CN103982462B - A kind of waveform jetting method of blade trailing edge - Google Patents
A kind of waveform jetting method of blade trailing edge Download PDFInfo
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- CN103982462B CN103982462B CN201410150792.0A CN201410150792A CN103982462B CN 103982462 B CN103982462 B CN 103982462B CN 201410150792 A CN201410150792 A CN 201410150792A CN 103982462 B CN103982462 B CN 103982462B
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Abstract
The present invention relates to a kind of waveform jetting method of blade trailing edge, belong to mechanical device and technical field of transportation.The present invention starts with from pneumatic means, offers identical rectangular slits along blade exhibition to each position, forms jet seam, to realize the mechanism of the effect of entity lobe structure; By modeling numerical calculation check is carried out to model, the final shaping trailing edge jet scheme, add spoiler and control each spoiler aperture size (i.e. spoiler and the overlapping area cracked), the disturbance of being processed into wavy velocity distribution designed by actual blade can play reduction fan, gas compressor noise; Reduce turbine noise, make the effect that downstream turbine vane inlet gas flow temperature is evenly distributed.This design method is simple, flexible, practical, is specially adapted to aviation/ground gas turbine field.
Description
Technical field
The present invention relates to a kind of waveform jetting method of blade trailing edge, belong to mechanical device and technical field of transportation.
Background technique
Answer national defence, economic construction development need, propose requirements at the higher level to aviation/ground gas turbine performance, this is comprising reduction fan/compressor noise, raising turbine inlet temperature (TIT).In order to realize this requirement, researcher proposes trailing edge and to crack jet-stream wind method, and has obtained successfully.But after trailing edge jet, blade exit air-flow ricing is still higher, reduces its noise reduction, cooling effect.
This respect, aero-gas turbine lobe nozzle technology provides reference thinking for reducing blade exit air-flow ricing further.Lobe nozzle proposed in 1970 mid-nineties 90s, this technology is by being designed to some lobe shapes of circumferential period profile and strengthening the blending of jet pipe afterbody jet and main flow by jet pipe tail edge, reduce main flow and jet speed poor, reduce temperature, thus reach the object making uniform stream, reduce noise, reduce infrared radiation.Such as, the discoveries such as Bradbury, Ahuja: when installing after small tabs in outside nozzle, can strengthen mixing of tail jet and ambient windstream, the speed exhaustion of tail jet is accelerated, and the core area of tail jet shortens.Lobe forces mixing tube and polytype mixer (as collaborated confluent, spray injection, vortex generator vortexgenerator) to compare discovery by P.K.Shumpert, lobed mixer can make be tending towards Homogeneous phase mixing inside and outside culvert in very short mixing distance, when mixing tube slenderness ratio equals 2, mixing efficiency reaches more than 80%, is better than other mixer.Between 1976-1982, General Electric Co. Limited (GE) is carried out the experimental research of system to the geometrical shape of lobed mixer at the exhaust gas mixing system of development E3 motor, research shows that depth of penetration has the greatest impact, and the spacing suitably reducing lobe and center cone is very favourable to the raising of blending efficiency.Be subject to above-mentioned research to inspire, if this technology can be adopted in the turbine such as fan/compressor, turbine, also will produce similar excellent effect.But, because blade is usually thinner, as sporocarp geometry adopts wave-pieced type trailing edge, will unavoidably cause blade structure strength deficiency.
Summary of the invention
The object of the invention is to reduce fan, gas compressor noise; Reducing turbine noise, downstream turbine vane inlet gas flow temperature is evenly distributed, providing a kind of by controlling trailing edge jet speed, make air-flow in exhibition to presenting uneven distribution thus improving the method for exit flow blending.
In order to achieve the above object, the present invention adopts following technological scheme:
Step 1, adopts the original blade profile of the method design of conventional mean camber line and thickness distribution.Wherein, mean camber line given way has single circular arc, bicircular arcs, many circular arcs, multinomial etc., and thickness distribution has NACA series etc.
