CN104420888B - Convergent runner transonic turbine blade and apply its turbine - Google Patents
Convergent runner transonic turbine blade and apply its turbine Download PDFInfo
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- CN104420888B CN104420888B CN201310364144.0A CN201310364144A CN104420888B CN 104420888 B CN104420888 B CN 104420888B CN 201310364144 A CN201310364144 A CN 201310364144A CN 104420888 B CN104420888 B CN 104420888B
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- molded line
- blade
- blade profile
- subsegment
- suction surface
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Abstract
The invention provides a kind of convergent runner transonic turbine blade and apply its turbine.The surface three dimension molded line of this convergent runner transonic turbine blade is formed along long-pending the folding of radial direction by N number of blade profile, wherein, and N >=3; In this N number of blade profile, each blade profile includes suction surface molded line and pressure side molded line, and in this N number of blade profile, the suction surface molded line of at least one blade profile exists indent molded line.Convergent runner transonic turbine blade of the present invention makes the pneumatic total losses of blade be reduced, and effectively reduces the flow losses of transonic turbine at supersonic domain.
Description
Technical field
The present invention relates to aerodynamic scope, particularly relate to the convergent runner transonic turbine blade of a kind of suction surface naked section of indent and apply its turbine.
Background technique
Traditional subsonic turbine compared by High-loaded Transonic Axial turbine can effectively improve a grade load, is widely applied in high thrust weight ratio aeroengine.Existing High-loaded Transonic Axial turbine is (as the E of GE company
3turbine etc.) main adopt gradual shrinkage runner, air-flow continues to accelerate to along evagination or straight suction surface molded line slightly and exceedes local velocity of sound after aditus laryngis reaches local velocity of sound in naked passage.Supersonic airstream in trailing edge place produces overhanging shock wave, expand and involve the reflected wave of their each comfortable suction surfaces, constitute with the overhanging shock wave of trailing edge the wave system structure that there is complex effects relation each other.This wave system structure increases along with larger velocity gradient and entropy usually, not only produces shock loss but also can affect the evolution of suction surface boundary layer and tail, thus change the aerodynamic loss of blade.These losses all can increase along with the raising of turbine stage load and blade exit Mach number.
Summary of the invention
(1) technical problem that will solve
In view of above-mentioned technical problem, the invention provides a kind of convergent runner transonic turbine blade and apply its turbine, to reduce the flow losses of transonic turbine at supersonic domain.
(2) technological scheme
According to an aspect of the present invention, a kind of convergent runner transonic turbine blade is provided.The surface three dimension molded line of this convergent runner transonic turbine blade is formed along long-pending the folding of radial direction by N number of blade profile, wherein, and N >=3; In this N number of blade profile, each blade profile includes suction surface molded line and pressure side molded line, and in this N number of blade profile, the suction surface molded line of at least one blade profile exists indent molded line.
According to another aspect of the present invention, a kind of turbine is additionally provided.This turbine comprises: turbine rotor; And several above-mentioned convergent runner transonic turbine blades, be uniformly distributed circumferentially on the wheel hub surface of described turbine rotor.
(3) beneficial effect
As can be seen from technique scheme, convergent runner transonic turbine blade of the present invention and in applying its turbine, because suction surface molded line exists indent molded line on its naked section, thus the pneumatic total losses of blade is reduced, the even property of circumferential asymmetry of exit flow improves, and reduces the unsteady flo w impact on downstream blade row boundary layer.
Accompanying drawing explanation
Figure 1A and Figure 1B is the 3 dimensional drawing of embodiment of the present invention convergent runner transonic turbine blade under different visual angles;
Fig. 1 C is the long-pending folded figure of the three-dimensional blade profile of embodiment of the present invention convergent runner transonic turbine blade;
Fig. 2 is the blade profile figure of the present embodiment convergent runner transonic turbine blade and adjacent blades;
Fig. 3 is the suction surface molded line Bezier control point distribution map of an embodiment of the present invention convergent runner transonic turbine blade blade profile;
Fig. 4 is the 3 dimensional drawing of embodiment of the present invention turbine.
[primary component symbol description of the present invention]
1-blade profile; 2-suction surface molded line;
3-pressure side molded line; 4-blade profile leading edge;
5-blade profile trailing edge; 6-blade profile passage
7-hides section; First subsegment of naked section of 8-;
Second subsegment of naked section of 9-; 3rd subsegment of naked section of 10-;
Naked section of 11-; 12-center of gravity;
13-amasss superimposing thread;
Point on A, B, C, D, E-suction surface molded line;
The terminal of F-pressure side molded line;
The axial length that L-is naked section;
L
2the axial length of-naked section of the second subsegment; L
3the axial length of-naked section the 3rd subsegment;
P
1, P
2, P
3, P
4, P
5, P
6, P
7-Bezier control point.
