CN113279817B - Method for correcting influence of blade end rounding on flow - Google Patents
Method for correcting influence of blade end rounding on flow Download PDFInfo
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- CN113279817B CN113279817B CN202110639408.3A CN202110639408A CN113279817B CN 113279817 B CN113279817 B CN 113279817B CN 202110639408 A CN202110639408 A CN 202110639408A CN 113279817 B CN113279817 B CN 113279817B
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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
- 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
-
- 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
-
- 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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- 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
- Y02P—CLIMATE CHANGE MITIGATION TECHNOLOGIES IN THE PRODUCTION OR PROCESSING OF GOODS
- Y02P70/00—Climate change mitigation technologies in the production process for final industrial or consumer products
- Y02P70/50—Manufacturing or production processes characterised by the final manufactured product
Abstract
Blade end partMethod for correcting the influence of rounding on the flow. And more particularly to axial flow turbines. The invention aims to solve the problems that the prior engineering method cannot solve the influence of flow change caused by the rounding of the end part of the blade and correct the height of the working part of the blade. According to the relative size of the blade-end blade-shaped throat width O and the blade radius R, the invention determines a calculation formula for correction, and calculates the reduction value A of the flow areabCalculating the total flow area A of the blade without considering the radius by an integral method0Calculating the area correction coefficient DeltaACalculating the efficiency correction coefficient delta according to the full three-dimensional CFD loss librarybCalculating the total correction coefficient delta, calculating the partial height delta L of the corrected blade, and calculating the height of the corrected blade
To be provided with
And (5) repeating the first step to the eighth step for the original blade height, and obtaining the final corrected blade working part height when the correction coefficient result is convergence. The invention is used in the field of axial flow turbines.
Description
Technical Field
The invention relates to the field of axial flow turbines, in particular to a method for correcting influence of blade end rounding on flow.
Background
With the technical progress, the design of the axial flow turbine is being turned from 'rough' to 'fine', the conversion makes the flow control requirements higher, especially the flow control of the first few stages is very critical, and the balance between the turbine output and the efficiency needs to be made: the flow is too large, and the equipment efficiency is low; the flow is too small, and the output of the equipment is insufficient. The first few stages of the axial turbine are again the smallest height of the working part, the end rounding has a great influence and, if not taken into account, causes efficiency and output problems. Taking a blade with a working portion of 20mm height and root tip portion rounded R3mm as an example, consider a reduction in flow rate of about 10% after rounding.
Conventional designs do not account for the flow variation caused by blade tip rounding, but rather address this problem by leaving a large margin in the system design. The method enables the unit to deviate from a design point in the running process, the unit efficiency is seriously influenced, and particularly when the blades are short. There is also a literature that theoretical research is carried out by a full three-dimensional CFD method, but the influence of end rounding on the flow is influenced by factors such as the height of a working part of the blade, the rounding radius, the size of a throat part and the like, and the method cannot be popularized in engineering. Therefore, the research on an engineering method, considering the influence of the end rounding on the flow rate and correcting, is a problem to be solved urgently in the turbine 'fine' design.
In summary, the engineering method in the prior art cannot solve the problem that the flow change is affected and the height of the working part of the blade is corrected due to the rounding of the end part of the blade.
Disclosure of Invention
The invention provides a method for correcting the influence of the end rounding of the blade on the flow, aiming at solving the problems that the engineering method in the prior art cannot solve the influence of the end rounding of the blade on the flow change and correct the height of the working part of the blade.
