CN101418813A - Optimum design method for wall whorl of compressor - Google Patents
Optimum design method for wall whorl of compressor Download PDFInfo
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- CN101418813A CN101418813A CNA2008102394464A CN200810239446A CN101418813A CN 101418813 A CN101418813 A CN 101418813A CN A2008102394464 A CNA2008102394464 A CN A2008102394464A CN 200810239446 A CN200810239446 A CN 200810239446A CN 101418813 A CN101418813 A CN 101418813A
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Abstract
The invention relates to a method for optimization design of compressor wall surface vortex. The wall surface vortex is the wall surface source for generating flow field vortex and separation, the wall surface vortex diagnosis can reveal the key area having high vortex generation rate on the wall surface of blade. The wall surface vortex is put into optimization process, the peak value integration of the wall surface vortex is taken as a target function or constraint condition, optimization design is performed according to the key area revealed by the wall surface vortex, and the distribution of blade wall surface vortex is controlled and the performance of the compressor is improved. The design method grasps the flow mechanism in the optimize process, performs optimization with pertinence, reduces the dependence on the designers' experience, and improves the optimization efficiency.
Description
Technical field
The present invention relates to a kind of aero-engine compressor Optimization Design, relate in particular to a kind of gas compressor design method of optimizing blade wall vorticity distributions.
Background technique
Gas compressor is one of three big parts of aeroengine, plays the effect to air-flow compression work done.The overall performance index of gas compressor comprises flow, pressure ratio, efficient etc.The development of computational fluid mechanics (CFD) and various optimized Algorithm has promoted the development of the pneumatic numerical optimization of gas compressor.The gas compressor aerodynamic optimization, the general overall performance index such as pressure ratio or efficient set also may select for use two above indexs to be combined to form multiple objective function, under certain constraint conditio as objective function, with CFD is analysis tool, is optimized at blade profile or the curved form of plunderring.
The pneumatic numerical optimization of gas compressor can weaken the dependence to artificer's experience, allows computer generation replace the people to search out more excellent design proposal automatically, can significantly reduce the workload of artificial modification.But also there are some problems at present in numerical optimization, and is longer as the optimization time, and the cost height particularly utilizes CFD to find the solution the situation that the gas compressor interior three-dimensional flows for need, need repeatedly find the solution the flow field in the optimizing process, and is consuming time longer; In addition and since set be the overall performance parameter as objective function, lack assurance in the optimizing process to fluid reason mechanism, optimum parameters lacks specific aim, can make also that to optimize cost very high, income is also less sometimes.
Gas compressor inside is a high-intensity complicated vorticity field, and wall is the main root that vorticity produces.Wall vorticity stream has reflected the production rate of vorticity at wall, and it is the inner wall root that produces separation and vortex in flow field, can disclose the big key area of vorticity production rate.Wall vorticity stream is defined as the product of dynamic viscosity coefficient and wall vorticity normal direction gradient,
Wherein σ is wall vorticity stream, and μ is a dynamic viscosity coefficient, and ω is the wall vorticity, and n is the wall normal vector.
If can control wall vorticity distributions in optimizing process, the key area that discloses at wall vorticity stream is optimized, and is expected to hold flow mechanism in optimizing process, is optimized targetedly, thereby shortens the optimization time, improves optimization efficiency.
Traditional optimization method exists following aspect to replenish at least:
(1) wall vorticity stream is put into optimizing process as Diagnostic parameters, control blade wall vorticity distributions;
(2) key area that discloses at wall vorticity stream is optimized, and improves optimization efficiency.
Summary of the invention
As replenishing of gas compressor traditional optimal design method, the invention provides a kind of optimum design method for wall whorl.
Fig. 1 is the flow chart of optimum design method for wall whorl of compressor of the present invention.Different is with general optimization method, method of the present invention flows peak integration with the wall vorticity in optimizing process be objective function or constraint conditio, the key area that diagnosis discloses at wall vorticity stream is optimized, and reaches the purpose that control wall vorticity flows and improve the gas compressor performance.
Wall vorticity stream is the inner wall root that produces separation and vortex in flow field, the diagnosis of wall vorticity stream can disclose the big key area of blade wall vorticity production rate, be illustrated in figure 2 as one and stride rotor suction surface wall vorticity distributions, can clearly find a positive peak band that disturbs to cause by shock wave/boundary layer, it will cause flow separation, it is unfavorable that gas compressor is added the merit supercharging, should weaken positive peak and push it against the downstream as far as possible for rotor.The direction of improving wall vorticity distributions is: reduce the peak value that causes separation, make its position push the downstream to, it is level and smooth that it is distributed.Wall vorticity stream is put into gas compressor optimal design process as the blade surface Diagnostic parameters, with wall vorticity stream peak integration is objective function, or still as objective function the wall vorticity is flowed peak integration as constraint conditio with overall performance parameter pressure ratio, efficient, be optimized at vane foil or the curved form of plunderring, especially the key area that can disclose at wall vorticity stream such as Fig. 1 stride that regional cross section is optimized in the rotor leaf, form the Optimization Design that a kind of wall vorticity stream instructs.
