CN104677638A - Blade tip jet test device - Google Patents
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- CN104677638A CN104677638A CN201310608066.4A CN201310608066A CN104677638A CN 104677638 A CN104677638 A CN 104677638A CN 201310608066 A CN201310608066 A CN 201310608066A CN 104677638 A CN104677638 A CN 104677638A
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Abstract
A blade tip jet test device comprises a subsonic turbine cascade wind tunnel. The wind tunnel comprises a fan, a pressure stabilizing barrel, a honeycomb, convergence devices, an inlet section, a movable side plate, a test cascade, and a rotatable semi disk. The cascade is composed of blades. The device further comprises a sheet used for making blade tips, and blade tip jet holes which are distributed in the range of chord length at a distance from the front edge of the blades and are adjustable. In the thickness direction of the blades, the tangential jet angle, flow-direction jet angle and jet flow of the jet holes can be adjusted. Static pressure holes are distributed on the surfaces of the test blades. Test points are distributed on the section of the exit of the cascade. An optimal jet scheme is obtained in the invention, the performance of the scheme in the range of attack angle of an actual blade is verified, and whether the blade tip jet scheme has industrial practical popularization value can be well verified.
Description
Technical field
The present invention relates to marine gas turbine performances areas, particularly a kind ofly reduce gas turbine internal clearance flow losses by Active Control Method thus improve the test unit of gas turbine proficiency and overall output power.
Background technology
Gas turbine is the core drive equipment on 21 century high-power naval vessel, and its development level can embody the advanced degree of a national shipping industry, therefore needs to greatly develop it.Runner internal flow loss is then one of principal element of restriction gas turbine proficiency, and therefore numerous research institution it can be used as their subject study center of gravity.
Clearance Flow loss is one of important component part of movable vane internal flow loss.In high-pressure turbine, movable vane 45% flow losses, in turbine stage, 30% flow losses are all caused by Clearance Flow.Research proves, Clearance Flow makes leaf top heat transfer coefficient rise about 200%.
Because Clearance Flow has larger impact to turbine performance, therefore must take measures to weaken Clearance Flow.Wherein a kind of method effectively weakening Clearance Flow is exactly leaf top spray gas.Pougare has carried out preliminary simple research to leaf top spray gas first in 1986.Result of study shows, and leaf top spray gas effectively can weaken the appearance of Clearance Flow and Gap cirele.
Current research is thought, the effect of leaf top spray gas to Clearance Flow is mainly manifested in following three aspects: (1) leaf top spray gas plays blocking action to Clearance Flow, reduces Clearance Flow loss; (2) gap entrance speed in gas orifice downstream reduces, the blending declines of Clearance Flow and main flow; (3) in gap, near gas orifice, entropy increase and decrease is little.
But the domestic leaf top spray pneumatic control research for Clearance Flow still rests on the numerical simulation stage at present, there is no corresponding test unit and studies leaf top spray gas scheme.
Summary of the invention
The present invention aims to provide a kind of feasible leaf top spray gas test unit, by this device to leaf top spray gas scheme to the actual effect research experiment of control gap flow losses, thus can verify whether leaf top spray gas scheme possesses industrial actual promotional value preferably.
In order to realize object, the present invention is realized by following technical scheme, and a kind of leaf top spray gas test unit, comprises subsonic turbine cascade wind tunnel, described wind-tunnel comprises blower fan, tube of pressure-stabilizing, honeycomb, convergence, inducer, mobile side board, test leaf grating and rotating semi-disc; Air-flow enters described tube of pressure-stabilizing after blower fan pressurization, and through honeycomb, air-flow is by homogenizing, straightening; Then through convergence, inducer and mobile side board, enter test leaf grating, and described leaf grating is made up of pilot blade, and described leaf grating block is inlaid on described semi-disc, can regulate the angle of attack of leaf grating entrance when disk rotational; This test unit also comprises the thin slice for making vane tip, and described thin skin is fixed with described pilot blade and overlapped completely with its position; Clearance height is there is between described blade and described semi-disc; This test unit also comprises leaf top spray pore, and it distributes adjustable within the scope of the chord length apart from described blade inlet edge one segment distance; The distribution of described gas orifice on described vane thickness direction is adjustable; The tangential jet angle adjustable of described gas orifice; Described gas orifice flows to jet angle adjustable; Described gas orifice spray air flow is adjustable; Described pilot blade surface distributed has baroport; Described leaf grating outlet is distributed with test point.