Step 2, modeling also carries out numerical calculation check to model.Concrete grammar is:
Step 2.1, sets up Three-dimension Numerical Model to the original blade profile that step 1 designs, opens rectangular slits along trailing edge central position, forms jet seam;
The broadside of described seam is vertical with blade profile mean camber line, and seam broadside is offered by blade trailing edge mean camber line both sides symmetry, and long side direction is parallel with blade profile trailing edge place mean camber line; The Extreme breadth of seam is the half of this blade profile trailing edge radius of arc, and blade profile mean camber line direction, long edge extends to trailing edge border.
Step 2.2, in blade interior, selected n location point is as the location point of plan interpolation spoiler arbitrarily, and the location point of plan interpolation spoiler is positioned at jet seam outlet port and edge is opened up to being uniformly distributed.The spoiler number that wherein value of n is added by design is determined.
Step 2.3, the location point that selected for step 2.2 n is intended adding spoiler is divided into s group (2 < s < 100 successively, during first simulation, s is any value), each group except last group to comprise location point number identical.
The method often being organized the effluxvelocity size that the corresponding trailing edge of location point cracks by setting reaches the effect simulating spoiler coutroi velocity, concrete grammar is: setting is often organized the effluxvelocity that in location point, the corresponding trailing edge of each point cracks and varied in size, and the effluxvelocity that the trailing edge of each group correspondence cracks is by period profile, thus form the identical waveform of s wavelength.The corresponding wave period of one group of location point, along exhibition to effluxvelocity and wavelength form the effect of lobe nozzle external form (namely trailing edge jet presents period profile).
Step 2.4, each plan that regulating step 2.3 sets adds the effluxvelocity size of spoiler location point, thus changes the wave amplitude size of waveform, controls the waveform shape in a wavelength, makes waveform top speed V
maxmean velocity mixed with air-flow
there is following provisions scope,
Step 2.5, the import of fixed model, exit condition, under the effluxvelocity situation of spoiler location point is added in the grouping of step 2.3 and each plan of step 2.4 setting, calculate turbine pneumatic results of property, and by compared with turbine outlet pitot loss condition given to turbine pneumatic results of property and designing requirement, if result meets pitot loss condition, then the wave amplitude size of n that step 2.3 the is selected location point and grouping situation and correspondence intending adding spoiler is as the final shaping trailing edge jet scheme.If result is discontented with sufficient pitot loss condition, then by again being divided into groups by n location point place spoiler, change packet count s, thus change waveform quantity and effluxvelocity, re-execute step 2.3 to step 2.5, until turbine pneumatic results of property meets pitot loss condition.
Because along exhibition to the waveform quantity formed
wherein λ is the wavelength of each waveform, and h is that leaf is high, i.e. the extreme length of wavelength, and therefore waveform quantity and wavelength are inversely proportional to.
The wavelength that different groupings is corresponding different, the corresponding different wave amplitude of different effluxvelocities.
Step 3, according to the final shaping trailing edge jet scheme that step 2 obtains, adds spoiler and controls each spoiler aperture size (i.e. spoiler and the overlapping area cracked), being processed into actual blade.
The jet that the spoiler of different opening size is corresponding stitches the effluxvelocity difference exporting effluent stream; When spoiler surface is parallel with the broadside that cracks, then there is no air-flow from middle outflow of cracking; When spoiler surface is vertical with the broadside that cracks, then airspeed is maximum value.
The turbine blade tail that method described in step 1 to step 3 of the present invention is applicable to fan and gas compressor cracks jet-stream wind design.
Beneficial effect
The present invention starts with from pneumatic means, adopts the direct waveform of trailing edge to spray the mechanism of the effect to realize entity lobe structure; The disturbance of designed wavy velocity distribution can be played and reduce fan, gas compressor noise; Reduce turbine noise, make the effect that downstream turbine vane inlet gas flow temperature is evenly distributed.This design method is simple, flexible, practical, is specially adapted to aviation/ground gas turbine field.