Embodiment
For making the object, technical solutions and advantages of the present invention clearly understand, below in conjunction with specific embodiment, and with reference to accompanying drawing, the present invention is described in more detail.It should be noted that, in accompanying drawing or specification describe, similar or identical part all uses identical figure number.The implementation not illustrating in accompanying drawing or describe is form known to a person of ordinary skill in the art in art.In addition, although herein can providing package containing the demonstration of the parameter of particular value, should be appreciated that, parameter without the need to definitely equaling corresponding value, but can be similar to corresponding value in acceptable error margin or design constraints.The direction term mentioned in embodiment, such as " on ", D score, "front", "rear", "left", "right" etc., be only the direction with reference to accompanying drawing.Therefore, the direction term of use is used to illustrate and is not used for limiting the scope of the invention.
The invention provides and a kind ofly there is the convergent runner transonic turbine blade of indent molded line naked section of suction surface and apply its turbine.This blade weakens in trailing edge the strong interaction of stretching between shock wave reflection ripple and the overhanging shock wave of trailing edge, decreases the shock loss produced because of the two superposition.
In one exemplary embodiment of the present invention, provide the convergent runner transonic turbine blade of a kind of suction surface naked section of indent.Figure 1A and Figure 1B is the stereogram of embodiment of the present invention convergent runner transonic turbine blade under different visual angles.Fig. 1 C is the long-pending folded figure of the three-dimensional blade profile of embodiment of the present invention convergent runner transonic turbine blade.
Please refer to Figure 1A, Figure 1B and Fig. 1 C, the surface three dimension molded line of the present embodiment convergent runner transonic turbine blade is formed along long-pending the folding of radial direction (r direction) by 5 blade profiles, each blade profile is formed by the circular arc smooth connection of leading edge, trailing edge by suction surface molded line 2 and pressure side molded line 3, and suction surface molded line exists indent molded line.
Below the blade profile of the present embodiment convergent runner transonic turbine blade is described in detail.
Fig. 2 is the blade profile figure of the present embodiment convergent runner transonic turbine blade and adjacent blades.Please refer to Fig. 2, the blade profile 1 of convergent runner transonic turbine blade is passed through the circular arc smooth connection of blade profile leading edge 4, blade profile trailing edge 5 by suction surface molded line 2 and pressure side molded line 3.Wherein, the radius of this circular arc is between 0.1mm ~ 5mm.
The pressure side molded line 3 of convergent runner transonic turbine blade and the suction surface molded line 2 of adjacent blades blade profile form the blade profile passage 6 that width reduces gradually.The import of blade profile passage 6 is formed between the leading edge of this convergent runner transonic turbine vane foil and the leading edge of the same radial location blade profile of adjacent blades.
Continue referring to Fig. 2, the suction surface molded line 2 of blade profile 1 vertically (z direction) comprising: hide section 7, for suction surface molded line 2 is positioned at the part of blade profile passage, as the part between Fig. 2 mid point A and some B; Naked section 11, for suction surface molded line 2 is positioned at the part outside blade profile passage, as the part between Fig. 2 mid point B and some E.The outlet of blade profile passage 6 is formed between naked section of starting point B of current convergent runner transonic turbine vane foil and adjacent blades same radial location blade profile pressure side molded line terminal F.
Continue referring to Fig. 2, naked section 11 vertically (z direction) comprise again: the first subsegment 8, towards blade exterior direction protrude, as Fig. 2 mid point B and some C between part; Second subsegment 9, it is recessed into towards blade interior direction, is above-mentioned indent molded line, as the part between Fig. 2 mid point C and some D; And the 3rd subsegment 10, protrude towards blade exterior or be straight, as Fig. 2 mid point D and the part put between E.
Please refer to Fig. 2 and Fig. 3, the first subsegment 8 is connected with the second subsegment 9.The curvature of the first subsegment 8 and the second subsegment 9 tie point is 0, and the first subsegment 8 of these tie point both sides and the second subsegment 9 have the contrary curvature of sign symbol.Second subsegment 9 is connected with the 3rd subsegment 10.The curvature of the second subsegment 9 and the 3rd subsegment 10 tie point is 0, and the second subsegment 9 and the 3rd subsegment 10 of these tie point both sides have the contrary curvature of sign symbol.
