CN110030038A - Consider the asymmetric stator design method of blade tip transonic fan of BLI inlet distortion effect - Google Patents
Consider the asymmetric stator design method of blade tip transonic fan of BLI inlet distortion effect Download PDFInfo
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- CN110030038A CN110030038A CN201910201619.1A CN201910201619A CN110030038A CN 110030038 A CN110030038 A CN 110030038A CN 201910201619 A CN201910201619 A CN 201910201619A CN 110030038 A CN110030038 A CN 110030038A
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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
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
- F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
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- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
This application discloses a kind of asymmetric stator design methods of blade tip transonic fan for considering BLI inlet distortion effect, comprising the following steps: Step 1: stator blade to be circumferentially divided into distorted region and non-distorted region according to the fan stator import incoming flow situation of prototype under the conditions of BLI inlet distortion；Step 2: remodeling is optimized to the stator blade for being divided into distorted region, meanwhile, the stator blade for being divided into non-distorted region keeps prototype；Step 3: combining the prototype blade of the remodeling stator blade of distorted region and non-distorted region, complete cycle is obtained to asymmetric stator blade.
Description
Technical field
The application belongs to compressor fan stator design field, and in particular, to a kind of consideration boundary layer suction
The asymmetric stator design method of (Boundary Layer Ingestion, abbreviation BLI) blade tip transonic fan.
Background technique
Fly the trend that hair integrated configuration is next-generation Civil Aviation Flight device design.With pushing away for boundary layer suction effect
Into system layout, it is laid out compared to conventional power system, theoretically can reduce 5%~10% aircraft oil consumption rate, it is each
Big aeronautical research mechanism is good.Using the aircraft of BLI propulsion system, by the boundary layer suction of a part of low speeds flow of fuselage
Enter dynamical system, reduce exhaust velocity, propulsive efficiency is promoted, to reduce the complete machine oil consumption rate of aircraft.
However BLI propulsion system also designs for engine and brings new challenge, since fan needs are continued working abnormal
Become air inlet to flow down, this makes fan pneumatic efficiency reduce by 1%~2%.Therefore, the high-performance wind under the conditions of BLI inlet distortion
Fan is designed to for an important research topic instantly.
BLI inlet distortion causes fan internal flow to show circumferential asymmetry, and total pressure distortion is after by rotor
It is developed, blade tip distortion intensity increases, and distortion expands along the circumferential extension of generation, circumferential coverage is turned to, rotor outlet
(i.e. stator import) flow field shows asymmetry, and the stator flow angle of distorted region significantly deviates design value.The angle of attack is bigger than normal
Cause stator blade profile suction surface flow separation occur, generates biggish flow losses, fan efficiency is caused to decline.Therefore, traditional
According to uniform air inlet design fan stator be difficult to meet work requirements under the conditions of inlet distortion.
Based on the fan stator optimization design research in the asymmetric flow field of inlet distortion condition, external research team is carried out
A few thing is crossed, attempts the asymmetric design of progress stator to reduce the flow losses of stator in asymmetric flow field.
1996, Rolls-Royce aero-engine company (Rolls-Royce company) was led by Asymmetrical Optimization fan outlet
Leaf, adjust local blade chord length and established angle has to slow down influence of the asymmetric casing load-carrying construction in guide vane downstream for guide vane
Effect the separation of guide vane angular region is inhibited to flow.However, stator flow asymmetry caused by the casing load-carrying construction of downstream no matter
All it is significantly less than stator flow asymmetry caused by BLI effect inlet distortion from scale or amplitude.
2017, Cambridge-Massachusetts science and engineering research team Gunn and Hall reduced BLI effect using the design of asymmetric stator
The flow losses of certain low rotary speed fan under inlet distortion.Asymmetric remodeling has been carried out to the primitive blade profile of stator first, has adjusted leaf
Then piece metal angle and chord length have carried out the remodeling of asymmetry to stator blade.The result shows that: two dimension is carried out to fan stator
Asymmetric retrofit can reduce the flow losses of blade tip high-load region；Carry out the asymmetry remodeling of three dimendional blade, Ke Yijin
One step reduces the separation loss of stator blade root.But the work of Gunn and Hall be carried out based on a low rotary speed fan, and
Civil aircraft fan is usually big bypass ratio, high revolving speed and blade tip Supersonic, and whether asymmetric stator optimization design is suitable for
Verifying is not yet received in high-loaded fan stator.