Accompanying drawing explanation
Fig. 1 is the original two dimensional blade profile of prior art;
Fig. 2 is the two-dimentional blade profile with wavy jet of the present invention; Wherein (a) is blade profile overall structure, and (b) is trailing edge partial enlarged drawing.
Fig. 3 is the trailing edge jet schematic diagram in embodiment; Letter and number implication in figure is: 1 represents spoiler, and Vmax is wave amplitude (i.e. maximum effluxvelocity), and λ is wavelength;
Fig. 4 is the trailing edge jet parameters figure in embodiment;
Fig. 5 is the Numerical Simulation Results of embodiment, and the quantity of waveform is 5.Wherein (a) is Uniform jet simulation result, and (b) is for having the simulation result of wavy jet.
Embodiment
In order to better objects and advantages of the present invention are described, below in conjunction with drawings and Examples, content of the present invention is described further.
This example method according to summary of the invention redesigns an axial flow turbine vane foil, and verifies its action effect by numerical method.The relevant aerodynamic parameter of the present embodiment is as follows: import stagnation pressure 111325Pa, exit static pressure 90000Pa.Designing requirement pitot loss can not lower than 90%, therefore proposal plan requires formation 5 waveforms, and namely periodicity is 5 cycles, namely at least needs 5 groups of spoilers, and often group has 10 spoiler set-points.
Step 1, provides turbine vane type according to certain original blade profile data and conventional method, as shown in Figure 1.And determine its aeroperformance by numerical simulation.Goldman turbine vane type is selected in this example.
Step 2, modeling also carries out numerical calculation check to model.Concrete grammar is:
Step 2.1, sets up Three-dimension Numerical Model to the original blade profile that step 1 designs, and rectangular slits is offered in the trailing edge center of arc position in selected model cross section, and the width edge length of this rectangular slits is the half of this blade profile trailing edge radius of arc, and long limit extends to the external boundary of trailing edge.Then offer identical rectangular slits along blade exhibition to each position, form jet seam.Described rectangular slits wide vertical with blade profile mean camber line, the wide mid point of rectangle is positioned at the place of center of arc of trailing edge, and the long limit of rectangle is parallel with the mean camber line at trailing edge place, blade profile cross section.As shown in Figure 2.
Step 2.2, in blade interior, selected 50 location points are as intending the location point adding spoiler arbitrarily, and the location point intending adding spoiler is positioned at jet seam outlet port and extends to being uniformly distributed.
Step 2.3, is divided into 5 groups successively by the location point that selected for step 2.2 50 are intended adding spoiler, has 10 location points intending adding spoiler in each group.
The method often being organized the effluxvelocity size that the corresponding trailing edge of location point cracks by setting reaches the effect simulating spoiler coutroi velocity, concrete grammar is: setting is often organized the effluxvelocity that in location point, the corresponding trailing edge of each point cracks and varied in size, and the effluxvelocity that the trailing edge of each group correspondence cracks is by period profile, thus form the identical waveform of 5 wavelength.The corresponding wave period of one group of location point, along exhibition to effluxvelocity and wavelength form the effect of lobe nozzle external form (namely trailing edge jet presents period profile).
Step 2.4, each plan that regulating step 2.3 sets adds the effluxvelocity size of spoiler location point, thus changes the wave amplitude size of waveform, controls the waveform shape in a wavelength, makes waveform top speed V
maxmean velocity mixed with air-flow
there is following provisions scope,
in this example, the boundary conditions of setting rectangular slits is pressure export condition, and the pressure maximum that each group intends 10 points of the location point adding spoiler is 92000Pa, and minimum pressure values is 90000Pa; The numerical relation of all the other each points in one-period is sinusoidal distribution.
