CN103982462A - Wavelike jet method for blade trailing edges - Google Patents
Wavelike jet method for blade trailing edges Download PDFInfo
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- CN103982462A CN103982462A CN201410150792.0A CN201410150792A CN103982462A CN 103982462 A CN103982462 A CN 103982462A CN 201410150792 A CN201410150792 A CN 201410150792A CN 103982462 A CN103982462 A CN 103982462A
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Abstract
The invention relates to a wavelike jet method for blade trailing edges, which belongs to the technical fields of mechanical devices and transportation. Starting with a pneumatic means, identical rectangular slots are arranged at all the positions along the spanwise direction of a blade, so that jet slots are formed to realize the mechanism of the effect of a physical lobe structure; by creating a model and carrying out numerical calculation to check the model, a trailing edge jet scheme is finalized, spoilers are added, moreover, the opening degree (i.e., the superposing area between the spoilers and the slots) of each spoiler is controlled, and thereby the actual blade is worked out. The disturbance of designed wavelike velocity distribution can achieve the effects of reducing the noise of a fan, a compressor and a turbine and uniformly distributing the inlet flow temperature of downstream turbine blades. The design method is simple, flexible, practical and particularly suitable for the field of aeronautic/ground gas turbines.
Description
Technical field
The present invention relates to a kind of waveform jetting method of blade trailing edge, belong to mechanical device and transportation technology field.
Background technique
Answer national defence, economic construction development need, aviation/ground gas turbine performance is proposed to requirements at the higher level, this is comprising reducing fan/compressor noise, improving turbine inlet temperature (TIT).In order to realize this requirement, researcher has proposed the trailing edge jet-stream wind method of cracking, and has obtained successfully.Yet after trailing edge jet, blade exit air-flow ricing is still higher, has weakened its noise reduction, cooling effect.
This respect, aero-gas turbine lobe nozzle technology provides reference thinking for further reducing blade exit air-flow ricing.Lobe nozzle proposed in 1970 mid-nineties 90s, this technology strengthens the blending of jet pipe afterbody jet and main flow by jet pipe tail edge being designed to some lobe shapes of circumferential period profile, reduce main flow and jet speed is poor, reduce temperature, thereby reach, make the object that air-flow is even, reduce noise, reduction infrared radiation.For example, the discoveries such as Bradbury, Ahuja: after small tabs being installed in outside nozzle, can strengthen mixing of tail jet and ambient windstream, make the speed exhaustion quickening of tail jet, the core area of tail jet shortens.P.K.Shumpert forces mixing tube and polytype mixer (as interflow confluent, injection injection, vortex generator vortex generator) relatively to find lobe, lobed mixer can make be tending towards even mixing inside and outside culvert in very short mixing distance, in mixing tube slenderness ratio, equal at 2 o'clock, mixing efficiency reaches more than 80%, is better than other mixer.Between 1976-1982, General Electric Co. Limited (GE) is the geometrical shape of lobed mixer have been carried out to the experimental research of system at the exhaust gas mixing system of development E3 motor, research shows that depth of penetration has the greatest impact, and the spacing that suitably reduces lobe and center cone is very favourable to the raising of blending efficiency.Be subject to above-mentioned research and inspire, if can adopt this technology in the turbines such as fan/compressor, turbine, also will produce similar excellent effect.Yet, because blade is conventionally thinner, as sporocarp adopts wave-pieced type trailing edge how much, will unavoidably cause blade structure strength deficiency.
Summary of the invention
The object of the invention is in order to reduce fan, gas compressor noise; Reduce turbine noise, make downstream turbine blade inlet air flow uniformity of temperature profile, provide a kind of by controlling trailing edge jet speed, thus make air-flow in exhibition to the method that presents uneven distribution and improve exit flow blending.
In order to achieve the above object, the present invention adopts following technological scheme:
Step 1, adopts the method for conventional mean camber line and thickness distribution to design original blade profile.Wherein, mean camber line given way has single circular arc, two circular arc, many circular arcs, multinomial etc., and thickness distribution has NACA series etc.