Further, this test unit also comprise three hole probes, be arranged at the position of described blade inlet edge one segment distance of being separated by and the position of described blade trailing edge of being separated by, for obtaining the data of the stagnation pressure of air-flow incoming flow, static pressure and orientation angle; Electronic control translation stage, realizes displacement robotization and experimental data pointwise collection; Thermostatic type hot-wire anemometer, for measuring two speed components of air-flow two-dimensional flow; Digital multi-channel pressure scanning valve, for measuring described blade surface static pressure, leaf grating outlet stagnation pressure; Air compressor, for providing the gases at high pressure needed for leaf top spray gas; Mass flowmeter, for measuring leaf top spray airshed.
Further, described pilot blade have employed axial flow gas turbine high-pressure turbine movable vane blade, gets its 50% leaf height cross section blade profile as test blade profile.
The invention has the advantages that, its leaf top spray gas test unit proposed can measure the situation of change of Secondary Flow distribution in leaf top spray gas rear blade passage preferably, and by means of blade surface static pressure changes in distribution, thus study the impact of Clearance Flow by leaf top spray gas easily.Meanwhile, by means of parameter such as adjustment jet position, jet angle, jet amount etc., easily can draw a best jet scheme, and verify the performance of the program in the range of angles of attack of actual blade.By above research, can verify whether leaf top spray gas scheme possesses industrial actual promotional value preferably.
Accompanying drawing explanation
By reading the detailed description done non-limiting example done with reference to the following drawings, other features, objects and advantages of the present invention will become more obvious:
Fig. 1 is turbine plane cascade wind tunnel schematic diagram;
Fig. 2 leaf grating is measured runner and is imported and exported and measures cross-sectional distribution schematic diagram;
Fig. 3 turbo blade blade profile figure;
Fig. 4 leaf top spray gas structural representation;
Fig. 5 turbine blade surface baroport position distribution schematic diagram;
Fig. 6 outlet measuring point distribution schematic diagram;
Fig. 7 part test device pictorial diagram;
Fig. 8 main experimental conceptual scheme;
Under the different angle of attack operating mode of Fig. 9, clearance flow, outlet pitot loss distribution plan;
In Fig. 1,1 is tube of pressure-stabilizing 1, and 2 to be through honeycomb 2,3 and 4 are convergences 3, and 4,5 are inducers, 6 is mobile side boards, and 8 is test leaf gratings, and 7 is semi-discs.
In accompanying drawing, same or analogous Reference numeral represents same or analogous parts.
Embodiment
The present invention is set forth further below in conjunction with accompanying drawing.The preferred embodiment of the present invention is just not used in for helping to set forth the present invention and limits the scope of the invention.The preferred embodiment of the present invention does not have all details of detailed descriptionthe, does not limit the embodiment that this invention is only described yet.Obviously, according to the content of this instructions, can make many modifications and variations.This instructions is chosen and is specifically described these embodiments, is to explain principle of the present invention and practical application better, thus makes art technician can utilize the present invention well.The present invention is only subject to the restriction of claims and four corner and equivalent.After the content of having read the present invention's record, those skilled in the art can make various changes or modifications the present invention, and these equivalence changes and modification fall into the scope of the claims in the present invention equally.
Marine gas turbine flow losses Control experiment of the present invention carries out on subsonic turbine cascade wind tunnel, and its test unit as shown in Figure 1.
Air-flow enters tube of pressure-stabilizing 1 after blower fan pressurization, and after honeycomb 2, the basic homogenizing of air-flow, straightening, then through convergence 3,4, inducer 5, mobile side board 6, enter test leaf grating 8.Leaf grating block is inlaid on rotary semi-disc 7, can regulate the leaf grating entrance angle of attack when disk rotational.Shown in composition graphs 2, test leaf grating 8 is arranged on the rear 730mm position of wind-tunnel outlet, wind-tunnel discharge area 226mm × 125mm.
Test leaf grating 8 has 7 blades, constitute six effective runners, wherein, two blades #3, #4 are designed to hollow-core construction, as main measured zone, by pad, blade #1, #7 ensure that it does not exist blade tip clearance in leaf grating both sides, but and between side plate, have the slit of 1 ~ 2mm, mainly in order to weaken the boundary layer thickness of side plate accumulation, ensure the homogeneity of inlet flow field.