In the present embodiment, suction surface molded line is generated by the Bezier at 7 control points.Fig. 3 is the suction surface molded line Bezier control point distribution map of an embodiment of the present invention convergent runner transonic turbine blade blade profile.Please refer to Fig. 3, control point P
1, P
2and P
3be positioned at the outside of suction surface molded line 2, control point P
4, P
5and P
6be positioned at the inner side of suction surface molded line 2, control point P
7be positioned on suction surface molded line 2, thus be that naked section 11 of L constructs axial length is L at axial length
2indent molded line 9.
In the present embodiment, the suction surface molded line of blade profile is constructed by the Bezier at 7 control points.It will be apparent to those skilled in the art that the control point of Bezier can get 4 ~ numerous between.Get 4 ~ numerous Bezier for this control point, the following condition of its demand fulfillment, just can form the suction surface molded line of convergent runner transonic turbine blade of the present invention:
(1) outside being positioned at suction surface molded line is had at least in the control point of axial forward end part;
(2) control point of stage casing part has an inner side being positioned at suction surface molded line at least;
(3) control point of axial rearward end part is positioned on suction surface molded line or outside suction surface molded line.
It should be apparent to those skilled in the art that; by the one that Bezier determination suction surface molded line is in implementation of the present invention; those skilled in the art can also construct suction surface molded line of the present invention by the spline curve or circular curve etc. of other curvature at least Second Order Continuous; within protection scope of the present invention, no longer should repeat equally herein.
Please refer to Fig. 2 and Fig. 3, the axial length L of naked section accounts for 30.2% of blade profile 1 axial length.Wherein, in naked section, the axial length (L-L of the first subsegment
2-L
3) account for 4.2% of blade profile 1 axial length; The axial length L of the second subsegment
2account for 22.0% of blade profile 1 axial length.The axial length L of the 3rd subsegment
3account for 4.0% of blade profile 1 axial length.
It will be apparent to those skilled in the art that the shape and size that can design naked section as required.In other embodiments of the present invention, the axial length L of described naked section 11 accounts for 14 ~ 55% of blade profile 1 axial length.Wherein, the axial length (L-L of the first subsegment 8
2-L
3) account for 2 ~ 10% of blade profile 1 axial length; The axial length L of the second subsegment 9
2account for 10 ~ 30% of blade profile 1 axial length.The axial length L of the 3rd subsegment 10
3account for 2 ~ 15% of blade profile 1 axial length.
In the present embodiment, the ratio of the outlet pitch of blade profile and the exit width (geometry aditus laryngis width) of blade profile passage 6 is between 1.1-3.5, the geometry aditus laryngis width of blade profile passage is 8 ~ 15 times of blade profile trailing edge axis of small circle, blade profile inlet/outlet geometry flow angle (axis) is selected arbitrarily between 0 ~ 90 degree, and the exit Mach number of blade profile is 1.1 ~ 1.5.Blade profile outlet pitch is the distance between the trailing edge of the same radial location blade profile of adjacent two blade.
Please refer to Figure 1A, Figure 1B and Fig. 1 C, the present embodiment convergent runner transonic turbine blade is formed along long-pending the folding of radial direction by 5 blade profiles.It will be apparent to those skilled in the art that the number N of blade profile and designing requirement, technology difficulty are relevant, generally, the lower limit of blade profile number N is 3, and the upper limit is infinitely great.And in the preferred embodiment of the invention, the number N of blade profile is between 4 ~ 100.Preferably, blade profile number N is between 4 ~ 20.Optimally, blade profile number N desirable 4,5,6,7,8,9,10,11,12,13,14,15,50,100 etc.
In the present embodiment convergent runner transonic turbine blade, all there is indent molded line in the suction surface molded line of 5 blade profiles, but the present invention is not as limit.In other embodiments of the invention, also can be that some blade profile suction surface molded line be arranged in the middle part of blade exist indent molded line, or there is indent molded line, equally within protection scope of the present invention in the blade profile suction surface molded line at its two ends.
Please refer to Fig. 1 C and Fig. 2, in the present embodiment convergent runner transonic turbine blade, the blade profile 1 naked section of 5 suction surface molded line being existed indent molded line is long-pending folded with the line 13 by each blade profile 1 center of gravity 12, obtain the three-dimension curved surface of blade surface, namely long-pending superimposing thread 13 is the line of each blade profile center of gravity, and be straight line, but the present invention is not as limit.In other embodiments of the invention, each blade profile can also divide along the geometric ratio branch on its center of gravity, leading edge, trailing edge, the string of a musical instrument or the geometric ratio on mean camber line that dot product is folded obtains the three-dimensional molded line of described convergent runner transonic turbine blade surface.Further, long-pending superimposing thread can be not only straight line, can also be the space curve of arbitrary shape.