The technical scheme of the invention is as follows:
a method for correcting the influence of blade tip rounding on flow comprises the following steps:
step one, determining a calculation formula adopted for correction according to the relative size of the blade profile throat width O and the blade radius R at the end part of the blade:
when the blade end blade profile throat width O is more than or equal to 2R, the situation is A, and the calculation formula adopted by correction is
A01＝2(R2-πR2/4)＝0.4292R2 (1)；
When the blade end blade profile throat width O is less than 2R, the situation is B, and the calculation formula adopted by correction is
Step two, calculating a reduction value A of the through flow areab：
The numerical value of the blade rounding is small relative to the height of the working part of the blade, so that the blade profile throat width O at the end part of the blade is not changed within the height of the blade rounding R along the blade height direction, and the flow area is simplified into a rectangle;
root blend integration is either case a or case B:
when the root rounding area is the case A, the blade rounding radius at this time is R1Calculating by adopting a calculation formula (1) in the step one, and adding R1The root rounding area obtained in the step (1) is A1；
When the root rounding area is the case B, the blade rounding radius at this time is R2Calculating by adopting a calculation formula (2) in the step one, and adding R2The root rounding area obtained in the step (2) is A2；
The top rounded surface integral is either case a or case B,
when the tip rounding area is the case A, the blade rounding radius at this time is R3Calculating by adopting a calculation formula (1) in the step one, and adding R3In the above-mentioned step (1), the rounded top portion has an area A3；
When the tip rounding area is the case B, the blade rounding radius at this time is R4Calculating by adopting a calculation formula (2) in the step one, and adding R4Brought into (1) to obtain a rounded top area A4；
Flow area reduction value AbThe sum of the area reductions caused between the root rounding area and the top rounding area in case a or B, respectively;
step three, calculating the total flow area A of the blade without considering the rounding by adopting an integral method0：
The values of the known blade segment height L and blade tip profile throat width O are substituted into equation (3) to yield a total flow area A without rounding0Wherein L is the height of the blade part and O is the throat width;
step four, calculating an area correction coefficient deltaA：
ΔA＝-Ab/A0 (4)；
Reducing the flow area in the second step by a value AbTotal flow area A in the third step0Is substituted into the formula (4), the area correction coefficient Delta is obtainedAA value of (d);
step five, calculating an efficiency correction coefficient delta according to the full three-dimensional CFD loss libraryb：
Calculating the flow without rounding according to the software of the full three-dimensional CFD loss library, calculating the flow with rounding, comparing the difference between the flow without rounding and the flow with rounding with the flow without rounding, and calculating the efficiencyCorrection factor deltab；
Step six, calculating a total correction coefficient delta:
will step four middle deltaAAnd Δ in step fivebThe value of (c) is substituted into the formula (5),
Δ＝ΔA+Δb (5)；
step seven, calculating the partial height delta L of the correction blade:
substituting the value of L in the third step and the value of delta in the sixth step into the formula (6),
ΔL＝Δ×L (6)；
step eight, calculating the height of the corrected blade
Substituting the value of L in the third step and the value of Delta L in the sixth step into the formula (7),
step nine, with
And (5) repeating the steps from the first step to the eighth step for the original blade height, and obtaining the final corrected blade working part height when the result of the correction coefficient is convergence.
Compared with the prior art, the invention has the following effects:
1. the invention corrects the problem of flow change caused by the rounding of the end part of the axial flow turbine blade and solves the problem of lack of a correction method.
2. The invention corrects the area of the main influence factor, and the correction adopts a formula derived from the geometric relationship; and for the correction of the secondary influence factor efficiency, a full three-dimensional CFD loss library mode is adopted, so that the precision is high, and the requirement of engineering design is completely met.
3. The invention fully considers the engineering problem and has high efficiency. According to the first-level consideration, the full three-dimensional CFD calculation needs two to three days, the calculation method only needs a few minutes, and the design period can be greatly shortened by considering dozens of levels of a unit.
4. In the flow correction process, the method adopts the simplest and most effective correction method in engineering, namely, the height of the working part of the blade is corrected, so that the method is in accordance with the mainstream design thought of the turbine, and the method has strong engineering and is convenient to popularize and apply.
5. The invention has wide application, and can be applied to both the stationary blade and the moving blade; the axial flow turbine can be applied to steam turbines, gas turbines and working media such as air, supercritical carbon dioxide and the like.
Drawings
FIG. 1 is a schematic view of a vane end without radius of the present invention;
FIG. 2 is a schematic view of a vane end having a radius in accordance with the present invention;
FIG. 3 is an enlarged view of a portion of FIG. 2 at C;
FIG. 4 is a schematic view of the end rounding of the present invention causing a reduction in flow area at D;
FIG. 5 is a schematic view of the root throat width of the present invention;
FIG. 6 is a view of the M1 orientation of FIG. 5 with the radius of the invention A;
FIG. 7 is a view of M1 of FIG. 5 under B radii of the present invention;
FIG. 8 is a schematic view of the top throat width of the present invention;
FIG. 9 is a view of the M2 orientation of FIG. 8 with a radius of the invention A;
FIG. 10 is a view of M2 of FIG. 8 with B radii of the present invention;
FIG. 11 is a schematic illustration of an exemplary stationary vane to which the present invention is applicable;
FIG. 12 is a cross-sectional view B-B of FIG. 11;
FIG. 13 is a top view of FIG. 12;
FIG. 14 is a schematic view of an exemplary rotor blade to which the present invention is applicable;
FIG. 15 is a cross-sectional view N-N of FIG. 14;
fig. 16 is a top view of fig. 14.