Step 2.5, condition for import is pressure entrance, and stagnation pressure is 111325Pa, and exit condition is pressure export, and static pressure is 90000Pa.Set in the grouping of step 2.3 and step 2.4 each intend the effluxvelocity situation of adding spoiler location point under, calculate turbine pneumatic results of property, and by compared with turbine outlet pitot loss condition given to turbine pneumatic results of property and designing requirement.Result meets pitot loss condition, so the wave amplitude size of 50 that step 2.3 the are selected location points and grouping situation and correspondence intending adding spoilers is as the final shaping trailing edge jet scheme.
Step 3, according to the final shaping trailing edge jet scheme that step 2 obtains, adds spoiler and controls each spoiler aperture size (i.e. spoiler and the overlapping area cracked), being processed into actual blade.
Carry out three-dimensional CFD numerical simulation result as shown in Figure 5 to the present embodiment, therefrom can obtain, the exhibition of trailing edge jet velocity, after uneven distribution, can reduce blade exit air-flow ricing, reduces outlet pitot loss.Numerical simulation result shows that the disturbance that the jet wavy distribution of trailing edge causes can play the ricing reducing downstream blade entrance and the effect reducing outlet pitot loss.
Above-described specific descriptions; the object of inventing, technological scheme and beneficial effect are further described; be understood that; the foregoing is only specific embodiment of the invention case; for explaining the present invention, the protection domain be not intended to limit the present invention, within the spirit and principles in the present invention all; any amendment of making, equivalent replacement, improvement etc., all should be included within protection scope of the present invention.
Claims (5)
1. a waveform jetting method for blade trailing edge, is characterized in that: comprise the steps:
Step 1, adopts the original blade profile of the method design of conventional mean camber line and thickness distribution;
Step 2, modeling also carries out numerical calculation check to model; Concrete grammar is:
Step 2.1, sets up Three-dimension Numerical Model to the original blade profile that step 1 designs, opens rectangular slits along trailing edge central position, forms jet seam;
The broadside of described seam is vertical with blade profile trailing edge place mean camber line, and seam broadside is offered by blade profile trailing edge place mean camber line both sides symmetry, and long side direction is parallel with blade profile trailing edge place mean camber line; The Extreme breadth of seam is the half of this blade profile trailing edge place radius of arc, and mean camber line direction, blade profile trailing edge place, long edge extends to trailing edge border;
Step 2.2, in blade interior, selected n location point is as the location point of plan interpolation spoiler arbitrarily, and the location point of plan interpolation spoiler is positioned at jet seam outlet port and edge is opened up to being uniformly distributed; The spoiler number that wherein value of n is added by design is determined;
Step 2.3, the location point intending adding spoiler by selected for step 2.2 n is divided into s group, 2 < s < 100 successively, and when simulating for the first time, s is any value, and each group except last group to comprise location point number identical;
The method often being organized the effluxvelocity size that the corresponding trailing edge of location point cracks by setting reaches the effect simulating spoiler coutroi velocity, concrete grammar is: setting is often organized the effluxvelocity that in location point, the corresponding trailing edge of each point cracks and varied in size, and the effluxvelocity that the trailing edge of each group correspondence cracks is by period profile, thus form the identical waveform of s wavelength; The corresponding wave period of one group of location point, along exhibition to effluxvelocity and wavelength form the effect of lobe nozzle external form;
Step 2.4, each plan that regulating step 2.3 sets adds the effluxvelocity size of spoiler location point, changes the wave amplitude size of waveform, controls the waveform shape in a wavelength, make waveform top speed V
maxmean velocity mixed with air-flow
there is following provisions scope,
Step 2.5, the condition for import of fixed model, the exit condition of fixed model, under the effluxvelocity situation of spoiler location point is added in the grouping of step 2.3 and each plan of step 2.4 setting, calculate turbine pneumatic results of property, and by compared with turbine outlet pitot loss condition given to turbine pneumatic results of property and designing requirement, if result meets pitot loss condition, then the wave amplitude size of n that step 2.3 the is selected location point and grouping situation and correspondence intending adding spoiler is as the final shaping trailing edge jet scheme; If result is discontented with sufficient pitot loss condition, then by again being divided into groups by n location point place spoiler, change packet count s, thus change waveform quantity and effluxvelocity, re-execute step 2.3 to step 2.5, until turbine pneumatic results of property meets pitot loss condition;
Step 3, according to the final shaping trailing edge jet scheme that step 2 obtains, adds spoiler and controls each spoiler aperture size, being processed into actual blade.
