CN1312380C - Strong curved wing section of sea temperature difference energy-solar energy reboil circulation power generating steam turbine - Google Patents
Strong curved wing section of sea temperature difference energy-solar energy reboil circulation power generating steam turbine Download PDFInfo
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- CN1312380C CN1312380C CNB2005100307716A CN200510030771A CN1312380C CN 1312380 C CN1312380 C CN 1312380C CN B2005100307716 A CNB2005100307716 A CN B2005100307716A CN 200510030771 A CN200510030771 A CN 200510030771A CN 1312380 C CN1312380 C CN 1312380C
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Abstract
The present invention relates to a strong curved wing section of a sea temperature difference energy-solar energy reheating circulation power generating steam turbine. Aiming at the characteristics of small working medium gas flow rate and high steam turbine rotation speed, the pressure surface curvature at the front end of the wing section is decreased as far as possible. The ratio d/c of the maximum thickness d of the wing section and the chord length c of the wing section is 0.3, and the ratio xd/c of the maximum thickness position and the chord length of the wing section is 0.25; the ratio f/c of the maximum curvature f and the chord length c of the wing section is 0.1457, and the ratio xf/c of the maximum curvature position and the chord length of the wing section is 0.47. Although the front end of the wing section loses part of apply work capability of the wing section in order to avoid a larger attack angle, and the loss brought to the steam turbine by the apply work capability loss can sufficiently be compensated by a design of thick thickness and strong curvature. The wing section has circular arc transition at the back edge (xR/c=0.97), the ratio R/C of the radius R of a transition circular arc and the chord length c is 0.02, and an obtuse outer edge reduces the damage for the wing section by foreign objects greatly. And the present invention has easy process.
Description
Technical field
The present invention relates to a kind of aerofoil profile, relate in particular to a kind of reheat aerofoil profile of steam turbine of circulating generation of ocean thermal energy-solar energy that is used for, belong to field of energy source developing technology.
Background technique
Ocean thermal energy-solar energy circulating generation of reheating is a kind of mode of the novel acquisition energy.Being used for the reheat steam turbine of circulating generation of ocean thermal energy-solar energy is by a Working medium gas that flows out from solar thermal collector is imported in the steam turbine, promote the rotation of steam turbine, thereby the kinetic energy of working medium is converted into the mechanical energy of steam turbine and is converted into the purpose that electric power is exported or directly output realizes obtaining the energy by generator, is the mode of obtaining electric power a kind of complete environmental protection, cleaning.The blade of steam turbine is the most critical parts of such steam turbine.And for the blade of steam turbine, the aerofoil profile of leaf cross-section is selected and research is the direct factor that influence the mechanical efficient of steam turbine.
Owing to the flow of the Working medium gas that flows out from solar thermal collector is little, and the rotating speed of steam turbine is higher, so when utilizing ocean thermal energy-solar energy to reheat circulating generation, steam turbine is had special requirement.For general steam turbine, often adopt the measure of inlet whirl, promptly add a nozzle at the steam turbine inlet, improve the inlet angle of steam flow, but the adding of nozzle brings extra complexity not only for the steam turbine structure, but also can lose energy greatly, reduce cycle efficiency greatly.Therefore, not only simple in structure for such steam turbine, and for the requirement of vane airfoil profile, also different with general steam turbine.The steam turbine blade is met stream with inevasible with the bigger angle of attack in a lot of operating times.If select aerofoil profile commonly used (as NACA aerofoil profile, RAF-6 aerofoil profile, CLARK aerofoil profile, LS aerofoil profile, Gottingen aerofoil profile, FAGE﹠amp during the design blade; COLLINS aerofoil profile, RHODE GENESE aerofoil profile, COANDA aerofoil profile, EPPLER aerofoil profile etc.), tend to because the bigger pressure side curvature of aerofoil profile front end commonly used, make aerofoil profile under more abominable operating conditions (the big steam flow angle of attack), steam flow will separate at blade surface very soon.At this moment, the lift coefficient of aerofoil profile will descend significantly, the rapid increase of resistance coefficient, and turbine efficiency will reduce greatly, be difficult to reach designing requirement.At present, be used for the aerofoil profile of steam turbine design, often be limited in the less operating mode scope, in the operating mode scope, aerofoil profile has bigger lift coefficient and less resistance coefficient, still, in case leave this operating mode scope, aerofoil profile generation stall, performance worsens rapidly.Therefore, must design a kind of aerofoil profile that is specifically designed to such steam turbine.
