularly as follows:
31) in step 23) basis on, drum surface static pressure under different offsets is quadratured, solves radially aerodynamic force, tangential aerodynamic force, formula is
Wherein, FrFor radial direction aerodynamic force, FtFor tangential aerodynamic force, z is drum barrel axial coordinate, and r is radial direction radius, and L is axial length,For eccentric coordinate system circumference angle;
32) ignoring additional mass and inertia effects, when certain offset, solve aerodynamic stiffness coefficient and air damping coefficient, formula is
Wherein, Ω is off drum barrel eddy motion rotating speed, and e is offset, K, and C is Main rigidity coefficient and main damped coefficient respectively, k, and c is cross-couplings stiffness coefficient and cross-couplings damped coefficient. Wherein, the size of Main rigidity COEFFICIENT K reflects the air-flow impact on rotor-support-foundation system rigidity, and K value is more big, and rotor rigidity is more strong, and stability is more good. Otherwise, cross-couplings stiffness coefficient k shows as tangential force size, and its value is more big, and tangential force is more big, and rotor-support-foundation system is more unstable.
It is that drum barrel comb tooth when 0.2mm is calculated to eccentric amount e. Analyze the three-dimensional streamline in comb tooth cavity, it can be seen that air-flow has certain circumferential speed after being entered comb tooth cavity by higher-pressure region, rear end reveals to low-pressure end, and air-flow sudden expansion forms vortex after comb tooth step, consumes the energy revealed to low-pressure end. Under different eddy velocities, amount of leakage remains unchanged, and for 0.48kg/s, is about the 0.58% of total flow. But pressure is circumferentially uneven distribution, and during the change of whirling motion angular velocity, the fluctuation amplitude of pressure and phase place are all different. Same delivery type axial coordinate center, the axial static pressure of different frequency of vortex motion ratios is analyzed. After linear fit, can obtain radial force with whirling motion angular velocity relational expression is: FrThe relational expression of/e=-1.09 × 105-143.30 Ω, tangential force and whirling motion angular velocity is: Ft/ e=1.39 × 105-462.77 Ω. Aerodynamic stiffness and air damping coefficient can be obtained: K=107000N/m, k=138000N/m, c=143.3Ns/m ,=461.67Ns/m.
4) utilize the 3 d structure model in step 1), in step 2) basis on, the impact on drum barrel characteristic of the calculated gas flow exciting.
According to known drum surface aerodynamic force, utilize the mode that linear interpolation loads by step 22) in the static pressure that obtains be loaded into drum surface and carry out loading and calculate, utilize finite element software to calculate drum barrel malformation and STRESS VARIATION. This step completes in ANSYS, sets up 3 d structure model in software, sets constraint, loaded surfaces static pressure, then utilizes software to solve voluntarily, finally extract the result solved.
The above; being only the present invention preferably detailed description of the invention, but protection scope of the present invention is not limited thereto, any those familiar with the art is in the technical scope that the invention discloses; the change that can readily occur in or replacement, all should be encompassed within protection scope of the present invention. Therefore, protection scope of the present invention should be as the criterion with scope of the claims.
Claims (7)
1. the eccentric drum barrel aerodynamics evaluation method with labyrinth gas seals, it is characterised in that concretely comprising the following steps of these computational methods:
1) integrated fluid calculates and structural analysis, sets up the three-dimensional drum barrel geometrical calculation model with labyrinth gas seals and the three-dimensional drum barrel structural model with labyrinth gas seals; Described three-dimensional drum barrel structural model of setting up, drum barrel outer surface circumference grid divides corresponding with the fluid passage model meshes in three-dimensional drum barrel geometrical calculation model;
2) utilize step 1) in three-dimensional geometry computation model, calculate drum surface static pressure under different offset;
3) in step 2) basis on, calculate the drum surface with labyrinth gas seals radially aerodynamic force and tangential aerodynamic force;
4) utilize step 1) in 3 d structure model, in step 2) basis on, the impact on drum barrel characteristic of the calculated gas flow exciting.
2. a kind of eccentric drum barrel aerodynamics evaluation method with labyrinth gas seals according to claim 1, it is characterised in that described step 1) set up and specifically include with the three-dimensional drum barrel geometrical calculation model of labyrinth gas seals:
11) simplifying will not the geometric detail that affects greatly of stream field structure; Described geometric detail refers to the profile of tooth of comb tooth and sets in runner concrete shape size between simulation blade;
12) for speed-up computation convergence, Multigrid Technique grid division is adopted;
The number of plies of multi grid is determined by lattice number, and lattice number meets:
Σ2n+1n≥2
Wherein n represents reticulate layer;
The number of plies of multi grid is: min (n)+1;
13) calculate and set the ground floor mesh width of runner wall:
Wherein, ywallFor wall ground floor sizing grid, unit is m; VrefFor reference velocity, unit m/s; LrefFor reference length, unit is m; V is the kinematic viscosity of fluid, and unit is m2/ s;For characteristic, corresponding different turbulence models, there is different spans.
3. a kind of eccentric drum barrel aerodynamics evaluation method with labyrinth gas seals according to claim 1, it is characterised in that described step 2) particularly as follows:
21) the different eccentric amount es of drum barrel comb tooth and stator are set, choose suitable import and export boundary condition; Described import and export boundary condition refers to the pressure and temperature in import, exit;
22) calculating than Ω/ω according to different frequency of vortex motion and extract many groups static pressure, wherein Ω is off drum barrel eddy motion rotating speed, and ω is drum barrel rotor speed;
23) calculating on the basis of drum surface static pressure, obtaining the time dependent relation of drum surface static pressure p, transformation relation formula such as formula:
Wherein,For eccentric coordinate system circumference angle,For rotor coordinate circumference angle.
4. a kind of eccentric drum barrel aerodynamics evaluation method with labyrinth gas seals according to claim 3, it is characterised in that described step 22) in frequency of vortex motion ratio take 0,0.2 ,-0.5 ,-1.0.
5. a kind of eccentric drum barrel aerodynamics evaluation method with labyrinth gas seals according to claim 3, it is characterised in that described step 3) particularly as follows:
31) in step 23) basis on, drum surface static pressure under different offsets is quadratured, solves radially aerodynamic force, tangential aerodynamic force, formula is
Wherein, FrFor radial direction aerodynamic force, FtFor tangential aerodynamic force, z is drum barrel axial coordinate, and r is radial direction radius, and L is axial length,For eccentric coordinate system circumference angle;
32) ignoring additional mass and inertia effects, when certain offset, solve aerodynamic stiffness coefficient and air damping coefficient, formula is
Wherein, Ω is off drum barrel eddy motion rotating speed, and e is offset, K, and C is Main rigidity coefficient and main damped coefficient respectively, k, and c is cross-couplings stiffness coefficient and cross-couplings damped coefficient.
6. a kind of eccentric drum barrel aerodynamics evaluation method with labyrinth gas seals according to claim 5, it is characterised in that described step 32) in eccentric amount e=0.2mm.
7. a kind of eccentric drum barrel aerodynamics evaluation method with labyrinth gas seals according to claim 3, it is characterized in that, described step 4) particularly as follows: according to known drum surface aerodynamic force, utilize the mode that linear interpolation loads by step 22) in the static pressure that obtains be loaded into drum surface and carry out loading and calculate, utilize finite element software to calculate drum barrel malformation and STRESS VARIATION.
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