CN113107606B - Thermodynamic calculation and design algorithm for transverse stage of steam turbine - Google Patents
Thermodynamic calculation and design algorithm for transverse stage of steam turbine Download PDFInfo
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
- F01D21/003—Arrangements for testing or measuring
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/141—Shape, i.e. outer, aerodynamic form
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow blades
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
- F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06T—IMAGE DATA PROCESSING OR GENERATION, IN GENERAL
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Abstract
A calculation and design algorithm for the thermodynamic power of a transverse stage of a steam turbine belongs to the technical field of steam turbines. The method aims to solve the problems that a three-dimensional CFD is adopted for design in a traditional design algorithm, the design process is complex, the design accuracy cannot be guaranteed, and the working efficiency is low. The method of iterative iteration by adopting the three-dimensional CFD method has complex process, one scheme needs about 20-30 working hours, and the time is longer if the model selection problem is considered. By adopting the method, one scheme can be controlled within 3 working hours even if the type selection is considered, and the period is shortened by about 90 percent. After a plurality of schemes are needed in consideration of engineering design, the final construction scheme can be determined, and the time is saved remarkably. The method is suitable for designing and calculating the transverse stage of the steam turbine.
Description
Technical Field
The invention relates to the technical field of steam turbines, in particular to a thermodynamic calculation and design algorithm for a transverse stage of a steam turbine.
Background
In recent years, with the increase in the capacity of a steam turbine unit, a structure of full-cycle steam admission and a steam supplement valve has appeared. In order to adapt to the whole-cycle steam admission, the arrangement mode of a volute and a transverse stage is required. The transverse stage is different from the traditional axial flow stage and the traditional centripetal stage, no mature one-dimensional design method exists at present, and a three-dimensional CFD method is required. The traditional axial flow stage and centripetal stage have the same parameters of a static blade outlet and a movable blade inlet, while the transverse stage and the centripetal stage have different positions and greatly change thermal parameters. The transverse stage design not only needs to consider one-dimensional thermodynamic calculation, movable and static blade matching and the like, but also influences the through-flow capacity of the unit, and the adoption of a three-dimensional CFD process is complicated and seriously restricts the development of a steam turbine.
In summary, the conventional design algorithm is designed by using three-dimensional CFD, which is a complicated design process, and cannot ensure the design accuracy, and the working efficiency is low.
Disclosure of Invention
The invention provides a thermal calculation and design algorithm for a transverse stage of a steam turbine, aiming at solving the problems that the traditional design algorithm is designed by adopting three-dimensional CFD (computational fluid dynamics), the design process is complex, the design accuracy cannot be ensured, and the working efficiency is low.
The invention relates to a thermodynamic calculation method for a transverse stage of a steam turbine, which comprises the following specific algorithms:
step one, simplifying a volute and a transverse stage into a traditional axial flow stage according to a traditional design idea, carrying out through-flow design, and determining thermal and geometric parameters;
step two, extracting boundary conditions from the result of the step one, and using the boundary conditions as input data of the method of the invention, wherein the input data comprises static pressure p behind the movable blade 4 Static enthalpy i 4 A flow rate G; total enthalpy of volute inlet
And the total pressure of the inlet is greater or less than>
Height L of moving blade 4 Pitch diameter D of the moving blade 4 Angle beta of outlet of moving blade relative to steam flow 4 (ii) a The rotation speed omega; effective enthalpy drop>
Step three, according to the static pressure p behind the movable blades 4 Static enthalpy i 4 Determining the density rho by means of a water vapor calculation program 4 ；
Step four, calculating the linear velocity of the outlet of the movable blade
According to the conservation of mass, the axial velocity C behind the movable blade is obtained 4z ；
Step five, solving the tangential velocity C of the outlet of the movable blade according to the velocity triangle 4u ；
Sixthly, the outlet relative speed of the movable blade
Step seven, setting a movable blade speed coefficient psi;
step eight, assuming the axial speed C of the inlet of the movable blade 3Z ；
Ninth, axial speed of inlet of movable vane
Step ten, moving blade inlet is absoluteSpeed C 3 ；