Summary of the invention
The objective of the invention is at the deficiencies in the prior art, design provides a kind of reheat aerofoil profile of steam turbine of circulating generation of ocean thermal energy-solar energy that is used for, and the flow that can adapt to Working medium gas fully is little, the characteristic that the rotating speed of steam turbine is higher.By the design of new aerofoil profile, reduce the inlet angle of attack that working medium flows into steam turbine on the one hand as far as possible, even make aerofoil profile under the bigger angle of attack on the one hand, can guarantee that also blade has bigger lift coefficient and less resistance coefficient.
For realizing this purpose, the maximum ga(u)ge d of the aerofoil profile of the present invention's design is about with the ratio of the chord length c of aerofoil profile: d/c=0.3, maximum ga(u)ge position x
dWith the ratio of the chord length c of aerofoil profile be: x
d/ c=0.25; Aerofoil profile maximum camber f with the ratio of the chord length c of aerofoil profile is: f/c=0.1457, maximum ga(u)ge position x
fBe about x with the ratio of the chord length c of aerofoil profile
f/ c=0.47.Consider the hydraulic performance of the big angle of attack of aerofoil profile, aerofoil profile is at trailing edge x
R/ c=0.97 sentences arc transition, and transition arc radius R is R/c=0.02 with the ratio of the chord length c of aerofoil profile.
Wherein, X
dBe the abscissa value of aerofoil profile maximum ga(u)ge place aerofoil profile, X
fBe the abscissa value of aerofoil profile maximum camber place aerofoil profile, X
RAbscissa value for aerofoil profile arc transition place aerofoil profile.
The flow that the present invention is directed to Working medium gas is little, and the higher characteristics of the rotating speed of steam turbine are the steam flow angle of attack of avoiding entering the mouth bigger, reduce the pressure side curvature of aerofoil profile front end as far as possible, when striving for that steam flow flows into steam turbine, has less steam flow to separate and energy loss.
By increasing maximum ga(u)ge and camber is a kind of the most effectively means that will obtain bigger lift coefficient.Reducing of the pressure side curvature of aerofoil profile front end will certainly influence the acting ability of whole aerofoil profile, so by the method that the control adverse pressure gradient slows down nearly wall fluid, increase camber and thickness.Like this, though sacrificed the acting ability of a part of aerofoil profile for fear of the bigger angle of attack,, be enough to remedy the loss that the former brings for the steam turbine performance by big thickness, strong curved design at the aerofoil profile front end.
Big thickness and strong curved aerofoil profile are the most worrying to be mobile performance under the off-design condition of aerofoil profile, and the angle of attack increases a little, the resistance increase and the loss of lift that will cause airflow breakaway and bring thus.Compare with common Airfoil Design, consider the off design performance of aerofoil profile, in design during this aerofoil profile, have a mind to move behind the position with maximum ga(u)ge, enlarge the envelope curve of aerofoil profile as far as possible, with the acting ability of the off design performance that improves aerofoil profile.From flowing angle, point of maximum thickness also is difficult for too close leading edge.This mainly be because, after the too close leading edge of point of maximum thickness, " point " leading edge to walk around aerofoil profile of flowing and sharply quickening, the reach of pressure minimum point, the corresponding deterioration of adverse pressure gradient, and cause too early generation commentaries on classics to be twisted and corresponding loss of lift, after moving after the point of maximum thickness, the position of pressure minimum value can be pushed as far as possible to the rear portion of aerofoil profile, make aerofoil profile leading portion boundary layer stable, separation point is postponed, and helps the acting of aerofoil profile leading portion convex surface, thereby the performance of aerofoil profile can be improved on the whole.
In addition, because trailing edge is with arc transition, therefore more blunt outer rim makes foreign object reduce to minimum to the damage of aerofoil profile, and is easy to processing.
In sum, the reheat novel aerofoil profile of circulating generation steam turbine of ocean thermal energy-solar energy that is used for of the present invention has following characteristics:
1, this aerofoil profile front end reduces pressure side curvature as far as possible, with the steam flow angle of attack that reduces to enter the mouth.
2, the maximum ga(u)ge d of aerofoil profile is about with the ratio of the chord length c of aerofoil profile: d/c=0.3, aerofoil profile maximum camber f with the ratio of the chord length c of aerofoil profile is: f/c=0.1457, improve the acting ability of aerofoil profile, to remedy owing to the aerofoil profile forefront pressure curvature of face reduces to the influence of steam turbine acting ability.