Detailed Description
The first embodiment is as follows: the present embodiment is described with reference to fig. 1 to 16, and a method for correcting the influence of the rounding of the blade tip on the flow rate of the present embodiment includes the steps of:
step one, determining a calculation formula adopted for correction according to the relative size of the blade profile throat width O and the blade radius R at the end part of the blade:
when the blade end blade profile throat width O is more than or equal to 2R, the situation is A, and the calculation formula adopted by correction is
A01＝2(R2-πR2/4)＝0.4292R2 (1)；
When the blade end blade profile throat width O is less than 2R, the situation is B, and the calculation formula adopted by correction is
Step two, calculating a reduction value A of the through flow areab：
The numerical value of the blade rounding is small relative to the height of the working part of the blade, so that the blade profile throat width O at the end part of the blade is not changed within the height of the blade rounding R along the blade height direction, and the flow area is simplified into a rectangle;
root blend integration is either case a or case B:
when the root rounding area is the case A, the blade rounding radius at this time is R1Calculating by adopting a calculation formula (1) in the step one, and adding R1The root rounding area obtained in the step (1) is A1；
When the root rounding area is the case B, the blade rounding radius at this time is R2Calculating by adopting a calculation formula (2) in the step one, and adding R2The root rounding area obtained in the step (2) is A2；
The top rounded surface integral is either case a or case B,
when the tip rounding area is the case A, the blade rounding radius at this time is R3Calculating by adopting a calculation formula (1) in the step one, and adding R3In the above-mentioned step (1), the rounded top portion has an area A3；
When the tip rounding area is the case B, the blade rounding radius at this time is R4Calculating by adopting a calculation formula (2) in the step one, and adding R4The area of the top rounding is A4；
Flow area reduction value AbIs the sum of the area reductions caused between the root rounding area and the top rounding area in case a or case B, respectively;
step three, calculating the total flow area A of the blade without considering the rounding by adopting an integral method0：
The values of the known blade segment height L and blade tip profile throat width O are substituted into equation (3) to yield a total flow area A without rounding0Wherein L is the height of the blade part and O is the throat width;
step four, calculating an area correction coefficient deltaA：
ΔA＝-Ab/A0 (4)；
Reducing the flow area in the second step by a value AbTotal flow area A in the third step0Is substituted into the formula (4), the area correction coefficient Delta is obtainedAA value of (d);
step five, calculating an efficiency correction coefficient delta according to a full three-dimensional CFD loss libraryb：
Calculating the flow without rounding according to the software of the full three-dimensional CFD loss library, calculating the flow with rounding, comparing the difference between the flow without rounding and the flow with rounding with the flow without rounding, and calculating the efficiency correction coefficient deltab；
Step six, calculating a total correction coefficient delta:
will step four middle deltaAAnd Δ in step fivebThe value of (c) is substituted into the formula (5),
Δ＝ΔA+Δb (5)；
step seven, calculating the partial height delta L of the correction blade:
substituting the value of L in the third step and the value of delta in the sixth step into the formula (6),
ΔL＝Δ×L (6)；
step eight, calculating the height of the corrected blade
Substituting the value of L in the third step and the value of Delta L in the sixth step into the formula (7),
step nine, with
And (5) repeating the steps from the first step to the eighth step for the original blade height, and obtaining the final corrected blade working part height when the result of the correction coefficient is convergence.
The second embodiment is as follows: referring to fig. 4 to 6, the second step of the present embodiment will be described with reference to fig. 4 to 6, where the root rounding area is a in the case a, the area is a1The formula for calculating (a) is as follows,
A1＝2(R1 2-πR1 2/4)＝0.4292R1 2 (8)；
when the root rounding area is the case B in the second step, the area is A2；
The rest is the same as the first embodiment.