Eleven, according to the conservation of energy, the total enthalpy of the inlet of the movable vane
And the total enthalpy of the volute inlet>
Equal, calculate the static enthalpy at the inlet of the movable vane->
Is prepared from (i) 3 ，ρ 3 ) Investigating the water vapour table 3 ；
Step twelve, inlet density of moving blade
Is prepared from (i) 3 ,ρ 3 ) Obtaining the inlet entropy s of the movable vane by adopting a water vapor calculation program 3 (ii) a Is composed of(s) 3 ，p 4 ) Adopting a water vapor calculation program to obtain the isentropic enthalpy drop i of the movable blades 4s (ii) a By Δ h 4 ＝i 4 -i 4s To calculate the isentropic relative speed of the outlet of the movable vane>
Moving vane outlet relative speed>
Step thirteen, comparing W calculated in step twelve 4 W with step six 4 If the relative error is less than 10 -4 Continuing to the next step; otherwise, revision C 3 z, repeating the steps nine to twelve until the W of the step twelve and the step six 4 Relative error less than 10 -4 (ii) a Through the steps, all thermodynamic parameters, speed components and geometric parameters before and after the movable blade can be obtained;
fourteen, setting a speed coefficient epsilon from a section 2-2 to a section 3-3 of the computing station; according to the law of circular quantity, the tangential velocity of the outlet of the stator blade 3
Fifthly, obtaining all thermal parameters, velocity components and geometric parameters of the outlet of the stationary blade 3 by imitating the processes from the seventh step to the thirteenth step;
sixthly, obtaining the tangential speed of the volute inlet according to the thermal parameters of the volute inlet in the step one
Then, the total energy loss coefficient xi and the volute speed coefficient from the 0-0 section to the 4-4 section of the calculation station are obtained
Psi is the bucket velocity coefficient; according to the ring quantity theorem, the tangential speed of the stator vane inlet>
Seventhly, obtaining all thermal parameters, speed components and geometric parameters of the inlet of the stationary blade 3 by imitating the processes from the seventh step to the thirteenth step;
further, C calculated in the fourth step 4z Is calculated by the formula C 4z ＝G/)C 4z *π*D 4 *L 4 *ρ 4 )；
Further, in the fifth step, according to the velocity triangle, the formula for obtaining the tangential velocity of the outlet of the movable blade is C 4u ＝C 4z *tan(β 4 )-U 4 ；
Further, the absolute speed C of the inlet of the movable blade is calculated in the step ten 3 Is of the formula
The invention relates to a design algorithm of a turbine transverse stage, which comprises the following specific steps:
step one, transversely placing a fixed blade inlet steam flow angle
Step two, according to a 1 Selecting proper transverse stator blade molded line to ensure the geometric angle of molded line inlet and a in Respectively meet the design standard;
and step three, determining the relative grid distance T/b corresponding to the highest efficiency point by combining the molded line loss library according to the selected stator blade molded line. Note that T here is the pitch corresponding to the pitch circle diameter;
step four, transversely arranging the steam flow angle of the stationary blade outlet
Note that t here is the pitch of the steam outlet side pitch circle diameter pair;
step five, according to a out And determining the installation angle gamma of the transverse static blade so as to complete transverse static blade selection.
Compared with the prior art, the invention has the following beneficial effects:
the invention overcomes the defects of the prior art and thoroughly solves the problem that the transverse stage of the steam turbine is lack of an effective one-dimensional program. In the traditional method, overall parameters such as transverse enthalpy drop and loss are distributed according to axial flow calculation in one dimension, and a three-dimensional CFD method is adopted to iterate repeatedly to obtain a result meeting the requirement, even the problem that the one-dimensional requirement cannot be met and the one-dimensional calculation needs to be modified again occurs;
the design period is greatly shortened, and the working efficiency is improved. The method of iterative iteration by adopting the three-dimensional CFD method has complex process, one scheme needs about 20-30 working hours, and the time is longer if the model selection problem is considered. By adopting the method, one scheme can be controlled within 3 working hours even if the type selection is considered, and the period is shortened by about 90 percent. After a plurality of schemes are needed in consideration of engineering design, the final construction scheme can be determined, and the time is saved remarkably;
the precision completely meets the design requirements. The calculation method of the invention is based on the basic principles of fluid mechanics and impeller machinery, and corrects the speed coefficient (namely loss) which only affects the precision based on a large amount of three-dimensional CFD results, and the error between the speed coefficient and the three-dimensional CFD results can be controlled within 3%.