In the present embodiment, in the Supersonic Flow region of transonic turbine blade profile passage, indent molded line increases the suction surface molded line curvature between pneumatic aditus laryngis to its starting point, therefore the extensional wave intensity that within the scope of this, molded line produces increases, and makes the overhanging shock wave corrugated of the trailing edge of adjacent blades add the angle deflected to downstream around trailing edge.Indent molded line reduces in trailing edge wavefront, the flow angle (axis) after ripple of stretching shock wave reflection ripple by self molded line, thus makes the shock wave corrugated of this reflected wave add the angle upstream deflected around incidence point.
The reverse deflection in above-mentioned two shock wave corrugateds has postponed the joint stretching shock wave reflection ripple in the overhanging shock wave of trailing edge and trailing edge in the flowing direction.Because shock wave is that intensity after constantly decay and the superposition of more weak shock wave is also more weak along flowing to, therefore also less by the shock loss at joint place that postpones, that is, indent molded line weakens the shock loss produced owing to stretching the superposition of shock wave reflection ripple in the overhanging shock wave of trailing edge and trailing edge.This shock loss reduced makes the pneumatic total losses of blade be reduced, and the even property of circumferential asymmetry of exit flow improves, and reduces the unsteady flo w impact on downstream blade row boundary layer.
So far, the present embodiment convergent runner transonic turbine blade is introduced complete.
In another embodiment of the present invention, a kind of turbine applying above-mentioned convergent runner transonic turbine blade is additionally provided.This turbine comprises: turbine rotor and be uniformly distributed circumferentially the convergent runner transonic turbine blade on the wheel hub surface of turbine rotor.
It will be apparent to those skilled in the art that number and the size of the convergent runner transonic turbine blade in the present embodiment turbine can adjust as required, no longer repeat herein.
So far, the present embodiment turbine is introduced complete.
By reference to the accompanying drawings the present embodiment is described in detail above.Describe according to above, those skilled in the art should have convergent runner transonic turbine blade of the present invention and have clearly been familiar with.
In addition, the above-mentioned definition to each element is not limited in the various concrete structure or shape mentioned in mode of execution, and those of ordinary skill in the art can replace it with knowing simply.
In sum, the invention provides the convergent runner transonic turbine blade of a kind of suction surface naked section of indent.Because suction surface molded line exists indent molded line on its naked section, thus the pneumatic total losses of blade is reduced, the even property of circumferential asymmetry of exit flow improves, and reduces the unsteady flo w impact on downstream blade row boundary layer.
Above-described specific embodiment; object of the present invention, technological scheme and beneficial effect are further described; be understood that; the foregoing is only specific embodiments of the invention; be not limited to the present invention; within the spirit and principles in the present invention all, any amendment made, equivalent replacement, improvement etc., all should be included within protection scope of the present invention.
Claims (9)
1. a convergent runner transonic turbine blade, is characterized in that, its surface three dimension molded line is formed along long-pending the folding of radial direction by N number of blade profile, wherein, and N >=3;
In this N number of blade profile, each blade profile includes suction surface molded line and pressure side molded line, and in this N number of blade profile, the suction surface molded line of at least one blade profile exists indent molded line;
Wherein, form the blade profile passage that width reduces gradually between described suction surface molded line and the pressure side molded line of adjacent blades blade profile, this suction surface molded line comprises vertically:
Hide section, for described suction surface molded line is positioned at the part of blade profile passage;
Naked section, be positioned at the part outside blade profile passage for described suction surface molded line, comprise:
First subsegment, protrudes towards blade exterior direction;
Second subsegment is described indent molded line, and it is recessed towards blade interior direction; And
3rd subsegment, towards blade exterior protrude or be straight.
2. convergent runner transonic turbine blade according to claim 1, is characterized in that,
The curvature of described first subsegment and the second subsegment tie point is 0, and the first subsegment of these tie point both sides and the second subsegment have the contrary curvature of sign symbol;
The curvature of described second subsegment and the 3rd subsegment tie point is 0, and the second subsegment and the 3rd subsegment of these tie point both sides have the contrary curvature of sign symbol.
3. convergent runner transonic turbine blade according to claim 1, is characterized in that, described suction surface molded line is the spline curve of at least Second Order Continuous, circular curve or Bezier.