3, the maximum ga(u)ge position of this aerofoil profile is: x
d/ c=0.25 compares with other aerofoil profiles, and maximum ga(u)ge moves behind the position, thereby the performance of aerofoil profile can be improved on the whole.
4, during this Airfoil Design, at trailing edge x
R/ c=0.97 sentences arc transition, and the radius R of transition arc with the ratio of the ratio c of chord length is: R/c=0.02, and more blunt outer rim makes foreign object reduce to minimum to the damage of aerofoil profile, and more blunt outer rim also makes the processing of aerofoil profile reduce to minimum.
Description of drawings
Fig. 1 is an airfoil structure schematic representation of the present invention.
Among Fig. 1, the upper surface of 1 expression aerofoil profile, the lower surface of 2 expression aerofoil profiles, 3 is the mean camber line of aerofoil profile.
C is the chord length of aerofoil profile, and d is the maximum ga(u)ge of aerofoil profile, X
dBe the abscissa value of aerofoil profile maximum ga(u)ge place aerofoil profile, f is the maximum camber of aerofoil profile, X
fAbscissa value for aerofoil profile maximum camber place aerofoil profile.
Fig. 2 is aerofoil profile liter of the present invention, resistance coefficient plotted curve.
Among Fig. 2, α is the air-flow angle of attack, C
yBe wing section lift coefficient, C
xBe the profile drag coefficient.
Embodiment
Below be unit 1 with the aerofoil profile chord length, the specific embodiment of the present invention is further described.
Get after the aerofoil profile chord length is unit 1, the coordinate such as the table 1 of blade are listed.
Table 1 blade coordinate
| Upper surface | Lower surface | |||
| X | | X | Y | |
| 0 0 0.01 0.039917724 0.02 0.062667844 0.03 0.081184363 0.04 0.096981359 0.05 0.111737581 0.06 0.125557549 0.07 0.138469859 0.08 0.150507051 0.09 0.161702157 0.1 0.172089196 0.11 0.181703173 0.12 0.190576134 0.13 0.198740618 0.14 0.206227688 0.15 0.213086151 0.16 0.219379608 0.17 0.225162291 0.18 0.230480053 0.19 0.235368883 0.2 0.239861815 0.21 0.243984486 0.22 0.24776056 0.23 0.251209266 0.24 0.254347859 0.25 0.257190638 0.26 0.259750421 0.27 0.262038055 0.28 0.264062413 0.29 0.265832371 0.3 0.267354337 0.31 0.268636201 0.32 0.26968585 0.33 0.270510187 0.34 0.271116114 0.35 0.271510533 0.36 0.271699362 0.37 0.271689501 | 0 0 0.01 -0.027018233 0.02 -0.035546076 0.03 -0.041214871 0.04 -0.045386351 0.05 -0.048586573 0.06 -0.051085221 0.07 -0.053040556 0.08 -0.05455562 0.09 -0.055700916 0.1 -0.056526732 0.11 -0.057070044 0.12 -0.057357478 0.13 -0.057409738 0.14 -0.057241124 0.15 -0.056861988 0.16 -0.056277754 0.17 -0.055490394 0.18 -0.054497443 0.19 -0.053294956 0.2 -0.051879483 0.21 -0.050249544 0.22 -0.048403661 0.23 -0.04634134 0.24 -0.04406406 0.25 -0.041575765 0.26 -0.038881387 0.27 -0.035988319 0.28 -0.032906916 0.29 -0.02965049 0.3 -0.026234817 0.31 -0.022679617 0.32 -0.019007078 0.33 -0.015243823 0.34 -0.011416967 0.35 -0.007559051 0.36 -0.003701628 0.37 0.000119805 | |||
| 0.38 0.271487361 0.39 0.271097872 0.4 0.270526949 0.41 0.26978051 0.42 0.268863978 0.43 0.267782775 0.44 0.266541833 0.45 0.265146081 0.46 0.263600449 0.47 0.261910361 0.48 0.260080255 0.49 0.258115059 0.5 0.256019212 0.51 0.253797151 0.52 0.251453806 0.53 0.248993614 0.54 0.246421012 0.55 0.243740438 0.56 0.240955836 0.57 0.238068685 0.58 0.235078492 0.59 0.231983778 0.6 0.228785035 0.61 0.225481278 0.62 0.222072014 0.63 0.21855675 0.64 0.214934499 0.65 0.211204276 0.66 0.207366574 0.67 0.20341942 0.68 0.199362815 0.69 0.195195773 0.7 0.1909178 0.71 0.186527417 0.72 0.182024625 0.73 0.177407944 0.74 0.172676388 0.75 0.167829465 0.76 0.162866188 0.77 0.157783599 0.78 0.152585149 0.79 0.147265908 0.8 0.141825877 0.81 0.136264068 | 0.38 