Step 2, modeling is also carried out numerical calculation check to model.Concrete grammar is:
Step 2.1, sets up Three-dimension Numerical Model to the original blade profile of step 1 design, and rectangular slits is offered in the trailing edge center of arc position in selected model cross section, then along blade exhibition, to each position, offers identical rectangular slits, forms jet seam.
Described rectangular slits wide vertical with blade profile mean camber line, the wide mid point of rectangle is positioned at the center of arc place of trailing edge, and the long limit of rectangle is parallel with the mean camber line at trailing edge place, blade profile cross section.The Extreme breadth of rectangle is half of radius of arc, and long limit extends to the external boundary of trailing edge.
Step 2.2, in blade interior, selected n location point is as the location point of intending adding spoiler arbitrarily, and the location point of intending interpolation spoiler is positioned at jet seam outlet port and extends to being uniformly distributed.The spoiler number that wherein value of n is added by design is determined.
Step 2.3, n the location point of intending interpolation spoiler that step 2.2 is selected is divided into s group (2 < s < 100 successively, during first simulation, s is any value), it is identical that each group except last group comprises location point number.
By setting the method for the effluxvelocity size that the corresponding trailing edge of every group of location point cracks, reach the effect of simulation spoiler coutroi velocity, concrete grammar is: set the effluxvelocity that in every group of location point, the corresponding trailing edge of each point cracks and vary in size, and respectively organize effluxvelocity that corresponding trailing edge cracks by period profile, thereby form s the waveform that wavelength is identical.The corresponding wave period of one group of location point, along exhibition to effluxvelocity and the wavelength effect that forms lobe nozzle external form (being that trailing edge jet presents period profile).
Step 2.4, each effluxvelocity of intending interpolation spoiler location point that regulating step 2.3 is set is big or small, thereby changes the wave amplitude size of waveform, controls the waveform shape in a wavelength, makes waveform top speed V
maxwith the mixed mean velocity of air-flow
there is following provisions scope,
Step 2.5, the import of fixed model, exit condition, each that set in grouping and the step 2.4 of step 2.3 intended adding in the effluxvelocity situation of spoiler location point, calculate turbine pneumatic results of property, and the turbine pneumatic results of property turbine outlet pitot loss condition given with designing requirement compared, if result meets pitot loss condition, step 2.3 selected n is intended adding the location point of spoiler and grouping situation thereof and corresponding wave amplitude size as the final shaping trailing edge jet scheme.If result is discontented with sufficient pitot loss condition, change the quantity (being about to n location point divides into groups again) of waveform and the effluxvelocity of setting, re-execute step 2.3 to step 2.5, until turbine pneumatic results of property result meets pitot loss condition.
Because along exhibition to the waveform quantity forming
the wavelength that wherein λ is each waveform, h is that leaf is high, i.e. the extreme length of wavelength, so waveform quantity and wavelength are inversely proportional to.
Different wavelength corresponding to grouping, the corresponding different wave amplitudes of different effluxvelocities.
Step 3, the final shaping trailing edge jet scheme obtaining according to step 2, adds spoiler and controls each spoiler aperture size (being spoiler and the area that overlaps cracking), is processed into actual blade.
The effluxvelocity that the jet seam corresponding to spoiler of different opening size exports effluent stream is different; When spoiler surface is parallel with the broadside that cracks, there is no air-flow outflow from crack; When spoiler surface is vertical with the broadside that cracks, airspeed is maximum value.
The turbine blade tail that step 1 of the present invention to the method described in step 3 is applicable to fan and the gas compressor jet-stream wind design of cracking.