In order to ensure that leaf grating inlet flow field is uniformly distributed along pitch direction, arranging three hole probes in distance blade inlet edge 90mm position (Z/Cax=-1.5), realizing the even of leading edge air-flow by adjusting vane trailing edge side plate.Blade trailing edge outlet total pressure loss coefficient and flow angle distribution mainly draw in distance blade trailing edge 9mm cross section (Z/Cax=1.15) measurement.Outlet measurement utilizes two three hole probes to measure two adjacent runners simultaneously, to ensure the accuracy of measuring.
In order to warranty test conclusion has general applicability, this test unit Leaf have employed the axial flow gas turbine high-pressure turbine movable vane blade of typical high load capacity, low aspect ratio, for in " LISA " 1.5 grades of axial flow turbines of Zurich engineering college of Swiss Confederation, movable vane blade is prototype, get its 50% leaf height cross section blade profile as test blade profile, as Fig. 3.
The setting of leaf top spray gas scheme considers workability and the realizability in actual industrial, can not be too complicated, to such an extent as to significantly increases the cost of commercial Application.
Be hollow blade by #3, #4 blade design being positioned at runner central authorities in leaf grating, so that air goes out from leaf top spray.The depressed structure of leaf top spray as shown in Figure 4.
Spray air to be provided by extraneous air compressor, go out from leaf top spray after entering blade cavity.The thick about 2mm of vane tip thin slice, is fixed by counterbore screw and blade, and has three register pins to ensure to overlap completely with leaf position.Screw is concordant with leaf top with register pin height, ensures that impeller clearance height is identical on chord length direction.
Blade is fixed on chassis overhang by bottom bolts hole, and clearance height by adding pad to realize between blade and base plate.Pad molded line is identical with vane foil, and ensures that its position and leaf position fit like a glove by register pin.Spacer thickness is 1mm, and therefore clearance height change difference is 1mm.
Leaf top spray hole diameter is 1mm, and by being equidistantly evenly distributed within the scope of distance blade inlet edge 18 ~ 72% chord length, the spacing between the adjacent holes heart is about 4.6mm.Angle between gas orifice center line and leaf top surface is 45o, and the thickness of leaf top thin slice is 2mm, and therefore gas orifice length is about 2.83mm.Gas orifice is flowing to the distribution on direction, gas orifice center line in the projection of Ye Dingshang perpendicular to leaf pressure on top surface limit.Between gas orifice and leaf pressure on top surface limit, line space design is 3mm, substantially occurs that position is corresponding with leaf top separated vorticcs.
In order to the impact of measurement clearance flowing on blade surface static pressure, arranging two rows, 32 diameters at 50%, 97.5% leaf high altitude is respectively the baroport of 0.7mm, and wherein pressure face arranges 12 baroports, suction surface 20 baroports.
In Fig. 5, stain is blade surface static pressure pore size distribution position.
On leaf grating outlet, measuring point distribution as shown in Figure 6.
Along on leaf height direction, within the scope of 47% ~ 98% leaf height, a line measuring point is set every 2.5mm, totally 26 row.On pitch of cascade direction, measuring distance comprises 1.5 times of pitch of cascades altogether, arranges a row measuring point every 2.5mm, totally 33 row.Therefore measuring point leaf grating outlet distributed has 26 × 33=858.
Test is measured and is adopted instrument mainly to comprise:
1) three tubular three hole probes.
By three hole probes, obtain the data of the stagnation pressure of incoming flow, static pressure and orientation angle, its front face area is less than cylindrical three hole probes, smaller to the blocking of gas channel.
In order to reduce the impact of three hole probes on flow field after leaf grating trailing edge, we devise three hole probes of off-standard size, and distance probes bar portion, measuring position 90mm, as Fig. 7 (a).
2) electronic control translation stage
In the present invention, frame of axes adopts TSA400-B precise heavy-load type electronic control translation stage, as Fig. 7 (b).This electronic control translation stage, by driving stepper motor, realizes adjustment of displacement robotization.Stroke is 400mm, and minimum resolution is 0.003125mm, and maximal rate can reach 40mm/s.
