CN108487942A - Control the casing and blade combined shaping method of turbine blade-tip gap flowing - Google Patents
Control the casing and blade combined shaping method of turbine blade-tip gap flowing Download PDFInfo
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- CN108487942A CN108487942A CN201810214025.XA CN201810214025A CN108487942A CN 108487942 A CN108487942 A CN 108487942A CN 201810214025 A CN201810214025 A CN 201810214025A CN 108487942 A CN108487942 A CN 108487942A
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Classifications
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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
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
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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
- F01D5/20—Specially-shaped blade tips to seal space between tips and stator
-
- 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
Abstract
The casing and blade combined shaping method for controlling turbine blade-tip gap flowing, belong to the passive flow control technique field of turbomachine.The present invention is easily to form mixing loss to solve leakage vortex and leaf grating upper channel whirlpool that the setting form of existing blade tip clearance generates, caused by the big problem of energy loss.It includes：In axial-flow turbine rotor leaf grating, using bimodal Gaussian function curve in finitely defined domain as the molded line in blade mean camber line pitch direction, the casing inner wall curved surface of continuous fairing is built；The domain of the axial position point x of casing is 1% axial chord length on rear side of trailing edge 1% axial chord length on front side of the leading edge of blade and blade top；The domain of the radial position point y of casing is no more than 2.5% leaf height.The present invention is by the casing of turbine and blade repeat style.
Description
Technical field
The present invention relates to the casings and blade combined shaping method of control turbine blade-tip gap flowing, belong to turbomachine quilt
Dynamic flow control technique field.
Background technology
There is the relative motion of friction to avoid movable vane and casing, can retain between turbine cascade and casing between leaf top
The presence of gap, blade tip clearance can make leak fluid accelerate to flow into leaf grating and be flowed out in its suction surface side, finally roll to be formed and let out
Leak whirlpool.Just because of the presence of leakage vortex, so that loss caused by leaf grating upper channel whirlpool is significantly stronger than lower channel whirlpool, therefore, let out
Therefore one of the main source that leakage whirlpool becomes leaf grating aerodynamic loss controls upper channel whirlpool using various flow control methods
Formation and development becomes the important means for improving Cascade Aerodynamics.
Currently, the flow control method for Passage Vortex is broadly divided into active Flow Control and passive two kinds of flowing control.
Wherein, active Flow Control method usually introduces external energy source, such as jet stream eddy generator and Plasma Actuator, this
Although kind of a method can be adjusted under different operating modes, realization is complicated, and cost is higher；And passive flow control method
The adjustment of stream field is mainly realized by changing geometry, the realization of such as wing fence, groove etc., this method is simple in structure, at
This is relatively low, but is limited by limited operating mode.For the complex environment with blade tip clearance, using passive control mode simple in structure
More meet actual demand.
To ensure there are certain nargin space between rotating vane and casing, existing treated casing research mostly use slot,
The form being combined is stitched, from the point of view of pitch direction, the upper end wall molded line of construction is satisfied by special zigzag distribution, usually comes
It says, fluid is minimum in the resistance that the surface flow of continuous fairing is subject to.
Invention content
The invention aims to solve the leakage vortex of the setting form of existing blade tip clearance generation and leaf grating upper channel whirlpool
Easily form mixing loss, caused by the big problem of energy loss, provide a kind of control turbine blade-tip gap flowing casing and
Blade combined shaping method.
The casing and blade combined shaping method of control turbine blade-tip gap flowing of the present invention, it includes：
In axial-flow turbine rotor leaf grating, using bimodal Gaussian function curve in finitely defined domain as blade mean camber line pitch
The molded line in direction builds the casing inner wall curved surface of continuous fairing；
The bimodal Gaussian function curve representation formula is：
Wherein x is the axial position point of casing, and y is the radial position point of casing, n1For first peak peak height coefficient, n2It is
One peak peak height position parameter, n3For first peak peak width coefficient, n4For the second peak peak height coefficient, n5For the second peak peak height position parameter,
n6For the second peak peak width coefficient；
The domain of the axial position point x of casing is 1% axis on rear side of 1% axial direction chord length to trailing edge of blade and blade top leading edge front side
To chord length；The domain of the radial position point y of casing is no more than 2.5% leaf height.
