CN108487943A - The casing and leaf top groove design method moved based on bimodal function control room clearance flow - Google Patents
The casing and leaf top groove design method moved based on bimodal function control room clearance flow Download PDFInfo
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- CN108487943A CN108487943A CN201810214041.9A CN201810214041A CN108487943A CN 108487943 A CN108487943 A CN 108487943A CN 201810214041 A CN201810214041 A CN 201810214041A CN 108487943 A CN108487943 A CN 108487943A
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- Prior art keywords
- casing
- leaf
- bimodal
- curved
- curved indentations
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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
-
- 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
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The casing and leaf top groove design method moved based on bimodal function control room clearance flow, belongs to the passive flow control technique field of turbomachine.The present invention is to solve the setting form of existing blade tip clearance so that leakage flow loses big problem.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；Curved indentations are set at the top of flat-top movable vane, and the side thickness of the curved indentations is that 1% leaf is high, and the bosom of curved indentations is no more than 4% leaf height；The bottom profile of curved indentations is identical as the corresponding position surface profile of casing inner wall curved surface；The wall upper surface of curved indentations is trimmed to leaf identical with casing inner wall curved surface corresponding position surface profile top external periphery outline again.The present invention can preferably control the leakage flow of impeller clearance.
Description
Technical field
The present invention relates to the casing moved based on bimodal function control room clearance flow and leaf top groove design methods, belong to turbine
The passive flow control technique field of tool.
Background technology
Turbine leaf top tip clearance leakage flow not only makes leaf top load reduction nearby, and increases flow losses.Study table
Bright, secondary flow loss only accounts for 10% in blade tip clearance flow region, and the loss of wall surface boundary-layer accounts for 3%, is lost then caused by gap
Up to 87%.Therefore, clearance leakage of blade tip flow mechanism is studied, leaf top and case structure are improved, to improving the flowing of the regions Ye Ding
Situation, reduction flow losses are particularly significant.
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.
Invention content
The invention aims to solve the setting form of existing blade tip clearance so that leakage flow loss is big to ask
Topic, provide it is a kind of based on bimodal function control room clearance flow move casing and leaf top groove design method.
The casing of the present invention moved based on bimodal function control room clearance flow and leaf top groove design method, 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；
Curved indentations are set at the top of flat-top movable vane, and the side thickness of the curved indentations is that 1% leaf is high, and curved indentations are most
It is high that depths is no more than 4% leaf；The bottom profile of curved indentations is identical as the corresponding position surface profile of casing inner wall curved surface；
The wall upper surface of curved indentations is trimmed to leaf identical with casing inner wall curved surface corresponding position surface profile again
Push up external periphery outline.
The movable vane is prismatic blade.
The domain of the radial position point y of casing is no more than 6mm.
The side thickness of the curved indentations is 2mm.
Advantages of the present invention：The present invention has re-started corresponding structure with casing to the blade and blade top of turbine and has improved, and
A curved indentations are provided at the top of movable vane.It can make the inner wall surface pressure of casing again using the Curvature varying of bimodal curve
Distribution forms the low-pressure area of two recess in blade suction surface side middle and back, keeps the position in upper channel whirlpool whole along leaf Gao Xiangji
Casket migrates, and the sphere of action in reduction upper channel whirlpool, the trend for delaying upper channel whirlpool downstream to expand reduces energy loss.Meanwhile
Large scale standing vortex can be formed inside the curved indentations being arranged on leaf top, occupy portion gap space, effective control gap
Leakage flow and then the energy loss for reducing leakage rate and its bringing, further increase the aeroperformance of leaf grating.
The turbine of the method for the present invention design has the advantages such as simple in structure, cost is relatively low, control effect is good.
Description of the drawings
Fig. 1 is to carry out casing and the organigram of leaf top groove union moulding using the method for the present invention；
Fig. 2 is the spanwise direction schematic diagram of the casing and leaf top groove using the method for the present invention construction；
Fig. 3 is the pitch direction schematic diagram of the casing and leaf top groove using the method for the present invention construction；
Fig. 4 is damaged with flat-top leaf grating outlet energy using the leaf grating after the method for the present invention construction casing and leaf top groove
Lose index contrast figure；
Fig. 5 is existing flat-top groove scheme pitot loss cloud charts and three-dimensional streamline distribution map；
Fig. 6 is the casing that the method for the present invention constructs and leaf top groove union modeling scheme pitot loss cloud charts and three-dimensional
Streamline distribution figure.