Frame of axes control system adopts SC300 series displacement platform control box, can be implemented in the free movement on X, Y, Z three-dimensional.Because high precision displacement controls the employing of frame of axes automatically, make the data pointwise collection in experimentation seem very efficient and convenient, and can enough precision be ensured.
3) thermostatic type hot-wire anemometer
Produced by DANTEC company of Denmark, hot line probe adopts 55P62 type bidimensional hot line, as Fig. 7 (c).Fast instrument rinsed by constant temperature hot line, and to have thermal inertia little, the features such as frequency response is wide.At present its frequency response oneself more than 500 KHz, meet the needs of the various radio-frequency components occurred in turbulent flow completely.
X-type hot line is mainly used to two speed components measuring two-dimensional flow.According to the method for effective velocity in the present invention, be less than when 25 ° at yaw angle, uncertainty of measurement is no more than 3%, and when yaw angle is 35 ° time, uncertainty of measurement is about 5%.
4) digital multi-channel pressure scanning valve
The collection of blade surface static pressure, the total pressure measurement of leaf grating outlet is all adopt digital multi-channel pressure scanning valve (DSA3017), as Fig. 7 (d).Each module of DSA3017 pressure scanning valve has 16 passages, and can carry out 8 tunnel difference measurements or 16 tunnel absolute pressures measurements, single pass sampling rate is 45Hz simultaneously.
The static pressure measurement precision of DSA3017 module is ± 2.5Pa, is ± 2.5Pa/(0.5 × 1.293 × 27 × 27) Pa=± 0.53% with the ratio freely carrying out flow head.
5) air compressor
Needed for leaf top spray gas, gases at high pressure are provided by extraneous air compressor.This compressor can operate continuously, discharge pressure 0.86MPa, and air capacity is 0.45m3/min, fully can meet the needs of leaf top spray gas.
6) mass flowmeter
Leaf top spray airshed by D07-60A mass flow meter measurement, and with Flow Measurement Display Meter with the use of.It has the features such as precision is high, reproducible, fast response time, soft start, reliable and stable, working pressure range is wide.It is simple to operate, and can be connected with computing machine to realize automatic control.
This flow measurement weight range is 500 liters/min, measuring error ± 2%.
In the present invention, the performance of different leaf top spray gas scheme is studied, as shown in Figure 8.
1) along position jet on chord length direction on the impact of Clearance Flow
Leaf top spray pore has 10, and bore dia is 1mm, and by being equidistantly evenly distributed within the scope of distance blade inlet edge 18 ~ 72% chord length, the spacing between the adjacent holes heart is about 4.6mm.Angle between gas orifice center line and leaf top surface is 45o, and the thickness of leaf top thin slice is 2mm, and therefore gas orifice length is about 2.83mm.
Gas orifice is flowing to the distribution on direction, gas orifice center line in the projection of Ye Dingshang perpendicular to leaf pressure on top surface limit.
In order to study the impact that gas orifice controls along the jet position distribution of chord length Clearance Flow, the present invention have studied Clearance Flow situation under three kinds of jet operating modes in different chord lengths position, and gas orifice position distribution is as Fig. 8 (a).
Each jet structural parameters are in table 1.Operating mode A carries out leaf top spray gas by whole 10 holes, and spray air flow accounts for 1.11% main flow flow.Operating mode B, C then only have employed 7 gas orifices and carry out jet, and wherein in operating mode B, gas orifice is positioned at blade middle front part (#1 ~ #7), and operating mode C gas orifice is positioned at blade postmedian (#4 ~ #10).Substantially identical for ensureing the distribution of each gas orifice medium velocity, the jet amount of operating mode B, C is (7/10) * 1.11% ≈ 0.78%.
2) along position jet on vane thickness direction on the impact of Clearance Flow
In order to study the layout of gas orifice on vane thickness direction to the impact of Clearance Flow control effects, blade mean camber line arranges 10 gas orifices equally.Gas orifice and leaf top angle are still 45o, and the spacing between hole keeps 4.6mm constant.Gas orifice flowing to still perpendicular to leaf pressure on top surface limit on direction, as Fig. 8 (b).
3) tangential jet angle is on the impact of Clearance Flow
In order to study the tangential jet angular distribution of leaf top spray gas to the effect of Clearance Flow, measuring the jet control effects to Clearance Flow under three tangential angles of difference by test, being respectively 45o, 60o, 90o.