Content of the present invention is a kind of optimum design method for wall whorl of compressor, comprises having blade wall vorticity stream diagnostic function, and the function that wall vorticity stream peak integration is optimized design as objective function or constraint conditio at key area.
Description of drawings
Fig. 1 is an optimum design method for wall whorl of compressor flow chart of the present invention;
Fig. 2 is for striding rotor suction surface static pressure and wall vorticity distributions contrast ((a) (b) is wall vorticity distributions for static pressure distribution);
Fig. 3 optimizes front and back characteristic curve contrast for striding rotor;
Fig. 4 optimizes front and back suction surface wall vorticity distributions contrast ((a) (b) is the optimization back for before optimizing) for striding rotor;
Fig. 5 for stride rotor optimize before and after blade root, in, sharp blade profile contrast ((a) is blade root, is in the leaf (b), (c) is blade tip).
Embodiment
Its embodiment of optimum design method for wall whorl of compressor of the present invention comprises as shown in Figure 1: step 1, prototype is carried out three-dimensional viscosity CFD analyze, definition obtains blade wall vorticity distributions according to wall vorticity stream;
Step 2, judge whether wall vorticity distributions is reasonable, whether concrete observation has tangible wall vorticity stream peak region, whether has caused flow separation in conjunction with this peak value of flow field analysis, if it is flow-optimized then need to carry out the wall vorticity;
Step 3, change the key area geometric parameter according to wall vorticity stream diagnostic result and comprise blade profile and curvedly plunder form etc., wherein need analyze and change which kind of geometric format and produce effect most controlling this zone flows;
Step 4, regenerate three dimendional blade how much, carry out flow field CFD and analyze, obtain blade wall vorticity distributions, try to achieve target function value, compare with prototype with the streamed expression of wall vorticity;
Step 5, the certain optimized Algorithm of utilization are determined the direction of next step iteration of design parameter through the repeated calculation optimizing, finally to obtain optimum result, make blade wall vorticity distributions reasonable, and the gas compressor performance improves.
Using this design method to stride rotor blade profile to one optimizes.Rotor with the streamed expression of wall vorticity adds the merit amount as objective function (as (2) formula), is optimized at the cross section blade profile mean camber line of cubic curve parametrization (as (3) formula).
y＝a
1+a
2x+a
3x
2+a
3x
3 (3)
For optimizing the characteristic curve contrast of back rotor and prototype, a left side is flow-pressure ratio characteristic curve as Fig. 3, and the right side is flow-efficiency characteristic curve, and the black hollow dots is characteristic before optimizing, and red solid dot is for optimizing the back characteristic.Can find to optimize all raisings greatly of back rotor pressure ratio, efficient.Peak efficiencies point pressure ratio has improved 5.73%, and efficient has improved 1.12%.The suction surface wall vorticity distributions contrast (left side for optimize before, the right side for optimize back) of Fig. 4 for optimizing front and back, suction surface wall vorticity stream positive peak weakens after optimizing, scope is dwindled, move behind the position, weakened shock strength and postponed separation, add merit amount and efficient thereby improved blade.Fig. 5 for blade root before and after optimizing, in, the blade profile contrast of point.Above result has proved that the optimum design method for wall whorl of this invention can carry out the gas compressor optimal design efficiently.
The invention has the advantages that by means of the diagnosis of blade wall vorticity stream and disclose crucial flow region, put it in the optimizing process, flow peak integration as objective function or constraint conditio with the wall vorticity, be optimized design at the key area that discloses, thereby in optimizing process, hold flow mechanism, be optimized targetedly, reduced experimental dependence, improved optimization efficiency the artificer.
The above; only for the preferable embodiment of the present invention, but protection scope of the present invention is not limited thereto, and anyly is familiar with those skilled in the art in the technical scope that the present invention discloses; the variation that can expect easily or replacement all should be encompassed within protection scope of the present invention.