Beneficial effect
The present invention starts with from pneumatic means, adopts the direct waveform of trailing edge to spray to realize the mechanism of the effect of 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 of downstream turbine blade inlet air flow uniformity of temperature profile.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, is (b) 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 (being maximum effluxvelocity), and λ is wavelength;
Fig. 4 is the trailing edge jet parameters figure in embodiment;
Fig. 5 is embodiment's Numerical Simulation Results, and the quantity of waveform is 5.Wherein (a) is Uniform jet simulation result, (b) for having the simulation result of wavy jet.
Embodiment
For objects and advantages of the present invention are described better, below in conjunction with drawings and Examples, content of the present invention is described further.
This example redesigns an axial flow turbine vane foil according to method described in summary of the invention, and verifies its action effect by numerical method.The relevant aerodynamic parameter of the present embodiment is as follows: import stagnation pressure 111325Pa, outlet static pressure 90000Pa.Designing requirement pitot loss can not be lower than 90%, therefore proposal plan requires to form 5 waveforms, periodicity is 5 cycles, at least needs 5 groups of spoilers, and every 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.In this example, select Goldman turbine vane type.
Step 2, modeling is also carried out numerical calculation check to model.Concrete grammar is:
Step 2.1, sets up Three-dimension Numerical Model to the original blade profile of step 1 design, 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 half of this blade profile trailing edge radius of arc, and long limit extends to the external boundary of trailing edge.Then along blade exhibition, to each position, offer identical rectangular slits, form jet seam.Described rectangular slits wide vertical with blade profile mean camber line, the wide mid point of rectangle is positioned at the center of arc place 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 the location point of intending adding spoiler arbitrarily, and the location point that plan is added spoiler is positioned at jet seam outlet port and extends to being uniformly distributed.
Step 2.3,50 location points of intending interpolation spoiler that step 2.2 is selected are divided into 5 groups successively, have 10 location points of intending adding spoilers in each group.
By setting the method for the effluxvelocity size that the corresponding trailing edge of every group of location point cracks, reach the effect of simulation spoiler coutroi velocity, concrete grammar is: set the effluxvelocity that in every group of location point, the corresponding trailing edge of each point cracks and vary in size, and respectively organize effluxvelocity that corresponding trailing edge cracks by period profile, thereby form 5 waveforms that wavelength is identical.The corresponding wave period of one group of location point, along exhibition to effluxvelocity and the wavelength effect that forms lobe nozzle external form (being that trailing edge jet presents period profile).
Step 2.4, each effluxvelocity of intending interpolation spoiler location point that regulating step 2.3 is set is big or small, thereby changes the wave amplitude size of waveform, controls the waveform shape in a wavelength, makes waveform top speed V
maxwith the mixed mean velocity of 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 of 10 points of the location point of each group plan interpolation 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.Each that set in grouping and the step 2.4 of step 2.3 intended adding in the effluxvelocity situation of spoiler location point, calculates turbine pneumatic results of property, and the turbine pneumatic results of property turbine outlet pitot loss condition given with designing requirement compared.Result meets pitot loss condition, so selected 50 of step 2.3 are intended adding the location point of spoilers and grouping situation thereof and corresponding wave amplitude size as the final shaping trailing edge jet scheme.
Step 3, the final shaping trailing edge jet scheme obtaining according to step 2, adds spoiler and controls each spoiler aperture size (being spoiler and the area that overlaps cracking), is processed into actual blade.
The present embodiment is carried out to three-dimensional CFD numerical simulation result as shown in Figure 5, therefrom can obtain, trailing edge jet velocity is opened up after uneven distribution, can reduce blade exit air-flow ricing, reduces outlet pitot loss.Numerical simulation result shows that disturbance that the jet wavy distribution of trailing edge causes can play the ricing that reduces downstream blade entrance and the effect that reduces outlet pitot loss.
Above-described specific descriptions; object, technological scheme and beneficial effect to invention further describe; institute is understood that; the foregoing is only specific embodiment of the invention case; be used for explaining the present invention, the protection domain being not intended to limit the present invention, within the spirit and principles in the present invention all; any modification of making, be equal to replacement, improvement etc., within protection scope of the present invention all should be included in.
