WO2013091222A1 - 径流式液力透平优化设计方法 - Google Patents
径流式液力透平优化设计方法 Download PDFInfo
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- WO2013091222A1 WO2013091222A1 PCT/CN2011/084460 CN2011084460W WO2013091222A1 WO 2013091222 A1 WO2013091222 A1 WO 2013091222A1 CN 2011084460 W CN2011084460 W CN 2011084460W WO 2013091222 A1 WO2013091222 A1 WO 2013091222A1
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- optimization
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- cfd
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F03—MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
- F03B—MACHINES OR ENGINES FOR LIQUIDS
- F03B3/00—Machines or engines of reaction type; Parts or details peculiar thereto
- F03B3/10—Machines or engines of reaction type; Parts or details peculiar thereto characterised by having means for functioning alternatively as pumps or turbines
- F03B3/103—Machines or engines of reaction type; Parts or details peculiar thereto characterised by having means for functioning alternatively as pumps or turbines the same wheel acting as turbine wheel and as pump wheel
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
- F05B2240/00—Components
- F05B2240/20—Rotors
- F05B2240/24—Rotors for turbines
- F05B2240/242—Rotors for turbines of reaction type
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
- F05B2260/00—Function
- F05B2260/84—Modelling or simulation
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E10/00—Energy generation through renewable energy sources
- Y02E10/20—Hydro energy
Definitions
- the invention belongs to the residual pressure recovery technology in the fields of petrochemical, chemical fertilizer, chemical industry, etc., and relates to a design method of a hydraulic turbine, in particular to a design optimization method of a radial flow hydraulic machine. Background technique
- Hydraulic turbines entered the market in the late 1970s, with reverse pumps (REVERSE PUMP), Francis pump (FRANCIS), Kaplan (KAPLAX) and Pelton (PELTON).
- the reverse pump type hydraulic turbine realizes the pressure recovery of the liquid medium by the reverse operation of the centrifugal pump.
- the structure is simple, the cost is low, and the design is mature, so it is widely used in petrochemical plants.
- the flow requirements are strict. When the flow rate is too large, the recovery efficiency will be greatly reduced, and even there will be no recovery. Due to the above drawbacks, such hydraulic turbines tend to be replaced by radial turbines.
- the pressure drop required by the petrochemical plant process is often quite large, and there is a large amount of recyclable liquid pressure energy.
- the single-stage turbine is not suitable for high-pressure differential hydraulic recovery, only the addition liquid
- the level of the force turbine can increase the scale of energy recovery.
- the radial blade turbine hydraulic turbine is more efficient than the reversible pump hydraulic turbine, the number of turbines used in the same differential pressure is often less than that of the reverse pump turbine. The reduction will effectively improve the reliability of the rotor.
- the diameter of the radial vane turbine is relatively small, the structure is compact and the cost is low.
- variable geometry nozzles can be used because the nozzles on the annular runner are bolted and easy to replace, so that the hydraulic turbine has the best working efficiency and the design flow range is also better. width.
- the design theory of radial hydraulic turbine flow components there is limited information on the design theory of radial hydraulic turbine flow components.
- the invention discloses a radial hydraulic turbine optimization design method to provide support for the design of the hydraulic turbine flow passage component. Summary of the invention
- the object of the present invention is to provide a complete machine optimization design method for a radial flow turbine flow passage component, including a one-dimensional optimization design, an initial shape design of a flow passage component, and an optimized design method (a platform).
- the invention provides a radial flow hydraulic turbine optimization design method, comprising a one-dimensional thermal optimization design method, a three-dimensional modeling method of a flow component and a whole machine optimization method; wherein the overall machine optimization method comprises the following steps: nozzle guide vane and Impeller blade parameterization step, co-evolutionary genetic algorithm, adaptive approximation model, and CFD (Computational Fluid Dynamics) automatic calling algorithm.