4. convergent runner transonic turbine blade according to claim 3, it is characterized in that, described suction surface molded line is Bezier, in this Bezier:
The control point of axial forward end part has an outside being positioned at suction surface molded line at least;
The control point of stage casing part has an inner side being positioned at suction surface molded line at least;
The control point of axial rearward end part is positioned on suction surface molded line or the outside of suction surface molded line.
5. convergent runner transonic turbine blade according to claim 1, is characterized in that, the axial length of described naked section accounts for 14 ~ 55% of described blade profile axial length, wherein:
The axial length of described first subsegment accounts for 2 ~ 10% of described blade profile axial length;
The axial length of described second subsegment accounts for 10 ~ 30% of described blade profile axial length;
The axial length of described 3rd subsegment accounts for 2 ~ 15% of described blade profile axial length.
6. convergent runner transonic turbine blade according to any one of claim 1 to 5, is characterized in that:
Described blade profile number N is between 4 ~ 100;
Described suction surface molded line and pressure side molded line pass through the circular arc smooth connection of blade profile leading edge, blade profile trailing edge, and wherein, the radius of this circular arc is between 0.1mm ~ 5mm;
The ratio of the outlet pitch of described blade profile and the exit width of blade profile passage is between 1.1-3.5, and the geometry aditus laryngis width of blade profile passage is 8 ~ 15 times of blade profile trailing edge axis of small circle.
7. convergent runner transonic turbine blade according to any one of claim 1 to 5, is characterized in that, in described N number of blade profile all or several blade profiles be positioned in the middle part of blade there is described indent molded line.
8. convergent runner transonic turbine blade according to any one of claim 1 to 5, it is characterized in that, described N number of blade profile divides along the geometric ratio branch on its center of gravity, leading edge, trailing edge, the string of a musical instrument or the geometric ratio on mean camber line that dot product is folded obtains the three-dimensional molded line of described convergent runner transonic turbine blade surface, and described long-pending folded long-pending superimposing thread is straight line or space curve.
9. comprise a turbine for the convergent runner transonic turbine blade according to any one of claim 1 to 8, it is characterized in that, comprising:
Turbine rotor; And
Described in several, convergent runner transonic turbine blade, is uniformly distributed circumferentially on the wheel hub surface of described turbine rotor.
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|---|---|---|---|
| CN201310364144.0A CN104420888B (en) | 2013-08-19 | 2013-08-19 | Convergent runner transonic turbine blade and apply its turbine |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310364144.0A CN104420888B (en) | 2013-08-19 | 2013-08-19 | Convergent runner transonic turbine blade and apply its turbine |
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| Publication Number | Publication Date |
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| CN104420888A CN104420888A (en) | 2015-03-18 |
| CN104420888B true CN104420888B (en) | 2016-04-20 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2019226060A1 (en) * | 2018-05-21 | 2019-11-28 | Abt Accord Spółka Z Ograniczoną Odpowiedzialnością | A turbine blade and a turbine comprising such a blade |
Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110566503B (en) * | 2019-10-10 | 2020-05-15 | 珠海格力电器股份有限公司 | Centrifugal fan blade, centrifugal fan, air conditioner and transportation means |
| CN111927560A (en) * | 2020-07-31 | 2020-11-13 | 中国航发贵阳发动机设计研究所 | Low-position air inlet vane type pre-rotation nozzle structure |
| CN112668122A (en) * | 2020-12-30 | 2021-04-16 | 哈尔滨汽轮机厂有限责任公司 | Turbine blade modeling design system based on python language |
Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3333817A (en) * | 1965-04-01 | 1967-08-01 | Bbc Brown Boveri & Cie | Blading structure for axial flow turbo-machines |
| FR2728618B1 (en) * | 1994-12-27 | 1997-03-14 | Europ Propulsion | SUPERSONIC DISTRIBUTOR OF TURBOMACHINE INPUT STAGE |
| US6358012B1 (en) * | 2000-05-01 | 2002-03-19 | United Technologies Corporation | High efficiency turbomachinery blade |
| EP2019186B1 (en) * | 2006-04-17 | 2016-01-06 | IHI Corporation | Blade |
| US8393872B2 (en) * | 2009-10-23 | 2013-03-12 | General Electric Company | Turbine airfoil |
-
2013
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2019226060A1 (en) * | 2018-05-21 | 2019-11-28 | Abt Accord Spółka Z Ograniczoną Odpowiedzialnością | A turbine blade and a turbine comprising such a blade |
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