Summary of the invention
For the above-mentioned problems in the prior art, present applicant proposes a kind of leaves for considering BLI inlet distortion effect
The sharp asymmetric stator design method of transonic fan, comprising the following steps:
Step 1: according to prototype under the conditions of BLI inlet distortion (not considering design when BLI inlet distortion effect)
Fan stator import incoming flow situation stator blade is circumferentially divided into distorted region and non-distorted region；
Step 2: remodeling is optimized to the stator blade for being divided into distorted region, meanwhile, it is divided into non-distorted region
Stator blade keeps prototype；
Step 3: combining the prototype blade of the remodeling stator blade of distorted region and non-distorted region, obtain complete
Circumferential asymmetric stator blade.
In the embodiment of the application, the step 1 includes according to prototype under the conditions of BLI inlet distortion
The angle of attack of fan stator and the deviation situation of design value divide distorted region and non-distorted region.
In the embodiment of the application, the step 2 includes keeping its right by amendment stator import metal angle
Quasi- direction of flow optimizes remodeling to the stator blade for being divided into distorted region, to reduce the stator angle of attack.
Preferably, stator import metal angle is corrected by way of camber line in modification stator botanical origin blade profile.
Preferably, stator blade profile is defined by the way of camber line and thickness distribution in.
In the embodiment of the application, parametrization fitting is carried out to stator blade profile, with to being divided into distorted region
Stator blade optimize remodeling.
In the preferred embodiment of the application, using 8 rank Bezier curves to stator blade product superimposing thread and middle arc
Line carries out parametrization fitting.
In the embodiment of the application, guarantee that blade axial direction chord length is constant, the x at the control point of Bezier curve is sat
Mark immobilizes, and in retrofitting process, the y-coordinate by modifying control point makes vane inlet metal angle be revised as target value, and
And to guarantee that outlet metal angle is constant, the y-coordinate at the 8th, 9 control point is constant, and the interlude control point of Bezier curve changes
The y-coordinate difference linear change of type and prototype to 0, thus in obtaining camber line Bezier curve control point.
Preferably, blade optimization Transform Type design is carried out with the Autoblade software in NUMECA software package.
In the preferred embodiment of the application, the step 2 includes: p- 150 ° to -60 ° of circumferential zones drop
The angle of attack of low blade tip, p- 60 ° to -30 ° of circumferential zones reduce the angle of attack of 50% leaf height or more, p- 30 ° to 30 ° of circumferential area
Domain reduces the high angle of attack of full leaf, keeps prototype to 30 ° Dao -150 ° of circumferential zones.
As it can be seen that the stator blade for being divided into distorted region under the conditions of BLI inlet distortion is optimized remodeling by the application
And the stator blade for keeping the non-distorted region of prototype is combined to form complete cycle to asymmetric stator blade, it is negative to have adjusted stator
Lotus spatial distribution reduces stator circumferential direction regional area high load capacity, has obtained asymmetric stator optimization design.In blade tip transonic fan
It is middle to be designed with asymmetric stator, delay the flow separation of distorted region stator blade profile suction surface, it is logical to reduce stator leaf grating
Flow losses in road alleviate the asymmetry of fan internal flow, and fan stage efficiency is effectively promoted.
Detailed description of the invention
Attached drawing shows the illustrative embodiments of the application, and it is bright together for explaining the principle of the application,
Which includes these attached drawings to provide further understanding of the present application, and attached drawing is included in the description and constitutes this
Part of specification.
Fig. 1 shows different leaf eminence stator angle of attack distributions (90%, 50%, 10% leaf is high)；
Fig. 2 shows different leaf eminence stator metal angles (remodeling metal angle-prototype metal angle) distribution (90%, 70%,
50%, 30%, 10% leaf is high)；
Fig. 3 is the asymmetric stator structure schematic diagram of the application (90% leaf is high)；
Fig. 4 shows stator outlet entropy comparison diagram (90% leaf is high)；
Fig. 5 shows stator outlet entropy comparison diagram (50% leaf is high)；
Fig. 6 shows stator outlet entropy comparison diagram (10% leaf is high)；
Fig. 7 shows the stator S1 stream interface VELOCITY DISTRIBUTION of prototype and Transform Type design under different leaf height and circumferential angle and compares
Figure.
Specific embodiment
The application is described in further detail with embodiment with reference to the accompanying drawing.It is understood that this place
The specific embodiment of description is only used for explaining related content, rather than the restriction to the application.It also should be noted that being
Convenient for description, part relevant to the application is illustrated only in attached drawing.