- the radial flow hydraulic turbine optimization design method is as follows:
- the initial shape of the flow-through component is designed, including nozzle vane shape, impeller meter and volute design; (3) Perform CFD analysis on the flow field of the through-flow components such as the volute, nozzle, impeller, etc. in the whole machine environment, obtain the performance data of the initial design, and analyze the flow loss;
- the algorithm has the ability to deal with multi-variable highly nonlinear problems; because the original problem is reasonably segmented on the basis of considering the correlation of variables, considering the correlation between sub-problems, at the maximum On the basis of retaining the characteristics of the original problem, the amount of calculation required for optimization is reduced;
- (8M is used in the optimization process, using the dynamic sampling strategy to update the approximate model, automatically calling fewer CFD calculations, continuously improving the accuracy of the model in the potential optimal region, and improving the optimization efficiency;
- the one-way thermal optimization method includes the following steps:
- the one-dimensional thermal design uses the genetic algorithm to automatically complete the optimization process through the computer, while the non-traditional relies on continuous trial and error;
- the whole machine optimization method includes the following steps:
- the modules of the optimization method are not simply sequenced, but are organically integrated.
- CFD needs to be called to complete the establishment of the initial sample database, and the optimization algorithm is called to complete the approximation.
- the fitting work of the model; the fitted approximation model is used as the objective function to guide the optimization; in the process of optimization, the CFD calculation is called according to the needs of the algorithm calculation, and the appropriate sample points are added.
- the accuracy of the approximate model in the potential optimal region is updated.
- both the optimization algorithm and the CFD are called, and the approximate model is updated at the same time.
- the purpose of the one-dimensional thermal optimization design is to satisfy various constraints within the range of parameter values, match the relevant design parameters of each component, determine the diameter of the impeller inlet and outlet, the speed triangle, and the shape of the blade wheel, to lay the foundation for the design of the three-dimensional flow channel. .
- the wheel cycle efficiency is selected as the objective function, the corresponding dimensionless parameter is the design variable, various constraints are given, and the genetic algorithm is introduced to form a one-dimensional thermal optimization design method.
- the impeller wheel cycle efficiency ⁇ can be expressed as a function of the following dimensionless parameters: In the above formula
- D y Di wheel diameter ratio (average diameter of impeller outlet / impeller inlet diameter)
- the range of values for the above dimensionless parameters is largely determined based on empirical data combined with actual design requirements. Optimization needs to ensure a wide parameter search space as much as possible, but there is no too unreasonable parameter combination; depending on the application, the variable value range may be different, and it needs to be adjusted according to experience. For example, the following is a more appropriate range of variable values:
- the Mach number of the nozzle outlet is constrained by the reaction degree ⁇ : Proper selection of a large ⁇ can give full play to the advantage of using inertial force to work. However, if the ⁇ is too large, the impeller load will be too large, and the inside of the turbine will be The increase in external air leakage loss and the friction loss of the wheel also causes an insignificant increase, and the axial force that the rotor is subjected to increases accordingly. ⁇ should not be too small, otherwise c may be too large and exceed the local speed of sound.
- the relative leaf height is within a certain range and meets the minimum leaf height requirement: 0.03 ⁇ ⁇ 0.15, ⁇ 3mm
- Hydraulic turbines need to operate at fixed or variable flow rates in different processes.
- a fixed-angle nozzle configuration can be used, and the vanes are pneumatically shaped to reduce flow losses, as shown in Figure 1(a).
- an adjustable angle nozzle configuration is required to improve the performance of the hydraulic turbine. Since the rotating mechanism is to be mounted on the nozzle, the elongated pneumatic blade is no longer suitable, and it is necessary to find a suitable blade shape.
- Fig. 1(b) shows a guide vane type suitable for the adjustable structure.
- the three-dimensional shape of the impeller includes a meridian profile, a work wheel and an exit inducer design.
- the meridian lines of the wheel and the wheel cover are all elliptical.
- the working wheel blades take into account the strength requirements and are generally radial straight blades.