The invention carries out program embedding aiming at the particularity of the selection of the transverse stationary blade, and can realize the combined design of one-dimensional calculation and selection. The invention is suitable for all turbine horizontal stage structures such as a plurality of inlets of the volute, double split flow of the movable blade and the like, and has wide applicability.
Drawings
FIG. 1 is a schematic diagram of a prior art horizontal stage computing station;
FIG. 2 is a schematic diagram of a prior art axial flow computing station;
FIG. 3 is a schematic diagram of a prior art centrifugal stage computing station;
FIG. 4 is a schematic diagram of a turbine cross-stage thermodynamic computing plant according to the present invention;
FIG. 5 is a cross-stage vane sizing graph of a turbine cross-stage design algorithm in accordance with the present invention;
FIG. 6 is a volute dual-inlet configuration of the present invention;
FIG. 7 is a cross-level dual-split architecture of the present invention;
the figure includes a transverse vane 1, a blade 2, and a vane 3.
Detailed Description
The first embodiment is as follows: the present embodiment is described with reference to fig. 1 to 7, and a specific algorithm of the thermodynamic calculation of the turbine transverse stage according to the present embodiment is as follows:
step one, simplifying a volute and a transverse stage into a traditional axial flow stage according to a traditional design thought, carrying out through flow design, and determining thermal and geometric parameters;
step two, extracting boundary conditions from the result of the step one, and using the boundary conditions as input data of the method of the invention, wherein the input data comprises static pressure p behind the movable blade 4 Static enthalpy i 4 A flow rate G; total enthalpy of volute inlet
And the total pressure of the inlet is greater or less than>
Height L of moving blade 4 Diameter of pitch circle of moving blade D 4 Angle beta of outlet of moving blade relative to steam flow 4 (ii) a The rotation speed omega; effective enthalpy drop>
Step three, according to the static pressure p behind the movable blades 4 Static enthalpy i 4 Determining the density rho by means of a water vapor calculation program 4 ；
Step four, calculating the linear velocity of the outlet of the movable blade
According to the conservation of mass, the axial velocity C behind the movable blade is obtained 4z ；
Step five, solving the tangential velocity C of the outlet of the movable blade according to the velocity triangle 4u ；
Sixthly, the outlet relative speed of the movable blade
Step seven, setting a movable blade speed coefficient psi;
step eight, assuming the axial speed C of the inlet of the movable blade 3Z ；
Ninth, axial speed of inlet of movable vane
Step ten, moving blade inlet absolute speed C 3 ；
Eleven, according to the conservation of energy, the total enthalpy of the inlet of the movable vane
And the total enthalpy of the volute inlet>
Equal, calculate the static enthalpy at the inlet of the movable vane->
Is prepared from (i) 3 ，ρ 3 ) Investigating the water vapour table 3 ；
Step twelve, inlet density of moving blade
Is prepared from (i) 3 ,ρ 3 ) Obtaining the inlet entropy s of the movable vane by adopting a water vapor calculation program 3 (ii) a Is composed of(s) 3 ，p 4 ) Adopting a water vapor calculation program to obtain the isentropic enthalpy drop i of the movable blades 4s (ii) a By Δ h 4 ＝i 4 -i 4s To calculate the isentropic relative speed of the outlet of the movable vane>
Moving vane outlet relative speed>
Step thirteen, comparing the W calculated in the step twelve 4 W with step six 4 If the relative error is less than 10 -4 Continuing the next step; otherwise, revision C 3 z, repeating the steps nine to twelve until the W of the step twelve and the step six 4 Relative error less than 10 -4 (ii) a Through the steps, all thermodynamic parameters, speed components and geometric parameters before and after the movable blade can be obtained;
fourteen, setting a speed coefficient epsilon from a section 2-2 to a section 3-3 of the computing station; according to the law of circular quantity, the tangential velocity of the outlet of the stator blade 3
Fifthly, obtaining all thermal parameters, velocity components and geometric parameters of the outlet of the stationary blade 3 by imitating the processes from the seventh step to the thirteenth step;
sixthly, obtaining the tangential speed of the volute inlet according to the thermal parameters of the volute inlet in the step one
Re-solving computing stationTotal energy loss coefficient xi and volute velocity coefficient from 0-0 section to 4-4 section
Psi is the bucket velocity coefficient; according to the ring quantity theorem, the tangential speed of the stator vane inlet>
Seventhly, obtaining all thermal parameters, speed components and geometric parameters of the inlet of the static blade 3 by imitating the process from the step seven to the step thirteen.