The definition of jet tangential angle is as shown in Fig. 8 (c).
4) impact of jet angle on Clearance Flow is flowed to
For research gas orifice is flowing to impact direction distributing and controls Clearance Flow, keeping other optimum configurations constant, be only vertical with axis by gas orifice angular setting, and being no longer perpendicular to blade pressure limit, as shown in Fig. 8 (d).
5) jet scheme performance comparison
Contrast each jet scheme above, outgoing quality average total pressure coefficient, clearance flow result are as shown in table 2.
Can find out, after adopting leaf top spray gas scheme, because it is to the inhibition of Clearance Flow, make to be declined to a great extent by the flow in gap.When wherein the maximum range of decrease is for employing jet operating mode A, reach 78.25%, the operating mode E range of decrease is taken second place, and is 77.82%, and gas orifice is minimum perpendicular to Ye Dingshi (operating mode F) effect to clearance flow, is 38.11%.
Leaf top spray gas is substantially identical with clearance flow on the improve quality impact of average total pressure coefficient of leaf grating outlet.When adopting operating mode A, on outlet, stagnation pressure coefficient is minimum, adopts during operating mode E and takes second place, maximum when adopting operating mode F, is even greater than original outlet stagnation pressure coefficient when not adopting leaf top spray gas.
Therefore, when arranging leaf top spray pore, should try one's best near blade postmedian position, because this region is the main forming position of Clearance Flow, the gas orifice being positioned at postmedian can flow by more effective control gap; On vane thickness direction, as far as possible near blade pressure limit, more control effects can be obtained; About tangential jet angular arrangement, adopt during 45o and 60o and the impact of clearance flow and stagnation pressure coefficient is more or less the same, illustrate that the impact of tangential jet angle within the scope of 45 ~ 60o is substantially identical.But consider actual processing, tangential jet angle can adopt 60o; As for flowing to jet angle, when gas orifice is perpendicular to leaf pressure on top surface limit, due to just in time contrary with Clearance Flow direction, therefore better control effects can be obtained.
The jet direction of the optimum drawn under operating condition of test of the present invention is operating mode E: gas orifice near pressure edge injection, jet amount be 1.11% main flow flow, gas orifice divides within the scope of 18 ~ 72% chord lengths perpendicular to leaf pressure on top surface limit, gas orifice, adopts the tangential jet angle of 60o.
Under gas turbine often operates in variable working condition condition, be therefore necessary that performance when there is the angle of attack to the movable vane import under off-design behaviour of leaf top spray gas scheme is studied.The present invention mainly have studied five inlet incidence angles, is the analysis of the jet effect under-15o ,-8.5o, 0o (design conditions), 8.5o and 12o respectively.The jet scheme of optimum drawn before its middle period top spray gas scheme adopts: operating mode E.
Under the leaf top spray gas design angle of attack, clearance flow is minimum, and under non-design inlet incidence angle condition, leaf top spray gas still can control gap flow preferably, and clearance flow distributes and is substantially symmetrically distributed.Under non-design angle of attack operating mode, leaf top spray gas also can reduce outlet pitot loss preferably, as shown in Figure 9.Wherein, when the negative angle of attack (i=-8.5o), the best results of leaf top spray gas.
Table 1 leaf top spray gas structural parameters;
The different jet scheme of table 2 is on the impact of clearance flow, stagnation pressure coefficient;
| Jet operating mode | Jet amount/main flow (%) | Gas orifice quantity | Tangential angle | Flow to angle | Leaf grating outlet stagnation pressure coefficient | Clearance flow/main flow (%) |
| Original operating mode | 0 | 0 | 0 | 0 | 0.3501 | 4.792 |
| Operating mode A | 1.11 | 10 | 45 | PS | 0.2745 | 1.042 |
| Operating mode B | 0.78 | 7，F | 45 | PS | 0.3056 | 2.315 |
| Operating mode C | 0.78 | 7，B | 45 | PS | 0.2934 | 1.805 |
| Operating mode D | 1.11 | 10，C | 45 | PS | 0.2985 | 1.867 |
| Operating mode E | 1.11 | 10 | 60 | PS | 0.2781 | 1.063 |
| Operating mode F | 1.11 | 10 | 90 | PS | 0.3744 | 2.966 |
| Operating mode G | 1.11 | 10 | 45 | Z | 0.3191 | 1.823 |
Therefore can prove that leaf top spray gas scheme has good applicability, be one of measure of good control gap flow losses.