- the hydraulic turbine outlet inducer should meet several requirements: It has good hydraulic properties; the formed blade has better strength characteristics; it is easy to process and inspect.
- the non-expandable parabolic paraboloid of the cylindrical base has advantages in terms of hydraulic performance, strength, processing technology, etc., and can meet several requirements for the induction of vane type. Therefore, the present invention adopts a straight-line paraboloid with a non-expandable cylindrical surface to face the wind deflector for blade modeling. As shown in Figure 3, through the impeller axis The plane is called the meridional plane, the plane perpendicular to the axis of rotation of the impeller is called the radial plane, and the end surface perpendicular to the axis of rotation of the impeller is the radial end surface.
- Fig. 4 is the program flow chart.
- the volute consists of three parts: the inlet tube, the coil tube and the ring accelerator.
- the ternary flow in the volute is simplified to a constant flow of binary adiabatic, and it is assumed that the mass of the liquid of a certain section of the scroll is concentrated on the core of the section. Therefore, by determining the variation of the fluid parameters along the corrugated section core connection line, it is possible to understand the fluid flow in the scroll and design the volute accordingly.
- the flow rate of the working fluid passing through any section F of the scroll tube is in the following relationship with the cross-sectional azimuth angle ⁇ and the number of scroll tubes Z v :
- ⁇ is the height of the volute, is the radius of the section circle, is the width of the nozzle blade, is the number of speed, is the azimuth angle, 0 ⁇ is the liquid exit angle, and the azimuth angle 0 in each of the above calculation formulas appears in an implicit form.
- the parameters of a given section can be solved by computer programming to design the volute. 3.
- Parametric expression of the nozzle blades is carried out using two B-spline curves (which can also be described by Bezier curves or NURBS).
- control points are selected to control the upper and lower curves.
- the blade tail and the leading edge points (points 1 and 8) are fixed; to reduce the control variables used, the shape of the nozzle vanes is changed only by changing the ordinates of the remaining control points (a total of 6 variables).
- the nozzle mounting angle is also used as an optimization variable and is determined by performance optimization, as shown in Figure 503). For adjustable nozzles, a total of 7 variables are used to parameterize the nozzle vanes.
- the elliptical curve is used for the leaf wheel noon line
- the radial straight blades are used for the working wheel
- the induction wheel is described by the cylindrical-parabolic equation.
- the parameterization of the impeller blades is based on the initial geometry of the blades.
- the five modeling parameters c ⁇ c ⁇ A ⁇ and ⁇ 3 ⁇ 4 are selected as the optimized variables for the impeller blades.
- the optimized design of the hydraulic turbine needs to be carried out in the whole machine environment.
- the CFD analysis is carried out in the whole machine environment, and the parameter optimization method and the advanced co-evolutionary genetic algorithm (CCGA) are combined to establish a complete design method of the hydraulic turbine.
- CCGA advanced co-evolutionary genetic algorithm
- the objective function is a combination of the two, expressed as
- Pr represents the expansion ratio of the liquid expander
- Pr° is the expansion ratio of the initial design
- cnc 2 is the empirical coefficient
- the optimization platform consists of four main modules: parametric generation of nozzle vanes and impeller blades, co-evolutionary genetic algorithm (CCGA), adaptive approximation model technique, and CFD Automatic call calculations.
- CCGA co-evolutionary genetic algorithm
- adaptive approximation model technique adaptive approximation model technique
- CFD Automatic call calculations CFD Automatic call calculations.
- these four modules are organically integrated. The figure shows the flow chart of the optimization platform. A detailed description of each module is given below.
- Parametric module parameterize the blade of the nozzle by using the spline curve, change the profile of the nozzle blade by changing the coordinates of the control point; if it is an adjustable nozzle, it can also describe the change of the installation angle of the nozzle blade; -
- the parabolic method expresses the impeller blades, and the impeller design can be modified by adjusting the geometric parameters. The above method is implemented by the program and is conveniently outputted in the CFD software data interface format to automatically generate nozzle and impeller blade data during the optimization process.