0.003871721 0.39 0.007519609 0.4 0.011029943 0.41 0.014372156 0.42 0.017518145 0.43 0.020441779 0.44 0.02312186 0.45 0.025540638 0.46 0.027689732 0.47 0.029587383 0.48 0.031254299 0.49 0.032709214 0.5 0.033968398 0.51 0.035047136 0.52 0.035959231 0.53 0.036716023 0.54 0.037329839 0.55 0.037810045 0.56 0.038166994 0.57 0.038409562 0.58 0.038545637 0.59 0.038584093 0.6 0.038531339 0.61 0.038395758 0.62 0.038183757 0.63 0.037901747 0.64 0.037553179 0.65 0.037139038 0.66 0.036658833 0.67 0.036113054 0.68 0.035502197 0.69 0.034826261 0.7 0.034086231 0.71 0.033282108 0.72 0.032414878 0.73 0.031484541 0.74 0.030492083 0.75 0.029437503 0.76 0.028322282 0.77 0.027146912 0.78 0.025911886 0.79 0.024618683 0.8 0.02326681 0.81 0.021858732 |
| 0.82 0.13057851 0.83 0.124770189 0.84 0.118839598 0.85 0.112786737 0.86 0.106613578 0.87 0.100320121 0.88 0.093907845 0.89 0.087377736 0.9 0.080731274 0.91 0.073968457 0.92 0.067091752 0.93 0.060101652 0.94 0.052999635 0.95 0.04578718 0.96 0.03846626 0.97 0.031037861 0.98 0.023503954 0.99 0.01586602 1 0 | 0.82 0.020394449 0.83 0.018874948 0.84 0.017301214 0.85 0.015676205 0.86 0.014001401 0.87 0.01227976 0.88 0.010513746 0.89 0.008706812 0.9 0.006860435 0.91 0.004978068 0.92 0.003061682 0.93 0.001114235 0.94 -0.000861314 0.95 -0.0028625 0.96 -0.004887351 0.97 -0.006931924 0.98 -0.008995231 0.99 -0.01016715 1 0 |
The maximum ga(u)ge of this aerofoil profile is about: d=0.3, the maximum ga(u)ge position is: x
d=0.25; Camber is: f=0.1457, x
f=0.47.Trailing edge x=0.97 place is the arc transition of R=0.02 with the radius.
1, at this aerofoil profile front end, reduces pressure side curvature, with the steam flow angle of attack that reduces to enter the mouth as far as possible.
2, the maximum ga(u)ge of this aerofoil profile is about: d=0.3, and camber is: f=0.1457, improve the acting ability of aerofoil profile.
3, the maximum ga(u)ge position of this aerofoil profile is: x
d=0.25, to compare with other aerofoil profiles, maximum ga(u)ge moves behind the position, thereby the performance of aerofoil profile can be improved on the whole.
4, during this Airfoil Design, at trailing edge x=0.97 place, be the arc transition of R=0.02 with the radius, more blunt outer rim makes foreign object reduce to minimum to the damage of aerofoil profile, and more blunt outer rim also makes the processing of aerofoil profile reduce to minimum.
When reynolds' number is 3 * 10
5The time, the liter of this aerofoil profile, resistance coefficient are as shown in Figure 2.Can find that from Fig. 2 though the pressure side curvature of aerofoil profile front end reduces, because the thickness of aerofoil profile increases, the acting ability of aerofoil profile is not subjected to very big influence, maximum lift coefficient is: C
Ymax=1.185; Owing to move behind the maximum ga(u)ge position, stall angle increased:
Claims (2)
1, a kind of aerofoil profile that is used for the steam turbine of ocean temperature difference energy and solar energy reheat circulating electric generating, the maximum ga(u)ge d that it is characterized in that aerofoil profile with the ratio of the chord length c of aerofoil profile is: d/c=0.3, the maximum ga(u)ge position is: x
d/ c=0.25; Maximum camber f with the ratio of the chord length c of aerofoil profile is: f/c=0.1457, the maximum camber position is: x
f/ c=0.47; Aerofoil profile is at trailing edge x
R/ c=0.97 sentences arc transition, and the radius R of transition arc with the ratio of chord length c is: R/c=0.02; X wherein
dBe the abscissa value of aerofoil profile maximum ga(u)ge place aerofoil profile, X
fBe the abscissa value of aerofoil profile maximum camber place aerofoil profile, X
RAbscissa value for aerofoil profile arc transition place aerofoil profile.