The third concrete implementation mode: referring to fig. 8 to 10, the second step of the present embodiment is that when the area of the rounded top is a, the area is a3；
A3＝2(R3 2-πR3 2/4)＝0.4292R3 2 (10)；
When the area of the top rounding in the second step is the case B, the area is A4：
The others are the same as in the first or second embodiment.
The fourth concrete implementation mode: the present embodiment will be described with reference to fig. 1 to 10, and the flow area reduction value a in step two of the present embodimentbDividing into four conditions according to the relative sizes of the blade-shaped throat width O and the blade rounding radius R in the first step;
the first method comprises the following steps: when the root rounding area is the case A and the tip rounding area is the case A, the flow area is decreased by the value Ab＝A1+A3；
And the second method comprises the following steps: when the root rounding area is the case A and the tip rounding area is the case B, the flow area is decreased by the value Ab＝A1+A4；
And the third is that: when the root rounding area is the case B and the apex rounding area is the case A, the flow area is decreased by the value Ab＝A2+A3；
And fourthly: when the root rounding area is the case B and the tip rounding area is the case B, the flow area is decreased by the value Ab＝A2+A4。
The others are the same as the first, second or third embodiments.
The fifth concrete implementation mode: referring to fig. 1 to 10, the present embodiment is described, and the result of the correction coefficient in step nine of the present embodiment is infinitely small, that is, the finally corrected blade working part height is obtained. The others are the same as the first, second, third or fourth embodiments.
The sixth specific implementation mode: referring to fig. 1 to 10, the present embodiment will be described, and when the result of the correction coefficient in step nine of the present embodiment is 0.001, the finally corrected blade working part height is obtained.
The rest of the description is the same as the description of the first, second, third, fourth or fifth embodiment.
The seventh embodiment: the present embodiment will be described with reference to fig. 1 to 16, and the efficiency correction coefficient Δ in step five of the present embodimentbThe calculation formula of (2) is as follows:
the other embodiments are the same as the first, second, third, fourth, fifth or sixth embodiments.
The present invention has been described in terms of the preferred embodiments, but it is not limited thereto, and any simple modification, equivalent change and modification made to the above embodiments according to the technical spirit of the present invention will still fall within the technical scope of the present invention.
Claims (5)
1. A method for correcting the influence of blade end rounding on flow is characterized in that: it comprises the following steps:
step one, determining a calculation formula adopted for correction according to the relative size of the blade profile throat width O and the blade radius R at the end part of the blade:
when the blade end blade profile throat width O is more than or equal to 2R, the situation is A, and the calculation formula adopted by correction is
A01＝2(R2-πR2/4)＝0.4292R2 (1)；
When the blade end blade profile throat width O is less than 2R, the situation is B, and the calculation formula adopted by correction is
Step two, calculating a reduction value A of the through flow areab：
The numerical value of the blade rounding is small relative to the height of the working part of the blade, so that the blade profile throat width O at the end part of the blade is not changed within the height of the blade rounding R along the blade height direction, and the flow area is simplified into a rectangle;
root blend integration is either case a or case B:
when the root rounding area is the case A, the blade rounding radius at this time is R1Calculating by adopting a calculation formula (1) in the step one, and adding R1The root rounding area obtained in the step (1) is A1；
When the root rounding area is the case B, the blade rounding radius at this time is R2Calculating by adopting a calculation formula (2) in the step one, and adding R2The root rounding area obtained in the step (2) is A2；
The top rounded surface integral is either case a or case B,
when the tip rounding area is the case A, the blade rounding radius at this time is R3Calculating by adopting a calculation formula (1) in the step one, and adding R3In the belt (1), the area of the top rounding is A3；
When the tip rounding area is the case B, the blade rounding radius at this time is R4Calculating by adopting a calculation formula (2) in the step one, and adding R4Brought into (1) to obtain a rounded top area A4；
Flow area reduction value AbIs the sum of the area reductions caused between the root rounding area and the top rounding area in case a or case B, respectively;
step three, calculating the total flow area A of the blade without considering the rounding by adopting an integral method0：
The values of the known blade segment height L and blade tip profile throat width O are substituted into equation (3) to yield a total flow area A without rounding0Wherein L is the height of the blade part and O is the throat width;
step four, calculating an area correction coefficient deltaA：
ΔA＝-Ab/A0 (4)；
Reducing the flow area in the second step by a value AbTotal flow area A in the third step0Is substituted into the formula (4), the area correction coefficient Delta is obtainedAA value of (d);
step five, calculating an efficiency correction coefficient delta according to the full three-dimensional CFD loss libraryb：
Calculating the flow without rounding according to the software of the full three-dimensional CFD loss library, calculating the flow with rounding, comparing the difference between the flow without rounding and the flow with rounding with the flow without rounding, and calculating the efficiency correction coefficient deltab；
Step six, calculating a total correction coefficient delta:
will step four middle deltaAAnd Δ in step fivebThe value of (c) is substituted into the formula (5),
Δ＝ΔA+Δb (5)；
step seven, calculating the partial height delta L of the correction blade:
substituting the value of L in the third step and the value of delta in the sixth step into the formula (6),
ΔL＝Δ×L (6)；
step eight, calculating the height L of the corrected blade:
substituting the value of L in the third step and the value of Delta L in the sixth step into the formula (7),
and step nine, taking L-L as the original blade height, repeating the steps from the first step to the eighth step, and obtaining the final corrected blade working part height when the result of the correction coefficient is convergence.