- Approximate model module Construct a certain number of group sample designs, and perform CFD analysis on the samples in the whole environment to obtain the objective function values to establish the approximate model for initialization. In the subsequent optimization calculation, this approximation model is used to replace the time-consuming CFD calculation to complete the objective function evaluation and accelerate the optimization process. In the optimization process, new points are added according to the algorithm needs to improve the potential model. The most advantageous prediction accuracy.
- Variable grouping algorithm module The key problem in the co-evolution algorithm is reasonable variable grouping.
- correlation data between different variables is obtained by statistically distributing distribution data of individual populations of genetic algorithms.
- the optimization variables are divided into multiple groups (ie, variable space segmentation) to optimize the calculation using the co-evolution genetic algorithm.
- Co-evolutionary Genetic Algorithm (CCGA) module Co-evolutionary genetic algorithm divides a complex multivariate optimization problem into multiple relatively independent sub-problems, and uses genetic algorithm to solve each sub-problem one by one. Reasonable segmentation of the problem based on the correlation between variables can effectively reduce the amount of computation required for optimization. Since each genetic algorithm individual has only a part of the optimization variables, when it is necessary to calculate a candidate individual objective function value, it needs to be combined with variables from other populations to obtain the objective function of the candidate individual. DRAWINGS
- Figure 1 (a) and (b) show the fixed mounting angle and the adjustable mounting angle nozzle vane pattern.
- Figure 2 Schematic diagram of the impeller meridian plane.
- Figure 3 is a schematic view of an impeller blade.
- the origin 0 is selected on the impeller rotation axis O.
- the length Y of the arc on the 0-angle and the radial plane is positive when it is the same as the direction of rotation of the impeller, and vice versa, and is calculated from the mid-surface of a certain working wheel blade.
- O. The axis of the center paraboloid. It is assumed that the intersection of the central paraboloid and the outer end face is a straight line and passes through this axis.
- O and O The distance between the two shafts is R a and the angle of the top of the blade is reduced!
- ⁇ is a positive value of the axial projection of the angle between the intersection of the central parabola and the outer end face and the radial line at the average radius, and the angle ⁇ of the blade top wrap angle is also positive.
- Fig. 5 is a schematic diagram of parameterization and adjustable installation angle of the nozzle guide vane.
- Figure 6 shows a schematic diagram of how to implement automatic CFD call during the optimization process of the hydraulic turbine.
- Figure 7 shows the flow chart of the hydraulic turbine optimization design program platform. detailed description
- the initial shape of the flow-through component is designed, including the nozzle guide vane shape, the impeller meter, and the volute design.
- a fixed-mount angle nozzle configuration is recommended, and the vanes are pneumatically shaped to reduce flow losses, as shown in Figure 1 (a).
- Figure 1 (a) For hydraulic turbines with variable flow operation, in order to improve the hydraulic turbine's changing conditions The performance requires the use of an adjustable angle nozzle structure, which in turn requires the use of a vane type suitable for adjustable structural requirements, Figure l(b).
- the three-dimensional shape of the impeller includes a meridian profile, a work wheel and an exit inducer design. As shown in Fig.
- the meridian line of the hydraulic turbine impeller wheel and wheel cover adopts an elliptic curve
- the working wheel blades are radial straight blades
- the exit induction wheel adopts a cylindrical base surface non-expandable straight grain parabolic surface guide.
- the wind wheel performs blade shape.
- Figures 3(a), (), and (c) show the meridional projection of the impeller, the projection, and the development of the cylindrical section of the induction wheel. According to the above scheme, the numerical simulation and computer programming make it easy to realize three-dimensional forming of the impeller.
- Figure 4 shows the flow chart of the impeller design procedure.
- Equation (4) gives the relationship of the geometric parameters of the volute.
- the parameterization of the geometry is performed and the optimized design variables are extracted.