Further, it further includes construction curved surface patch identical with casing inner wall curved surface, and the curved surface patch is used for phase
That answers is placed in the upper surface on blade and blade top.
Further, the blade is prismatic blade.
Advantages of the present invention：The present invention is using bimodal Gaussian function curve in finitely defined domain as the type in mean camber line pitch direction
Line builds the three-dimensional turbine upper end wall curved surface of continuous fairing, it makes casing inner wall (on turbine by the Curvature varying of bimodal curve
End wall) surface pressure redistribution, can make blade suction surface side middle and back formed two recess low-pressure areas, make on blade lead to
The position in road whirlpool is whole to be migrated along leaf height to casing direction, reduces its sphere of action, and upper channel whirlpool is delayed downstream to expand
Trend effectively improves the mobility status in flow field, reduces the loss of turbine cascade rotor energy.
Casing and blade construction after being reconfigured using the method for the present invention is simple, and constructions cost is relatively low, to channel
The control effect in whirlpool is good.
Description of the drawings
Fig. 1 is the organigram that casing and blade combined shaping are carried out using the method for the present invention；
Fig. 2 is the pitch direction schematic diagram using the casing of the method for the present invention construction；
Fig. 3 is compared with flat-top leaf grating outlet energy-loss factor using the leaf grating after the method for the present invention construction casing
Figure；
Fig. 4 is the existing secondary motion pattern in flat-top leaf grating outlet for considering blade tip clearance；
Fig. 5 is using the secondary motion pattern in leaf grating outlet after the method for the present invention construction casing；
Fig. 6 is the relative position relation schematic diagram of casing and blade；
Fig. 7 is by the structural schematic diagram after casing in Fig. 6 and leaf decomposition；
Fig. 8 is the radial cross section of Fig. 6；
Fig. 9 is the pitot loss cloud charts of flat-top leaf grating prototype and three-dimensional streamline distribution map；
Figure 10 is the casing remodeling pitot loss cloud charts and three-dimensional streamline distribution map using the method for the present invention construction.
Specific implementation mode
The embodiments of the present invention will be described in detail below with reference to the drawings：
In conjunction with shown in Fig. 1 and Fig. 2, the casing and blade of control turbine blade-tip gap flowing described in present embodiment, which are combined, to be made
Type method, it includes：
In axial-flow turbine rotor leaf grating 1, saved by blade mean camber line 2 of bimodal Gaussian function curve in finitely defined domain
Molded line away from direction builds the casing inner wall curved surface 3 of continuous fairing；
The bimodal Gaussian function curve representation formula is：
Wherein x is the axial position point of casing, and y is the radial position point of casing, n1For first peak peak height coefficient, n2It is
One peak peak height position parameter, n3For first peak peak width coefficient, n4For the second peak peak height coefficient, n5For the second peak peak height position parameter,
n6For the second peak peak width coefficient；
In conjunction with shown in Fig. 1 and Fig. 2, the domain of the axial position point x of casing is that leading edge 4 front side 1% in blade and blade top is axial
1% axial chord length on rear side of chord length to trailing edge 5；The domain of the radial position point y of casing is no more than 2.5% leaf height, Ke Yiqu
The value of radial position point y is no more than 6mm.
Compared with other case structures being transformed by slot, crack structure, the casing curve of construction more connects present embodiment
Continuous fairing, advantageously reduces loss coefficient, and be conducive to process.The case structure that present embodiment is constructed passes through 6
Coefficient (n1、n2、n3、n4、n5And n6) to close determine, be easy to the optimization of scheme.The case structure of the method for the present invention construction is being protected
While card does not increase leakage, the loss caused by upper channel whirlpool is reduced, the promotion of aerodynamic performance of turbine cascade is realized.
Since the concrete shape of bimodal Gaussian function curve in the disclosure is determined by 6 coefficients, horizontal according to 6 factor 5
Orthogonal scheme can utilize the agent model of Kriging method constructor coefficient and outlet energy loss, and
It is optimized using genetic algorithm, obtains best bimodal curve scheme.