The second embodiment is as follows: the present embodiment will be described with reference to fig. 1, and the present embodiment is a further limitation of the thermodynamic calculation described in the first embodiment, the thermodynamic calculation of the turbine horizontal stage in the present embodiment, and C calculated in the fourth step 4z Is calculated by the formula C 4z ＝G/(C 4z *π*D 4 *L 4 *ρ 4 )。
The third concrete implementation mode: the present embodiment will be described with reference to fig. 1, which is a further limitation of the thermodynamic calculation described in the first embodiment, and in the thermodynamic calculation of a turbine horizontal stage described in the present embodiment, the equation for determining the tangential velocity of the outlet of the rotor blade from the velocity triangle in the fifth step is C 4u ＝C 4z *tan(β 4 )-U 4 。
The fourth concrete implementation mode: the present embodiment will be described with reference to fig. 1, and the present embodiment is a further limitation of the thermodynamic calculation described in the first embodiment, and in the thermodynamic calculation of the turbine horizontal stage described in the present embodiment, the absolute speed C of the inlet of the rotor blade is calculated in the tenth step 3 Is of the formula
The fifth concrete implementation mode: the present embodiment is described with reference to fig. 1 to 7, and the design algorithm of the turbine transverse stage according to the present embodiment specifically includes the following steps:
step one, transversely placing a fixed blade inlet steam flow angle
Step two, according to a 1 Selecting proper transverse stator blade molded line to ensure the geometric angle of molded line inlet and a in Respectively meet the design standard;
and step three, determining the relative grid distance T/b corresponding to the highest efficiency point by combining the molded line loss library according to the selected stator blade molded line. Note that T here is the pitch corresponding to the pitch circle diameter;
step four, transversely arranging the steam flow angle of the stationary blade outlet
Note that t here is the pitch of the steam outlet side pitch circle diameter pair;
step five, according to a out And determining the installation angle gamma of the transverse static blade so as to complete transverse static blade selection.
The sixth specific implementation mode: the present embodiment is described with reference to fig. 1 to 7, and a specific algorithm of the thermodynamic calculation of the turbine transverse stage according to the present embodiment is as follows: taking an N660-31/600/620/620 type ultra-supercritical secondary reheat extraction condensing steam turbine as an example, the method of the invention is used for calculating the parameters of a high-pressure single-flow transverse stage, and the calculation results of typical parameters are shown in the following table:
| parameter name | Unit of | Three dimensional CFD results | The invention calculates the result | And three-dimensional CFD error |
| Flow rate | t/h | 1489.92 | 1501.1 | +0.75％ |
| Static pressure behind the moving blade | MPa | 8.51 | 8.51 | 0.0％ |
| Static pressure in front of moving blade | MPa | 8.76 | 8.85 | +1.03％ |
| Static pressure behind stationary blade | MPa | 8.87 | 8.78 | -1.01％ |
| Static pressure before stationary blade | MPa | 9.09 | 9.14 | +0.56％ |
| Rear velocity of moving blade | m/s | 60.21 | 60.5 | +0.48％ |
| Forward speed of moving blade | m/s | 173.39 | 175.33 | +1.12％ |
| Stator blade rear velocity | m/s | 144.99 | 143.12 | -1.29％ |
| Stator blade front velocity | m/s | 48.87 | 49.03 | +0.32％ |
The seventh embodiment: the present embodiment is described with reference to fig. 1 to 7, and a specific algorithm of the thermodynamic calculation of the turbine transverse stage according to the present embodiment is as follows: taking an N660-31/600/620/620 type ultra-supercritical double-reheat extraction condensing steam turbine as an example, the method of the invention is used for calculating the parameters of the low-pressure double-flow-direction transverse stage, and the calculation results of typical parameters are shown in the following table:
| parameter name | Unit of | Three dimensional CFD results | The invention calculates the result | Error from three-dimensional CFD |
| Flow rate | t/h | 601.44 | 598.12 | -0.55％ |
| Static pressure behind the moving blade | MPa | 0.53 | 0.54 | +1.88％ |
| Static pressure in front of moving blade | MPa | 0.64 | 0.63 | -1.56％ |
| Static pressure behind stationary blade | MPa | 0.68 | 0.66 | -2.94％ |
| Static pressure before stationary blade | MPa | 0.80 | 0.82 | +2.50％ |
| Rear velocity of moving blade | m/s | 81.50 | 82.47 | +1.19％ |
| Forward speed of moving blade | m/s | 359.58 | 371.29 | +3.26％ |
| Stator blade rear velocity | m/s | 324.20 | 314.33 | -3.04％ |
| Stator blade front velocity | m/s | 131.80 | 134.37 | +1.95％ |
The physical meaning of the variables in the invention is as follows:
variables are as follows: subscripts:
p: static pressure 0: calculated value 0
i: static enthalpy 1: computing station 1
G: and (3) flow rate 2: computing station 2
L: leaf height 3: computing station 3
D: pitch circle diameter 4: computing station 4
Beta: relative steam flow angle of the outlet of the movable blade 5: computing station 5
Omega: rotating speed s: isentropic
z: axial component
H u : effective enthalpy drop
ρ: density u: tangential component
U: linear velocity r: radial component
Psi: moving blade velocity coefficient in: stationary blade steam inlet side
C: resultant velocity out: stationary blade steam outlet side
s: entropy of the entropy
Epsilon: speed coefficient of computing station 2-computing station 3
W: relative velocity
Δ h: static-isentropic enthalpy
r: radius of the pipe
O: size of throat
t: pitch of
T: pitch of
γ: mounting angle
Xi: calculating total energy loss coefficients for stations 0-0 to 4-4
μ: coefficient of volute velocity
Claims (5)
1. A thermal calculation algorithm for a transverse stage of a steam turbine is characterized in that: the specific algorithm is as follows:
step one, simplifying a volute and a transverse stage into a traditional axial flow stage according to a traditional design idea, carrying out through-flow design, and determining thermal and geometric parameters;
step two, extracting boundary conditions from the result of the step one, and using the boundary conditions as input data of an algorithm, wherein the input data comprises static pressure p behind the movable blade 4 Static enthalpy i 4 A flow rate G; total enthalpy of volute inlet
Inlet total pressure
Height L of movable vane 4 Diameter of pitch circle of moving blade D 4 Angle of relative flow of outlet of rotor blade beta 4 (ii) a The rotation speed omega; effective enthalpy drop
Step three, according to the static pressure p behind the movable blades 4 Static enthalpy i 4 Determining the density rho by means of a water vapor calculation program 4 ；
Step four, calculating the linear velocity of the outlet of the movable blade
According to the conservation of mass, the axial velocity C behind the movable blade is obtained 4z ；
Step five, solving the tangential velocity C of the outlet of the movable blade according to the velocity triangle 4u ；
Sixthly, the outlet relative speed of the movable blade
Step seven, setting a movable blade speed coefficient psi;
step eight, assuming the axial speed C of the inlet of the movable blade 3Z ；
Ninth, axial speed of inlet of movable vane
Step ten, moving blade inlet absolute speed C 3 ；
Eleven, according to the conservation of energy, the total enthalpy of the inlet of the movable vane
And total enthalpy of volute inlet
Equality, calculating static enthalpy of inlet of moving blade
Is prepared from (i) 3 ,ρ 3 ) Investigating the water vapour table 3 ；
Step twelve, inlet density of moving blade
Wherein L is a Is leaf height, D a Is the pitch circle diameter; is prepared from (i) 3 ,ρ 3 ) Obtaining the inlet entropy s of the movable vane by adopting a water vapor calculation program 3 (ii) a Is composed of(s) 3 ，p 4 ) Adopting a water vapor calculation program to obtain the isentropic enthalpy drop i of the movable blades 4s (ii) a By Δ h 4 ＝i 4 -i 4s To obtain the isentropic relative velocity of the outlet of the movable vane