Claims (10)
1. a leaf top spray gas test unit, it is characterized in that comprising subsonic turbine cascade wind tunnel, described wind-tunnel comprises blower fan, tube of pressure-stabilizing, honeycomb, convergence, inducer, mobile side board, test leaf grating and rotating semi-disc; Air-flow enters described tube of pressure-stabilizing after blower fan pressurization, and through honeycomb, air-flow is by homogenizing, straightening; Then through convergence, inducer and mobile side board, enter test leaf grating, and described leaf grating is made up of pilot blade, and described leaf grating block is inlaid on described semi-disc, can regulate the angle of attack of leaf grating entrance when disk rotational; This test unit also comprises the thin slice for making vane tip, and described thin skin is fixed with described pilot blade and overlapped completely with its position; Clearance height is there is between described blade and described semi-disc; This test unit also comprises leaf top spray pore, and it distributes adjustable within the scope of the chord length apart from described blade inlet edge one segment distance; The distribution of described gas orifice on described vane thickness direction is adjustable; The tangential jet angle adjustable of described gas orifice; Described gas orifice flows to jet angle adjustable; Described gas orifice spray air flow is adjustable; Described pilot blade surface distributed has baroport; Described leaf grating outlet is distributed with test point.
2. test unit according to claim 1, what it is characterized in that this test unit also comprises three hole probes, be arranged at the position of described blade inlet edge one segment distance of being separated by and the position of described blade trailing edge of being separated by, for obtaining the data of the stagnation pressure of air-flow incoming flow, static pressure and orientation angle; Electronic control translation stage, realizes displacement robotization and experimental data pointwise collection; Thermostatic type hot-wire anemometer, for measuring two speed components of air-flow two-dimensional flow; Digital multi-channel pressure scanning valve, for measuring described blade surface static pressure, leaf grating outlet stagnation pressure; Air compressor, for providing the gases at high pressure needed for leaf top spray gas; Mass flowmeter, for measuring leaf top spray airshed.
3. test unit according to claim 1, is characterized in that described pilot blade have employed axial flow gas turbine high-pressure turbine movable vane blade, gets its 50% leaf height cross section blade profile as test blade profile.
4. test unit according to claim 1, is characterized in that described leaf grating is arranged on the rear 730mm position of wind-tunnel outlet, wind-tunnel discharge area 226mm × 125mm.
5. test unit according to claim 1, it is characterized in that described leaf grating has 7 blades, constitute six effective runners, wherein third and fourth piece of blade design is hollow-core construction, as main measured zone, first and the 7th piece of blade ensure that it does not exist blade tip clearance by pad, but and between described side plate, have the slit of 1 ~ 2mm.
6. test unit according to claim 2, is characterized in that arranging three hole probes respectively in distance blade inlet edge 90mm position with in distance blade trailing edge 9mm position.
7. test unit according to claim 1, it is characterized in that described is 2mm for making the sheet thickness of vane tip, fixed by counterbore screw and blade, and having three register pins to ensure to overlap completely with leaf position, described screw is concordant with the leaf top after making with the height of described register pin.
8. test unit according to claim 1, it is characterized in that described blade is fixed on semi-disc by bottom bolts hole, described clearance height by adding pad to realize between blade and semi-disc, described pad molded line is identical with described vane foil, and ensureing that its position and leaf position fit like a glove by register pin, spacer thickness is 1mm.
9. test unit according to claim 1, it is characterized in that described leaf top spray hole diameter is 1mm, length is 2.83mm, and by being equidistantly evenly distributed within the scope of distance blade inlet edge 18 ~ 72% chord length, the spacing between the adjacent holes heart is 4.6mm.
10. test unit according to claim 1, it is characterized in that respectively 50% and 97.5% leaf high altitude arrange two row amount to 32 diameters be the baroport of 0.7mm, wherein pressure face arranges 12 baroports, suction surface 20 baroports; Along on leaf height direction, within the scope of 47% ~ 98% leaf height, a line measuring point is set every 2.5mm, totally 26 row.
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