Shown in Fig. 2, embodiments of the present invention further include construction curved surface patch 6 identical with casing inner wall curved surface 3, described
Curved surface patch 6 is used to be placed in the upper surface on blade and blade top accordingly.It is to ensure in vane tip installation curved surface patch 6
The value of blade tip clearance is constant, consistent with former gap size, and the change of gap size is avoided to have an impact aeroperformance.In general,
The value of desirable blade tip clearance is high 2.5% of leaf.
Fig. 6 to Fig. 8 gives the clearly signal of the case structure constructed using the method for the present invention, the inner wall curved surface of casing
It is stretched along pitch direction (vane thickness direction) by the bimodal function curve of Gauss, for casing, function curve peak
Value point is treated casing deepest point, and for movable vane piece, function curve peak point is repairing type rear blade peak.
Blade described in embodiments of the present invention is prismatic blade.
Specific embodiment：
It is molded line to movable vane flat-top gap prototype leaf grating and by bimodal Gaussian function curve to verify the effect of the present invention
Treated casing leaf grating carried out numerical simulation.Physical simulation parameter and the results are shown in table below：
Table
As shown in figure 3, by comparing the energy-loss factor of prototype and treated casing scheme it can be found that with flat-top prototype
Leaf grating curve is compared, and uses influence of the bimodal Gaussian function curve for the casing inner wall Curve On The Surface of molded line to upper channel whirlpool more
Significantly, it can be substantially reduced its caused energy loss, the loss in the high range above of 90% leaf can be reduced.Globality
Energy parameter shows that the treated casing scheme of the method for the present invention opposite can reduce 10.9% stagnation pressure energy-loss factor, and makes
Leakage rate has dropped 17.8%.
In conjunction with shown in Fig. 4 and Fig. 5 and Fig. 9 and Figure 10, by comparing prototype and treated casing scheme outlet Secondary Flow
For line chart it can be found that in flat-top prototype leaf grating, the circumferential sphere of action of upper channel whirlpool and leakage vortex is almost consistent, oppositely oriented.
And bimodal Gaussian function curve is used obviously to reduce the scale of leakage vortex for the turbine upper end wall curved surface of molded line, although increasing
The coverage in upper channel whirlpool, but the sphere of action in upper channel whirlpool can be reduced, so that its adjacent circumferential expansion scale is less than leakage vortex,
The generation for effectively hindering leakage, largely avoids mixing loss strong between leakage vortex and upper channel whirlpool.Show this
Scheme of the invention can effectively inhibit the development in upper channel whirlpool, can significantly reduce the energy loss that upper channel vortex rope is come, and improve leaf grating
Whole aeroperformance.
Claims (3)
1. a kind of casing and blade combined shaping method of the flowing of control turbine blade-tip gap, which is characterized in that it includes：
In axial-flow turbine rotor leaf grating (1), saved using bimodal Gaussian function curve in finitely defined domain as blade mean camber line (2)
Molded line away from direction builds the casing inner wall curved surface (3) of continuous fairing；
The bimodal Gaussian function curve representation formula is：
Wherein x is the axial position point of casing, and y is the radial position point of casing, n1For first peak peak height coefficient, n2For first peak
Peak height position parameter, n3For first peak peak width coefficient, n4For the second peak peak height coefficient, n5For the second peak peak height position parameter, n6For
Second peak peak width coefficient；
The domain of the axial position point x of casing is 1% on rear side of 1% axial direction chord length to trailing edge (5) of blade and blade top leading edge (4) front side
Axial chord length；The domain of the radial position point y of casing is no more than 2.5% leaf height.
2. the casing and blade combined shaping method of control turbine blade-tip gap flowing according to claim 1, feature
It is, it further includes construction and the identical curved surface patch (6) of casing inner wall curved surface (3), and the curved surface patch (6) is for corresponding
It is placed in the upper surface on blade and blade top.