Relative speed of outlet of moving blade
Step thirteen, comparing W calculated in step twelve 4 W with step six 4 If the relative error is less than 10 -4 Continuing to the next step; otherwise, revision C 3 z, repeating the steps nine to twelve until the W of the step twelve and the step six 4 Relative error less than 10 -4 (ii) a Through the steps, all thermodynamic parameters, speed components and geometric parameters in front of the movable blade and behind the movable blade are obtained;
fourteen, setting a speed coefficient epsilon from a section 2-2 to a section 3-3 of the computing station; according to the law of circular quantity, the outlet tangential velocity of the stator blade (3)
Wherein D a Is the pitch circle diameter; c 3u For calculating the resultant velocity of the tangential components of station 3, D 2 To calculate the diameter of the station 2;
fifthly, obtaining all thermal parameters, velocity components and geometric parameters of the outlet of the stationary blade (3) by imitating the processes from the seventh step to the thirteenth step;
sixthly, obtaining the tangential speed of the volute inlet according to the thermal parameters of the volute inlet in the first step
Then, the total energy loss coefficient xi and the volute speed coefficient from the 0-0 section to the 4-4 section of the calculation station are obtained
Psi is the bucket velocity coefficient; according to the law of circular quantity, stator blade inlet tangential velocity
Wherein μ is a volute velocity coefficient;
seventhly, obtaining all thermodynamic parameters, velocity components and geometric parameters of the inlet of the static blade (3) by imitating the process from the step seven to the step thirteen.
2. The turbine transverse stage thermodynamic calculation algorithm according to claim 1, wherein: c calculated in the step four 4z Is calculated by the formula C 4z ＝G/(C 4z *π*D 4 *L 4 *ρ 4 )。
3. The turbine transverse stage thermodynamic calculation algorithm according to claim 1, wherein: in the step five, according to the velocity triangle, the formula for solving the tangential velocity of the outlet of the movable blade is C 4u ＝C 4z *tan(β 4 )-U 4 。
4. The turbine transverse stage thermodynamic calculation algorithm according to claim 1, wherein: in the step ten, the absolute speed C of the inlet of the movable blade is calculated 3 Is of the formula
5. The turbine transverse stage thermodynamic calculation algorithm according to claim 1, wherein: the design algorithm of the turbine transverse stage is as follows:
step one, transversely placing a fixed blade inlet steam flow angle
Wherein C is 1r Is stator blade inlet radial velocity, C 1u Is the stator blade inlet tangential velocity;
step two, according to a 1 Selecting proper transverse stator blade molded line to ensure molded line inlet geometric angle a 1 And a in Respectively meet the design standard;
thirdly, determining a relative grid distance T/b corresponding to the highest efficiency point by combining a molded line loss library according to the selected stator blade molded line; note that T here is the pitch corresponding to the pitch diameter, and b is the chord length;
step four, transversely arranging the steam flow angle of the stationary blade outlet
Note that t here is the pitch of the steam outlet side pitch circle diameter pair; c 2r To calculate the station 2 radial component resultant velocity, o is the throat size;
step five, according to a out And determining the installation angle gamma of the transverse static blade so as to complete transverse static blade selection.
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| JP2002349203A (en) * | 2001-05-24 | 2002-12-04 | National Institute For Materials Science | Virtual turbine calculation method |
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| DE19755982C2 (en) * | 1997-12-17 | 2000-05-31 | Abb Patent Gmbh | Guide vanes for use in the wet steam area of a steam turbine |
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