2, according to claim 1 be used for the reheat aerofoil profile of steam turbine of circulating generation of ocean thermal energy-solar energy, it is characterized in that the described aerofoil profile chord length c unit of being taken as 1 after, the blade coordinate is:
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| CNB2005100307716A CN1312380C (en) | 2005-10-27 | 2005-10-27 | Strong curved wing section of sea temperature difference energy-solar energy reboil circulation power generating steam turbine |
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| CNB2005100307716A CN1312380C (en) | 2005-10-27 | 2005-10-27 | Strong curved wing section of sea temperature difference energy-solar energy reboil circulation power generating steam turbine |
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| CN1312380C true CN1312380C (en) | 2007-04-25 |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN102094848A (en) * | 2011-03-22 | 2011-06-15 | 上海交通大学 | Airfoil for large-scale industrial high-pressure ratio axial flow compressor |
| CN102588188A (en) * | 2012-02-13 | 2012-07-18 | 上海交通大学 | Airfoil for variable geometry current generating water turbine |
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| FR3032494B1 (en) * | 2015-02-06 | 2018-05-25 | Safran Aircraft Engines | AUBE DE SOUFFLANTE |
| FR3089553B1 (en) | 2018-12-11 | 2021-01-22 | Safran Aircraft Engines | TURBOMACHINE DAWN AT ARROW LAW WITH HIGH MARGIN AT FLOTATION |
| CN112977815B (en) * | 2021-05-10 | 2021-08-27 | 北京三快在线科技有限公司 | Rotor craft, blade of rotor craft and wing section of blade |
| CN115593612B (en) * | 2022-12-15 | 2023-04-25 | 中国空气动力研究与发展中心空天技术研究所 | Self-balancing stall-resistant high-performance airfoil |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6450770B1 (en) * | 2001-06-28 | 2002-09-17 | General Electric Company | Second-stage turbine bucket airfoil |
| US6722851B1 (en) * | 2003-03-12 | 2004-04-20 | General Electric Company | Internal core profile for a turbine bucket |
| US6722852B1 (en) * | 2002-11-22 | 2004-04-20 | General Electric Company | Third stage turbine bucket airfoil |
| CN1568396A (en) * | 2001-07-13 | 2005-01-19 | 通用电气公司 | Second-stage turbine nozzle airfoil |
| CN1587674A (en) * | 2004-09-16 | 2005-03-02 | 上海交通大学 | Water turbine wingsection for ocean current generation |
| CN1673527A (en) * | 2005-03-24 | 2005-09-28 | 上海交通大学 | Ocean temperature difference energy and solar energy reheat circulating electric generating method |
-
2005
- 2005-10-27 CN CNB2005100307716A patent/CN1312380C/en not_active Expired - Fee Related
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6450770B1 (en) * | 2001-06-28 | 2002-09-17 | General Electric Company | Second-stage turbine bucket airfoil |
| CN1568396A (en) * | 2001-07-13 | 2005-01-19 | 通用电气公司 | Second-stage turbine nozzle airfoil |
| US6722852B1 (en) * | 2002-11-22 | 2004-04-20 | General Electric Company | Third stage turbine bucket airfoil |
| US6722851B1 (en) * | 2003-03-12 | 2004-04-20 | General Electric Company | Internal core profile for a turbine bucket |
| CN1587674A (en) * | 2004-09-16 | 2005-03-02 | 上海交通大学 | Water turbine wingsection for ocean current generation |
| CN1673527A (en) * | 2005-03-24 | 2005-09-28 | 上海交通大学 | Ocean temperature difference energy and solar energy reheat circulating electric generating method |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102094848A (en) * | 2011-03-22 | 2011-06-15 | 上海交通大学 | Airfoil for large-scale industrial high-pressure ratio axial flow compressor |
| CN102588188A (en) * | 2012-02-13 | 2012-07-18 | 上海交通大学 | Airfoil for variable geometry current generating water turbine |
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| CN1757883A (en) | 2006-04-12 |
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