Claims (5)
1. a waveform jetting method for blade trailing edge, is characterized in that: comprise the steps:
Step 1, adopts the method for conventional mean camber line and thickness distribution to design original blade profile;
Step 2, modeling is also carried out numerical calculation check to model; Concrete grammar is:
Step 2.1, sets up Three-dimension Numerical Model to the original blade profile of step 1 design, and rectangular slits is offered in the trailing edge center of arc position in selected model cross section, then along blade exhibition, to each position, offers identical rectangular slits, forms jet seam;
Described rectangular slits wide vertical with blade profile mean camber line, the wide mid point of rectangle is positioned at the center of arc place of trailing edge, and the long limit of rectangle is parallel with the mean camber line at trailing edge place, blade profile cross section; The Extreme breadth of rectangle is half of radius of arc, and long limit extends to the external boundary of trailing edge;
Step 2.2, in blade interior, selected n location point is as the location point of intending adding spoiler arbitrarily, and the location point of intending interpolation spoiler is positioned at jet seam outlet port and extends to being uniformly distributed; The spoiler number that wherein value of n is added by design is determined;
Step 2.3, n the location point of intending interpolation spoiler that step 2.2 is selected is divided into s group successively, 2 < s < 100, while simulating for the first time, s is any value, it is identical that each group except last group comprises location point number;
By setting the method for the effluxvelocity size that the corresponding trailing edge of every group of location point cracks, reach the effect of simulation spoiler coutroi velocity, concrete grammar is: set the effluxvelocity that in every group of location point, the corresponding trailing edge of each point cracks and vary in size, and respectively organize effluxvelocity that corresponding trailing edge cracks by period profile, thereby form s the waveform that wavelength is identical; The corresponding wave period of one group of location point, along exhibition to effluxvelocity and the wavelength effect that forms lobe nozzle external form;
Step 2.4, each effluxvelocity of intending interpolation spoiler location point that regulating step 2.3 is set is big or small, changes the wave amplitude size of waveform, controls the waveform shape in a wavelength, makes waveform top speed V
maxwith the mixed mean velocity of air-flow
there is following provisions scope,
Step 2.5, the import of fixed model, exit condition, each that set in grouping and the step 2.4 of step 2.3 intended adding in the effluxvelocity situation of spoiler location point, calculate turbine pneumatic results of property, and the turbine pneumatic results of property turbine outlet pitot loss condition given with designing requirement compared, if result meets pitot loss condition, step 2.3 selected n is intended adding the location point of spoiler and grouping situation thereof and corresponding wave amplitude size as the final shaping trailing edge jet scheme; If result is discontented with sufficient pitot loss condition, change the effluxvelocity that the quantity of waveform is again divided into groups n location point and set, re-execute step 2.3 to step 2.5, until turbine pneumatic results of property result meets pitot loss condition;
Step 3, the final shaping trailing edge jet scheme obtaining according to step 2, adds spoiler and controls each spoiler aperture size, is 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: different wavelength corresponding to grouping, the corresponding different wave amplitudes of different effluxvelocities.
4. the waveform jetting method of a kind of blade trailing edge according to claim 1, is characterized in that: the effluxvelocity that the jet seam corresponding to spoiler of different opening size exports effluent stream is different; When spoiler surface is parallel with the broadside that cracks, there is no air-flow outflow from crack; When spoiler surface is vertical with the broadside that cracks, 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 step 1 to the method described in step 3 is applicable to fan and the gas compressor jet-stream wind design of cracking.
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
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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 |
| CN112651075A (en) * | 2020-10-30 | 2021-04-13 | 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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| 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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Patent Citations (6)
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| US20030231961A1 (en) * | 2001-06-18 | 2003-12-18 | Chandraker A. L. | Cylindrical blades for axial steam turbines |
| 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 |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN112651075A (en) * | 2020-10-30 | 2021-04-13 | 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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