2. the waveform jetting method of a kind of blade trailing edge according to claim 1, is characterized in that: the extreme length of wavelength is that leaf is high, and waveform quantity and wavelength are inversely proportional to.
3. the waveform jetting method of a kind of blade trailing edge according to claim 1, is characterized in that: the wavelength that different groupings is corresponding different, the corresponding different wave amplitude of different effluxvelocities.
4. the waveform jetting method of a kind of blade trailing edge according to claim 1, is characterized in that: the jet that the spoiler of different opening size is corresponding stitches the effluxvelocity difference exporting effluent stream; When spoiler surface is parallel with the broadside that cracks, then there is no air-flow from middle outflow of cracking; When spoiler surface is vertical with the broadside that cracks, then airspeed is maximum value.
5. the waveform jetting method of a kind of blade trailing edge according to claim 1, is characterized in that: the turbine blade tail that the method described in step 1 to step 3 is applicable to fan and gas compressor cracks jet-stream wind design.
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| CN105569740A (en) * | 2016-03-03 | 2016-05-11 | 哈尔滨工程大学 | Turbine with blade wavy concave tailing edge slot cooling structures |
| CN107704665A (en) * | 2017-09-16 | 2018-02-16 | 吉利汽车研究院（宁波）有限公司 | Vehicle-mounted fan design method |
| CN111692117A (en) * | 2020-05-22 | 2020-09-22 | 哈尔滨工业大学 | Gas compressor active flow control method and device based on sweep frequency type ejector |
| CN112651075B (en) * | 2020-10-30 | 2022-11-04 | 中国直升机设计研究所 | Design method of spoiler for weakening tail screen movement of helicopter |
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| EP1605134A2 (en) * | 2004-05-28 | 2005-12-14 | General Electric Company | Device for balancing a gas turbine rotor and gas turbine engine comprising such a device |
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| CN102163244A (en) * | 2010-12-30 | 2011-08-24 | 北京理工大学 | Method for dolphin head-shaped processing of blade leading edge |
| CN102167163A (en) * | 2011-03-25 | 2011-08-31 | 北京航空航天大学 | Synthetic jet circulation control method for increasing wing lifting force |
| CN103790639A (en) * | 2013-12-26 | 2014-05-14 | 北京理工大学 | Method for edge strip shape modifying of front edge of end area blade of turbine |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| US6979178B2 (en) * | 2001-06-18 | 2005-12-27 | Bharat Heavy Electricals Ltd. | Cylindrical blades for axial steam turbines |
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Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1605134A2 (en) * | 2004-05-28 | 2005-12-14 | General Electric Company | Device for balancing a gas turbine rotor and gas turbine engine comprising such a device |
| CN101109396A (en) * | 2007-08-09 | 2008-01-23 | 上海交通大学 | Impeller mechanical wing profile with trailing edge ejection |
| CN102163244A (en) * | 2010-12-30 | 2011-08-24 | 北京理工大学 | Method for dolphin head-shaped processing of blade leading edge |
| CN102167163A (en) * | 2011-03-25 | 2011-08-31 | 北京航空航天大学 | Synthetic jet circulation control method for increasing wing lifting force |
| CN103790639A (en) * | 2013-12-26 | 2014-05-14 | 北京理工大学 | Method for edge strip shape modifying of front edge of end area blade of turbine |
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