Specific implementation mode
The embodiments of the present invention will be described in detail below with reference to the drawings：
It is recessed based on the dynamic casing of bimodal function control room clearance flow and leaf top described in present embodiment in conjunction with shown in Fig. 1 to Fig. 3
Slot design 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；
The domain of the axial position point x of casing is 1% on rear side of 4 front side of blade and blade top leading edge, 1% axial chord length to trailing edge 5
Axial chord length；The domain of the radial position point y of casing is no more than 2.5% leaf height；It can take the radial position point y's of casing
Domain is no more than 6mm.
Curved indentations 7 are set at the top of flat-top movable vane, and the side thickness of the curved indentations 7 is that 1% leaf is high, curved indentations 7
To be no more than 4% leaf high in bosom；The corresponding position surface profile phase of the bottom profile of curved indentations 7 and casing inner wall curved surface 3
Together；The side thickness of the curved indentations 7 can be 2mm with value.
The wall upper surface of curved indentations 7 is trimmed to again identical with 3 corresponding position surface profile of casing inner wall curved surface
Leaf top external periphery outline 6.
In present embodiment, for the leaf top curved surface of movable vane piece, if leaf top surface, leaf will be moved on curved indentations 7
It is identical with the shape of casing inner wall curved surface 3 that external periphery outline 6, which is pushed up, with the leaf top curved surface that curved indentations 7 collectively form.
In present embodiment, the shape of curved indentations 7 can be made of 3 rank B-spline surfaces.Control point is from 8 in
It is obtained in the decile straight line of camber line, according to the horizontal orthogonal scheme of 24 factor 5, is built and controlled using Kriging methods
The agent model of point and gap leakage flow rate, optimizes it using genetic algorithm, obtains best free form surface groove scheme.
The setting of the leaf top external periphery outline 6 can guarantee that the value of blade tip clearance is constant, consistent with former gap size, keep away
The change for exempting from gap size has an impact aeroperformance.In general, the value of desirable blade tip clearance is high 1.5% of leaf.
Compared with other case structures being transformed by slot, crack structure, the casing curve of construction more connects present embodiment
Continuous fairing, smoothly transits and advantageously reduces loss coefficient.The bottom of curved indentations 7 also has the surface to smoothly transit,
Loss coefficient can be reduced.
Embodiment of the present invention can further decrease the energy loss of leaf grating, and can significantly inhibit the leakage rate in gap, whole
Body promotes the aeroperformance of turbine cascade.
The movable vane is prismatic blade.
Specific embodiment：
It is molded line to movable vane flat-top groove prototype leaf grating and by bimodal Gaussian function curve to verify the effect of the present invention
Treated casing and leaf top groove remodeling leaf grating carried out numerical simulation.Physical simulation parameter and the results are shown in table below：
Table
As shown in figure 4, by comparing the energy-loss factor of prototype and treated casing scheme it can be found that with flat-top groove
Prototype curve is compared, and bimodal Gaussian function curve is used to retrofit curve to upper channel whirlpool for the treated casing of molded line and leaf top groove
Influence it is more notable, its caused energy loss can be substantially reduced, can be reduced in the high range above of 90% leaf
Loss.Integral performance parameter shows that the treated casing scheme of the method for the present invention opposite can reduce 6.3% energy loss system
Number, and leakage rate is made to have dropped 7%.
In conjunction with Fig. 5 and Fig. 6, by comparing prototype and treated casing and leaf top groove repairing type scheme pitot loss cloud charts
And three-dimensional streamline distribution map is it can be found that in flat-top groove prototype, the circumferential sphere of action of upper channel whirlpool and leakage vortex almost one
It causes, it is oppositely oriented.And bimodal Gaussian function curve is used obviously to reduce the ruler of leakage vortex for the turbine upper end wall curved surface of molded line
Degree, although increasing the coverage in upper channel whirlpool, can reduce the sphere of action in upper channel whirlpool, make its adjacent circumferential expansion ruler
Degree is less than leakage vortex, effectively hinders the generation of leakage, largely avoids strong between leakage vortex and upper channel whirlpool mix
Mixed loss.Show that the present invention program can effectively inhibit the development in upper channel whirlpool, can significantly reduce the energy that upper channel vortex rope is come
Loss improves the aeroperformance of leaf grating entirety.