Claims (6)
1, a kind of optimum design method for wall whorl of compressor is characterized in that, comprises step:
(1) prototype is carried out three-dimensional viscosity CFD and analyze, the definition of flowing according to the wall vorticity obtains blade wall vorticity distributions;
(2) judge whether wall vorticity distributions is reasonable, whether concrete observation has tangible wall vorticity stream peak region, whether has caused flow separation in conjunction with this peak value of flow field analysis, if it is flow-optimized then need to carry out the wall vorticity;
(3) change the key area geometric parameter according to wall vorticity stream diagnostic result and comprise blade profile and the curved form etc. of plunderring;
(4) regenerate three dimendional blade how much, carry out flow field CFD and analyze, obtain blade wall vorticity distributions, try to achieve target function value with the streamed expression of wall vorticity;
(5) use certain optimized Algorithm such as simulated annealing, determine the direction of next step iteration of design parameter,, finally obtain optimum result through the repeated calculation optimizing.
2, optimum design method for wall whorl of compressor as claimed in claim 1, it is characterized in that, disclose crucial flow region by means of the diagnosis of blade wall vorticity stream, the wall vorticity is banished in the optimizing process, as objective function or constraint conditio, the key area that discloses at wall vorticity stream is optimized design with wall vorticity stream peak integration.
3, optimum design method for wall whorl of compressor as claimed in claim 1 is characterized in that, the wall vorticity is flowed as the blade surface Diagnostic parameters.
4, optimum design method for wall whorl of compressor as claimed in claim 1 is characterized in that, more excellent wall vorticity distributions form is: reduce the peak value that causes separation, push its position to downstream, it is level and smooth that it is distributed.
5, optimum design method for wall whorl of compressor as claimed in claim 1 is characterized in that, the function of the streamed expression of wall vorticity is optimized as objective function or constraint conditio.
6, optimum design method for wall whorl of compressor as claimed in claim 1 is characterized in that, the key area that diagnosis discloses at wall vorticity stream is optimized design.
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102436181A (en) * | 2011-11-25 | 2012-05-02 | 中国航天空气动力技术研究院 | Flow control method for shear layer |
| CN106682292A (en) * | 2016-12-14 | 2017-05-17 | 西安交通大学 | Blade root structure optimization method of dimensionality reduction simulated annealing algorithm |
| CN107148599A (en) * | 2014-10-31 | 2017-09-08 | 西门子股份公司 | Method for predicting turbine performance |
| CN109655271A (en) * | 2018-12-27 | 2019-04-19 | 南京航空航天大学 | A kind of single pair hypersonic flow is to vortex generating device |
| CN110705079A (en) * | 2019-09-25 | 2020-01-17 | 哈尔滨工程大学 | Centrifugal compressor structure optimization method based on simulated annealing algorithm |
| CN112963255A (en) * | 2021-03-11 | 2021-06-15 | 西华大学 | Detachable two-stroke aeroengine active fuel auxiliary starting system and method |
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2008
- 2008-12-10 CN CNA2008102394464A patent/CN101418813A/en active Pending
Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102436181A (en) * | 2011-11-25 | 2012-05-02 | 中国航天空气动力技术研究院 | Flow control method for shear layer |
| CN102436181B (en) * | 2011-11-25 | 2013-04-24 | 中国航天空气动力技术研究院 | Flow control method for shear layer |
| CN107148599A (en) * | 2014-10-31 | 2017-09-08 | 西门子股份公司 | Method for predicting turbine performance |
| US10552555B2 (en) | 2014-10-31 | 2020-02-04 | Siemens Aktiengesellschaft | Method for the prediction of turbomachine performances |
| CN107148599B (en) * | 2014-10-31 | 2020-12-18 | 西门子股份公司 | Method for predicting turbine performance |
| CN106682292A (en) * | 2016-12-14 | 2017-05-17 | 西安交通大学 | Blade root structure optimization method of dimensionality reduction simulated annealing algorithm |
| CN106682292B (en) * | 2016-12-14 | 2019-10-11 | 西安交通大学 | A kind of leaf and root structure optimization method of dimensionality reduction simulated annealing |
| CN109655271A (en) * | 2018-12-27 | 2019-04-19 | 南京航空航天大学 | A kind of single pair hypersonic flow is to vortex generating device |
| CN110705079A (en) * | 2019-09-25 | 2020-01-17 | 哈尔滨工程大学 | Centrifugal compressor structure optimization method based on simulated annealing algorithm |
| CN110705079B (en) * | 2019-09-25 | 2023-01-03 | 哈尔滨工程大学 | Centrifugal compressor structure optimization method based on simulated annealing algorithm |
| CN112963255A (en) * | 2021-03-11 | 2021-06-15 | 西华大学 | Detachable two-stroke aeroengine active fuel auxiliary starting system and method |
| CN112963255B (en) * | 2021-03-11 | 2023-02-24 | 西华大学 | Detachable two-stroke aeroengine active fuel auxiliary starting system and method |
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