3. the casing and blade combined shaping method of control turbine blade-tip gap flowing according to claim 1 or 2, special
Sign is that the blade is prismatic blade.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810214025.XA CN108487942A (en) | 2018-03-15 | 2018-03-15 | Control the casing and blade combined shaping method of turbine blade-tip gap flowing |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810214025.XA CN108487942A (en) | 2018-03-15 | 2018-03-15 | Control the casing and blade combined shaping method of turbine blade-tip gap flowing |
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| CN108487942A true CN108487942A (en) | 2018-09-04 |
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| CN201810214025.XA Pending CN108487942A (en) | 2018-03-15 | 2018-03-15 | Control the casing and blade combined shaping method of turbine blade-tip gap flowing |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111006873A (en) * | 2019-12-05 | 2020-04-14 | 中国航发四川燃气涡轮研究院 | Method and device for acquiring peak value in blade tip clearance signal processing process |
| CN111460592A (en) * | 2020-04-03 | 2020-07-28 | 中国航发沈阳发动机研究所 | Blade profile and method for designing camber line thereof |
| CN113153447A (en) * | 2021-04-25 | 2021-07-23 | 西安交通大学 | Pre-rotation structure for strengthening cooling of leakage flow of turbine stationary blade end wall |
| CN114251130A (en) * | 2021-12-22 | 2022-03-29 | 清华大学 | Robust rotor structure and power system for controlling blade tip leakage flow |
| CN114962329B (en) * | 2022-05-27 | 2024-04-26 | 哈尔滨工程大学 | Compressor rotor clearance structure and application |
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| US4013376A (en) * | 1975-06-02 | 1977-03-22 | United Technologies Corporation | Coolable blade tip shroud |
| JPH0726904A (en) * | 1993-07-12 | 1995-01-27 | Ishikawajima Harima Heavy Ind Co Ltd | Blade tip structure of rotating machine |
| US20040028526A1 (en) * | 2002-08-09 | 2004-02-12 | Honda Giken Kogyo Kabushiki Kaisha | Axial flow compressor |
| CN102099548A (en) * | 2008-07-17 | 2011-06-15 | 西门子公司 | Axial turbine for a gas turbine with limited play between blades and housing |
| CN102099547A (en) * | 2008-07-17 | 2011-06-15 | 西门子公司 | Axial turbo engine with low gap losses |
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| CN104722368A (en) * | 2013-12-20 | 2015-06-24 | 耐驰干法研磨技术有限公司 | Machine Having A Cantilever-mounted Rotor |
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Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
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| US4013376A (en) * | 1975-06-02 | 1977-03-22 | United Technologies Corporation | Coolable blade tip shroud |
| JPH0726904A (en) * | 1993-07-12 | 1995-01-27 | Ishikawajima Harima Heavy Ind Co Ltd | Blade tip structure of rotating machine |
| US20040028526A1 (en) * | 2002-08-09 | 2004-02-12 | Honda Giken Kogyo Kabushiki Kaisha | Axial flow compressor |
| CN102099548A (en) * | 2008-07-17 | 2011-06-15 | 西门子公司 | Axial turbine for a gas turbine with limited play between blades and housing |
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| CN104722368A (en) * | 2013-12-20 | 2015-06-24 | 耐驰干法研磨技术有限公司 | Machine Having A Cantilever-mounted Rotor |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111006873A (en) * | 2019-12-05 | 2020-04-14 | 中国航发四川燃气涡轮研究院 | Method and device for acquiring peak value in blade tip clearance signal processing process |
| CN111006873B (en) * | 2019-12-05 | 2022-02-01 | 中国航发四川燃气涡轮研究院 | Method and device for acquiring peak value in blade tip clearance signal processing process |
| CN111460592A (en) * | 2020-04-03 | 2020-07-28 | 中国航发沈阳发动机研究所 | Blade profile and method for designing camber line thereof |
| CN111460592B (en) * | 2020-04-03 | 2023-08-04 | 中国航发沈阳发动机研究所 | Leaf profile and camber line design method thereof |
| CN113153447A (en) * | 2021-04-25 | 2021-07-23 | 西安交通大学 | Pre-rotation structure for strengthening cooling of leakage flow of turbine stationary blade end wall |
| CN114251130A (en) * | 2021-12-22 | 2022-03-29 | 清华大学 | Robust rotor structure and power system for controlling blade tip leakage flow |
| CN114251130B (en) * | 2021-12-22 | 2022-12-02 | 清华大学 | Robust rotor structure and power system for controlling blade tip leakage flow |
| CN114962329B (en) * | 2022-05-27 | 2024-04-26 | 哈尔滨工程大学 | Compressor rotor clearance structure and application |
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Application publication date: 20180904 |