It should be noted that in the absence of conflict, the feature in embodiment and embodiment in the application can
To be combined with each other.The application is described in detail below with reference to the accompanying drawings and in conjunction with embodiment.
This sentences the considerations of illustrating the application for high load capacity transonic fan grade NASA Stage67 fan stator BLI air inlet
The asymmetric stator design method of the blade tip transonic fan of distortion effect:
Firstly, according to the fan stator import incoming flow situation of prototype under the conditions of BLI inlet distortion by stator blade edge
Circumferentially it is divided into distorted region and non-distorted region.
In one embodiment of the application, according to the angle of attack of the fan stator of prototype under the conditions of BLI inlet distortion
Distorted region and non-distorted region are divided with the deviation situation of design value.Stage67 prototype fan is preferably based in BLI
Complete cycle unsteady numerical simulations result under the conditions of effect inlet distortion, it can be deduced that under the conditions of inlet distortion the angle of attack of stator with
The deviation situation of design value, it was found from the result of Fig. 1: -150 ° to 30 ° region blade tip angles of attack of circumferential position are bigger than normal；- 60 ° to 60 °
The angle of attack is bigger than normal in the leaf of region；- 30 ° to the 60 ° region blade root angles of attack are bigger than normal；Non- distorted region (30 ° of circumferential position Dao -150 °) it is quiet
The sub- angle of attack and prototype deviate little.
Secondly, remodeling is optimized to the stator blade for being divided into distorted region, meanwhile, it is divided into the quiet of non-distorted region
Blades keep prototype.
In the present embodiment, during carrying out Asymmetrical Optimization Design to stator, stator is divided into following three regions,
Be modified as follows to the stator angle of attack: -150 ° to -60 ° regions reduce the blade tip angle of attack, and -60 ° to -30 ° regions reduce
The high above angle of attack of 50% leaf, -30 ° to 30 ° regions reduce full leaf high angles of attack, and non-distorted region (30 ° of circumferential position Dao -150 °) is quiet
Son keeps prototype.Asymmetric stator import metal angle is as shown in Figure 2 along the high distribution of different leaves after optimization design.
It is then possible to make it be directed at direction of flow come to being divided into distorted region by amendment stator import metal angle
Stator blade optimizes remodeling, to reduce the stator angle of attack.
Preferably, in the present embodiment, stator import is corrected by way of camber line in modification stator botanical origin blade profile
Metal angle, to achieve the purpose that reduce the stator angle of attack.The following formula of the corresponding relationship of stator import metal angle and the angle of attack:
χ′in=xin+(itarget-iBLI)=χin+(αtarget-αBLI)
Wherein χin' for remodeling after stator import metal angle, χinFor the stator import metal angle of prototype, itargetFor
The target angle of attack, iBLIFor the angle of attack under the conditions of BLI inlet distortion, αtargetFor target blade geometry flow inlet angle, αBLIFor BLI distortion
Blade geometry flow inlet angle under inlet air conditions.
In the present embodiment, in order to correcting stator import metal by way of camber line in modification stator botanical origin blade profile
Angle defines stator blade profile by the way of camber line and thickness distribution in.
Preferably, parametrization fitting is carried out to stator blade profile, to optimize to the stator blade for being divided into distorted region
Remodeling.
In the present embodiment, stator geometry is extended to being divided into 11 with Autoblade software in NUMECA software package
Leaf section defines blade profile by the way of camber line and thickness distribution in, and blade is folded along center of gravity product, blade stacking line and middle camber line
Parametrization fitting is carried out using 8 rank Bezier curves simultaneously, carries out import metal angle to obtain camber line Bezier curve in blade
Remodeling, while keeping other leaf design parameters constant.
Using Bezier curve parametric method, only need to modify the control that control generates Bezier curve in optimization process
System point coordinate, can achieve the purpose that modify blade profile.In the present embodiment, joined using 8 rank Bezier curve centering camber lines
Numberization, 8 rank Bezier curves one share 9 control points (first control point is coordinate origin).1st control point (origin) and
2nd control point line and x-axis angle are defined as vane inlet metal angle, same 8th control point and the 9th control point line
Blade exit metal angle is defined as with x-axis angle, and the expression formula of vane inlet metal angle and blade exit metal angle is as follows:
Guarantee that blade axial direction chord length is constant, the x coordinate at Bezier curve control point immobilizes, and in retrofitting process, leads to
The y-coordinate for crossing modification control point makes vane inlet metal angle be revised as target value, for example, the y-coordinate at the 2nd control point of modification,
So that vane inlet metal angle is revised as target value, and second control point remodeling of label and prototype y-coordinate difference are delta.