2. A method of correcting for the effect of blade tip rounding on flow according to claim 1, characterised in that: when the root rounding area is the condition A in the second step, the area is A1The formula for calculating (a) is as follows,
A1＝2(R1 2-πR1 2/4)＝0.4292R1 2 (8)；
when the root rounding area is the condition B in the second step, the area is A2；
3. A method of correcting for the effect of blade tip rounding on flow according to claim 2, characterised in that: when the area of the top rounding in the second step is the condition A, the area is A3；
A3＝2(R3 2-πR3 2/4)＝0.4292R3 2 (10)；
When the area of the top rounding in the second step is the case B, the area is A4：
4. A method of correcting for the effect of blade tip rounding on flow according to claim 3, characterised in that: the reduction value A of the flow area in the second stepbAccording to the width O of the blade-shaped throat at the end part and the blade in the step oneThe relative size of the blend radius R is divided into four cases;
the first method comprises the following steps: when the root rounding area is the case A and the tip rounding area is the case A, the flow area is decreased by the value Ab＝A1+A3；
And the second method comprises the following steps: when the root rounding area is the case A and the tip rounding area is the case B, the flow area is decreased by the value Ab＝A1+A4；
And the third is that: when the root rounding area is the case B and the tip rounding area is the case A, the flow area is decreased by the value Ab＝A2+A3；
And fourthly: when the root rounding area is the case B and the tip rounding area is the case B, the flow area is decreased by the value Ab＝A2+A4。
5. A method of correcting for the effect of blade tip rounding on flow according to claim 4, characterised in that: and fifthly, if the result of the correction coefficient is infinitely small, the finally corrected height of the working part of the blade is obtained.
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| Publication number | Priority date | Publication date | Assignee | Title |
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| US3837761A (en) * | 1971-08-20 | 1974-09-24 | Westinghouse Electric Corp | Guide vanes for supersonic turbine blades |
| US4222172A (en) * | 1979-01-12 | 1980-09-16 | General Motors Corporation | Vane area measuring device |
| GB9417406D0 (en) * | 1994-08-30 | 1994-10-19 | Gec Alsthom Ltd | Turbine blade |
| US7371046B2 (en) * | 2005-06-06 | 2008-05-13 | General Electric Company | Turbine airfoil with variable and compound fillet |
| CN105333855B (en) * | 2014-12-17 | 2018-10-09 | 中国航空工业集团公司沈阳发动机设计研究所 | A method of it measures, calculate turborotor and throat area of guider |
| CN105485057B (en) * | 2015-12-25 | 2019-02-22 | 江苏源泉泵业股份有限公司 | A kind of Hydraulic Design Method of diagonal pumps radial vane |
| CN106640211A (en) * | 2016-10-27 | 2017-05-10 | 西北工业大学 | Edge-blended hole structure used for air film cooling of turbine blades |
| CN108132038B (en) * | 2017-12-08 | 2019-11-12 | 中国航发动力股份有限公司 | A kind of device and method measuring turborotor venturi minimum area |
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