Claims (4)
1. a kind of casing moved based on bimodal function control room clearance flow and leaf top groove design method, 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；
Curved indentations (7) are set at the top of flat-top movable vane, and the side thickness of the curved indentations (7) is that 1% leaf is high, curved indentations
(7) it is high that bosom is no more than 4% leaf；The corresponding position surface of the bottom profile and casing inner wall curved surface (3) of curved indentations (7)
Profile is identical；
The wall upper surface of curved indentations (7) is trimmed to again identical with casing inner wall curved surface (3) corresponding position surface profile
Leaf top external periphery outline (6).
2. the casing according to claim 1 moved based on bimodal function control room clearance flow and leaf top groove design method,
It is characterized in that, the movable vane is prismatic blade.
3. the casing according to claim 1 or 2 moved based on bimodal function control room clearance flow and leaf top groove design method,
It is characterized in that, the domain of the radial position point y of casing is no more than 6mm.
4. the casing according to claim 1 or 2 moved based on bimodal function control room clearance flow and leaf top groove design method,
It is characterized in that, the side thickness of the curved indentations (7) is 2mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810214041.9A CN108487943A (en) | 2018-03-15 | 2018-03-15 | The casing and leaf top groove design method moved based on bimodal function control room clearance flow |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810214041.9A CN108487943A (en) | 2018-03-15 | 2018-03-15 | The casing and leaf top groove design method moved based on bimodal function control room clearance flow |
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| Publication Number | Publication Date |
|---|---|
| CN108487943A true CN108487943A (en) | 2018-09-04 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810214041.9A Pending CN108487943A (en) | 2018-03-15 | 2018-03-15 | The casing and leaf top groove design method moved based on bimodal function control room clearance flow |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114251130A (en) * | 2021-12-22 | 2022-03-29 | 清华大学 | Robust rotor structure and power system for controlling blade tip leakage flow |
| CN114517794A (en) * | 2022-03-01 | 2022-05-20 | 大连海事大学 | Transonic speed axial compressor combined casing treatment structure |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE102010050185A1 (en) * | 2010-10-30 | 2012-05-03 | Deutsches Zentrum für Luft- und Raumfahrt e.V. | Axial turbo machine for e.g. gas turbine, has inner radial gap formed between blade tip of vane and hub shaft, and comprising wave shape extending in flow direction with amplitude values of minima and maxima of hub shaft to each other |
| CN103410779A (en) * | 2013-08-30 | 2013-11-27 | 哈尔滨工业大学 | Flow separation method for stationary cascade of high-load axial flow air compressor |
| CN106368973A (en) * | 2016-11-09 | 2017-02-01 | 哈尔滨工业大学 | Gap flow control method used between fixed blade and end wall of gas compressor and gas compressor |
-
2018
- 2018-03-15 CN CN201810214041.9A patent/CN108487943A/en active Pending
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE102010050185A1 (en) * | 2010-10-30 | 2012-05-03 | Deutsches Zentrum für Luft- und Raumfahrt e.V. | Axial turbo machine for e.g. gas turbine, has inner radial gap formed between blade tip of vane and hub shaft, and comprising wave shape extending in flow direction with amplitude values of minima and maxima of hub shaft to each other |
| CN103410779A (en) * | 2013-08-30 | 2013-11-27 | 哈尔滨工业大学 | Flow separation method for stationary cascade of high-load axial flow air compressor |
| CN106368973A (en) * | 2016-11-09 | 2017-02-01 | 哈尔滨工业大学 | Gap flow control method used between fixed blade and end wall of gas compressor and gas compressor |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN114517794A (en) * | 2022-03-01 | 2022-05-20 | 大连海事大学 | Transonic speed axial compressor combined casing treatment structure |
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Application publication date: 20180904 |
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