To guarantee that outlet metal angle is constant, the y-coordinate at the 8th, 9 control point is constant, the remodeling at the interlude control point of Bezier curve
It is generated with the y-coordinate difference linear change of prototype to 0, such as by following linear function mode:
Delta=y '2-y2
To the Bezier curve control point of camber line in acquisition.
Preferably, blade optimization Transform Type design is carried out with the Autoblade software in NUMECA software package, by acquisition
The Bezier curve control point input Autoblade of middle camber line can get the leaf geometric parameter of remodeling.
Finally, combining the prototype blade of the remodeling stator blade of distorted region and non-distorted region, complete cycle is obtained
To asymmetric stator blade.
In embodiments herein, according to the rule of metal angle and optimizing, 17 remodeling stator blades are sequentially generated, it will be abnormal
Become the 17 remodeling blades in region and the prototype blade combination of non-distorted region 17, obtains complete cycle asymmetric stator design.Fig. 3 shows
Go out in 90% leaf eminence, the comparison diagram of the stator blade profile of prototype and asymmetric Transform Type design.
How wind is influenced in order to illustrate the design effect of the asymmetric stator of the application and the asymmetric stator design of analysis
Aeroperformance is fanned, here, the complete cycle unsteady numerical simulations result of prototype and asymmetric remodeling stator is compared and analyzed.From
The comparison of compressor aeroperformance numerical result is as can be seen that the application improves BLI under the conditions of the BLI inlet distortion of table 1
Fan stage efficiency under the conditions of effect inlet distortion reduces stator loss coefficient, while fan internal flow asymmetry reduces,
Rotor efficiency small elevation.
Wherein adiabatic efficiency ηis.It is defined as follows with loss coefficient ω:
ω=(Pti-Pto)/(Pti-Pi)
PtoIndicate outlet stagnation pressure, PtiIndicate import section stagnation pressure, TtoFor outlet total temperature, TtiFor import section
Total temperature, PiFor import section static pressure.
Compressor aeroperformance numerical result compares under the conditions of 1 BLI inlet distortion of table
| Stator designs in compressor | Whole grade adiabatic efficiency ηis. | Rotor adiabatic efficiency ηis. | Stator loss coefficient ω |
| Prototype stator | 86.33% | 90.08% | 7.34% |
| Asymmetric remodeling stator | 87.16% | 90.24% | 6.00% |
| Opposite variation | + 0.96% | + 0.18% | - 18.29% |
Fig. 4 to fig. 6 is shown respectively in 90% leaf height, 50% leaf height and the comparison of 10% leaf eminence stator outlet entropy
Figure, it is available from the entropy comparison diagram of stator outlet: in -150 ° to 30 ° circumferential positions, at blade tip, asymmetric remodeling
The entropy of stator is significantly lower than prototype stator, and asymmetric stator design mainly reduces the flow losses of stator blade tip.
Fig. 7 shows the stator S1 stream interface VELOCITY DISTRIBUTION of prototype and Transform Type design under different leaf height and circumferential angle and compares
Figure.From (a) figure of Fig. 7, i.e. find out in 90% leaf height and -60 ° of circumferential position comparison diagrams, in flow distortion region, prototype stator
There is biggish flow separation in the suction surface of blade profile, and the remodeling stator Jing Guo asymmetric stator optimization design, blade profile suction
The isolated alleviation in face.From (b) figure of Fig. 7, i.e. find out in 50% leaf height and -30 ° of circumferential position comparison diagrams, leaf central part point into
Gas distortion intensity is minimum, flows preferably in prototype and remodeling stator.From (c) figure of Fig. 7, i.e. 10% leaf height and -30 ° of circumferential positions
It sets in comparison diagram and finds out, distortion causes the region stator blade root angle of attack excessive, occur flow separation in advance, and flowed in stator of retrofiting
It has moved isolated and has alleviated.
As it can be seen that the optimization method of asymmetric stator, has delayed blade profile suction surface separation stream in distortion area and non-distorted region
It is dynamic, reduce flow losses.
Here, although illustrating the design method of the application by taking high load capacity transonic fan grade NASA Stage67 as an example, this
Field it will be appreciated by the skilled person that the design method of the application can be applied to it is any consider BLI inlet distortion effect blade tip across
In the asymmetric stator design of sound fan.