- the suction and pressure surfaces of the nozzle vanes are fitted by two spline curves, and the coordinate values of the control points are obtained, which are used as the initial design expression, and some coordinate values are reasonably selected as the parameters of the nozzle airfoil optimization.
- Variable For adjustable nozzles, 1 variable can be added to indicate the nozzle mounting angle change.
- the impeller is parameterized and five variables ⁇ , ⁇ are selected. , ⁇ and as an optimization variable for the impeller blades, as shown in Figures 3(a), (b) and (c).
- ⁇ and as an optimization variable for the impeller blades, as shown in Figures 3(a), (b) and (c).
- 12 variables were used to parameterize the nozzle and impeller of the liquid expander. Six of these variables are used to control nozzle blade changes, one variable is used to control nozzle mounting angle changes, and five variables are used to optimize the impeller.
- Equation (5) gives its mathematical expression.
- a CFD-based optimization platform is established, which is suitable for the optimization of hydraulic turbine level.
- the automatic call of CFD is completed through a series of own programs and batch scripts to complete CFD analysis including candidate blade profile generation, grid.
- the process of partitioning, CFD setup and solver auto-solving, and numerical result acquisition is convenient for integration with the optimization program.
- the process is shown in Figure 6.
- Figure 7 is a flow chart of the optimized design platform, which mainly includes four modules: nozzle vane and impeller blade parameterization, co-evolutionary genetic algorithm, adaptive approximation model technology, and CFD automatic call.
- the optimization method effectively reduces the amount of calculation and accelerates the optimization convergence by the following measures: Using the approximate model to predict the objective function instead of calling the time-consuming CFD calculation each time; Using the approximate model algorithm with automatic update capability, continuously improve the model Improve the accuracy of the optimal optimal area and improve the efficiency of optimization.
- the introduction of co-evolutionary algorithms makes the algorithm capable of dealing with multivariable highly nonlinear problems.
- variable grouping algorithm detecting the (tight or loose) quantitative relationship between variables, segmenting a complex multivariate optimization problem into multiple relatively independent sub-problems (dividing the optimization variables into multiple groups) and using the genetic algorithm Solve each sub-problem one by one; based on the correlation between variables, reasonably segment the problem, consider the correlation between sub-problems, and effectively reduce the optimization problem based on the maximum retention of the original problem characteristics. The amount of calculation required.
- the adaptive genetic operator is used in the algorithm to improve the global search ability of the co-evolutionary algorithm and accelerate convergence.
- the modules of the optimization platform are not simply sequenced, but are organically integrated.
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Citations (4)
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CN1724847A (zh) * | 2004-07-22 | 2006-01-25 | 中国科学院工程热物理研究所 | 径流式涡轮径向元素叶轮等强度叶片造型及其方法 |
CN1828024A (zh) * | 2005-03-04 | 2006-09-06 | 徐大懋 | 提高能量转换效率的叶轮机械叶片设计方法 |
CN1847664A (zh) * | 2006-04-07 | 2006-10-18 | 刘昌喆 | 径流叶栅压气机 |
CN101915130A (zh) * | 2010-06-25 | 2010-12-15 | 北京理工大学 | 可变几何涡轮增压器喷嘴环三维叶片及其设计方法 |
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Patent Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
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CN1724847A (zh) * | 2004-07-22 | 2006-01-25 | 中国科学院工程热物理研究所 | 径流式涡轮径向元素叶轮等强度叶片造型及其方法 |
CN1828024A (zh) * | 2005-03-04 | 2006-09-06 | 徐大懋 | 提高能量转换效率的叶轮机械叶片设计方法 |
CN1847664A (zh) * | 2006-04-07 | 2006-10-18 | 刘昌喆 | 径流叶栅压气机 |
CN101915130A (zh) * | 2010-06-25 | 2010-12-15 | 北京理工大学 | 可变几何涡轮增压器喷嘴环三维叶片及其设计方法 |
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