Those skilled in the art is also understood that above embodiment just for the sake of clearly demonstrating the disclosure, and
It is not to be defined to the scope of the present disclosure.For those skilled in the art, on the basis of disclosed above also
Other variations or modification can be made, and these variations or modification are still in the scope of the present disclosure.
Claims (10)
1. a kind of asymmetric stator design method of blade tip transonic fan for considering BLI inlet distortion effect, comprising the following steps:
Step 1: according to the fan stator import incoming flow situation of prototype under the conditions of BLI inlet distortion by stator blade along week
To being divided into distorted region and non-distorted region；
Step 2: remodeling is optimized to the stator blade for being divided into distorted region, meanwhile, it is divided into the stator of non-distorted region
Blade keeps prototype；
Step 3: by distorted region remodeling stator blade and non-distorted region prototype blade combine, obtain complete cycle to
Asymmetric stator blade.
2. the method according to claim 1, wherein the step 1 includes according under the conditions of BLI inlet distortion
The deviation situation of the angle of attack of the fan stator of prototype and design value divides distorted region and non-distorted region.
3. the method according to claim 1, wherein the step 2 includes by amendment stator import metal
Angle makes it be directed at direction of flow to optimize remodeling to the stator blade for being divided into distorted region, to reduce the stator angle of attack.
4. according to the method described in claim 3, it is characterized in that, in modification stator botanical origin blade profile by way of camber line come
Correct stator import metal angle.
5. according to the method described in claim 4, it is characterized in that, defining stator leaf by the way of camber line and thickness distribution in
Type.
6. according to the method described in claim 5, it is characterized in that, carry out parametrization fitting to stator blade profile, with to being divided into
The stator blade of distorted region optimizes remodeling.
7. according to the method described in claim 6, it is characterized in that, using 8 rank Bezier curves to stator blade product superimposing thread and
Middle camber line carries out parametrization fitting.
8. the method according to the description of claim 7 is characterized in that guarantee blade axial direction chord length it is constant, the control of Bezier curve
The x coordinate of system point immobilizes, and in retrofitting process, the y-coordinate by modifying control point is revised as vane inlet metal angle
Target value, also, to guarantee that outlet metal angle is constant, the y-coordinate at the 8th, 9 control point is constant, the interlude of Bezier curve
The remodeling at control point and the y-coordinate difference linear change of prototype are to 0, so that the Bezier curve of camber line controls in obtaining
Point.
9. the method according to any one of claim 6 to 8, which is characterized in that in NUMECA software package
Autoblade software carries out blade optimization Transform Type design.
10. the method according to any one of claim 2 to 8, which is characterized in that the step 2 includes: p- 150 °
The angle of attack of blade tip is reduced to -60 ° of circumferential zones, p- 60 ° to -30 ° of circumferential zones reduce the angle of attack of 50% leaf height or more,
P- 30 ° to 30 ° of circumferential zones reduce the high angle of attack of full leaf, keep prototype to 30 ° Dao -150 ° of circumferential zones.
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112377269A (en) * | 2021-01-11 | 2021-02-19 | 中国空气动力研究与发展中心高速空气动力研究所 | Anti-distortion stator design method suitable for contra-rotating lift propulsion device |
| CN113864243A (en) * | 2021-09-10 | 2021-12-31 | 中国民航大学 | Axial flow compressor for improving full-circumferential flow field |
| CN113883098A (en) * | 2021-09-10 | 2022-01-04 | 中国民航大学 | Stator blade distortion-resistant axial flow compressor and stator blade distortion-resistant method of axial flow compressor |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112377269A (en) * | 2021-01-11 | 2021-02-19 | 中国空气动力研究与发展中心高速空气动力研究所 | Anti-distortion stator design method suitable for contra-rotating lift propulsion device |
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| CN113864243A (en) * | 2021-09-10 | 2021-12-31 | 中国民航大学 | Axial flow compressor for improving full-circumferential flow field |
| CN113883098A (en) * | 2021-09-10 | 2022-01-04 | 中国民航大学 | Stator blade distortion-resistant axial flow compressor and stator blade distortion-resistant method of axial flow compressor |
| WO2023050692A1 (en) * | 2021-09-10 | 2023-04-06 | 中国民航大学 | Stator vane distortion-resistant axial-flow compressor and stator vane distortion-resistant method for axial-flow compressor |
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