CN113051840A - Grid generation method for changing geometry of blade tip of gas compressor - Google Patents
Grid generation method for changing geometry of blade tip of gas compressor Download PDFInfo
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Abstract
The invention belongs to the technical field of computational fluid mechanics, and discloses a method for generating a flow field adaptive grid of a compressor blade. The method of the invention realizes that the mesh program which is correspondingly adapted is generated after the blade tip geometry is changed, and the mesh generated after the blade tip geometry is changed is poured into the commercial software for numerical simulation, thereby realizing the compensation of the mesh generation program function of the commercial software.
Description
Technical Field
The invention belongs to the technical field of computational fluid mechanics, relates to a method for generating a flow field adaptive grid of a compressor blade, and particularly relates to a grid generation method for changing the blade tip geometry of a compressor.
Background
The compressor is used as a main part of an aeroengine, and the performance of the compressor has important influence on the work of the whole aeroengine. With the development of computer technology, a plurality of researchers of fluid mechanics use the CFD technology to carry out numerical simulation on the flow field of the gas compressor, so that the cost investment in the experimental process is reduced. At present, numerical simulation technologies for conventional blades are mature, and include grid generation technologies, calculation technologies and the like.
During the processing or using process of the blade, the geometry at the blade tip is changed due to processing errors or abrasion, mechanical damage and the like existing in the actual using process, so that the blade tip clearance performance is influenced.
The conventional blade tip shape is a flat blade tip, when the blade tip geometry changes, the adapted grid structure should also change, and currently common commercial software, such as NUMECA software, cannot generate the adapted grid structure according to the change of the blade tip geometry.
Disclosure of Invention
The purpose of the invention is as follows: the invention uses NUMCA software to generate a conventional blade grid, then uses an autonomously developed program to read grid data, changes the geometric shape of the blade tip, generates an adaptive grid, and can generate a grid adaptive to the blade tip geometry after different changes, thereby realizing numerical simulation after the blade tip geometry is changed.
The technical scheme of the invention is as follows:
a method for generating a compressor blade flow field adaptive grid comprises the following steps:
step one, generating a conventional grid of a compressor blade by using common commercial software;
extracting the conventional grid data of the compressor blade to be processed;
thirdly, according to the set parameters, local encryption processing is carried out on the grids at the tip modification geometry of the modified compressor blades, and the tip geometry is reflected by enough grids to form the grids of the compressor blades with partially encrypted tips;
and step four, outputting the grid data of the compressor blade with the locally encrypted blade tip.
Furthermore, in the third step, different encryption processing methods are selected for different geometric transformation modes of the blade tips of the blades of the air compressor.
Further, the third step specifically comprises: a method of encrypting a tip side cut, a method of encrypting a tip rounding, and a method of encrypting a tip chamfer.
Further, the method for encrypting the cutting of the top side of the blade comprises the following steps:
one end of the blade top under the original condition is a point O, the initial point of blade tip deformation is a point A, the end point of blade tip deformation is a point C, the transition point of blade tip deformation is a point B, wherein AO is 3 times of clearance, and OC is 1/3 times of the thickness of the local blade; in the grid generating process, the OA section first layer grid line is translated towards the OC direction, and the translation distance d and the distance x between a certain point and the distance O satisfy the following relation:
and after the first layer of grid lines are determined, calculating the rest grids according to the encryption rule among the original grids.
Further, the blade tip rounding encryption method comprises a blade tip rounding pressure surface rounding encryption method and a blade tip rounding suction surface rounding encryption method, and the blade tip rounding pressure surface rounding encryption method is the same as the blade tip rounding suction surface rounding encryption method.
Further, the method for encrypting the top rounding pressure surface rounding comprises the following steps:
one end of the blade top under the original condition is a point O, the initial point of blade tip deformation is a point A, the end point of blade tip deformation is a point C, and the possible point of the blade tip under the original condition is defined as a point B;
translating a certain point B of a first layer grid line at the OA end near the leaf top, wherein the translation direction is OC direction, and the translation distance d satisfies the following relational expression:
wherein R is the fillet radius of the AC arc; and after the first layer of grid lines are determined, calculating the rest grids according to the encryption rule among the original grids.
Further, the blade top chamfer encryption method comprises a blade top chamfer pressure surface chamfer encryption method and a blade top chamfer suction surface chamfer encryption method, and the blade top chamfer pressure surface chamfer encryption method is the same as the blade top chamfer suction surface chamfer encryption method.
Further, the method for encrypting the chamfer angle of the pressure surface of the chamfer angle at the blade top comprises the following steps:
one end of the blade top under the original condition is a point O, the initial point of blade tip deformation is a point A, the end point of blade tip deformation is a point C, and the possible point of the blade tip under the original condition is defined as a point B;
translating a certain point B of a first layer grid line at the OA end near the leaf top, wherein the translation direction is OC direction, and the translation distance d satisfies the following relational expression:
d＝l(OB)·tanα，
wherein alpha is the angle of the chamfer;
and after the first layer of grid lines are determined, calculating the rest grids according to the encryption rule among the original grids.
Further, common commercial software is NUMECA software, and the mesh file is saved in the Plot3D format.
The invention has the advantages that: the method of the invention realizes that the mesh program which is correspondingly adapted is generated after the blade tip geometry is changed, and the mesh generated after the blade tip geometry is changed is poured into the commercial software for numerical simulation, thereby realizing the compensation of the mesh generation program function of the commercial software.
Drawings
FIG. 1 is a schematic flow diagram of the present invention;
FIG. 2 is a schematic diagram of the leaf tip side cut grid encryption of the present invention;
FIG. 3 is a schematic view of tip blending mesh encryption in accordance with the present invention;
FIG. 4 is a schematic diagram of tip chamfer mesh encryption in accordance with the present invention.
Detailed Description
This section is an example of the present invention and is provided to explain and illustrate the technical solutions of the present invention.
A method for generating a compressor blade flow field adaptive grid comprises the following steps:
step one, generating a conventional grid of a compressor blade by using common commercial software;
extracting the conventional grid data of the compressor blade to be processed;
thirdly, according to the set parameters, local encryption processing is carried out on the grids at the tip modification geometry of the modified compressor blades, and the tip geometry is reflected by enough grids to form the grids of the compressor blades with partially encrypted tips;
and step four, outputting the grid data of the compressor blade with the locally encrypted blade tip.
In the third step, different encryption processing methods are selected for different geometric transformation modes of the blade tips of the blades of the air compressor.
The third step specifically comprises: a method of encrypting a tip side cut, a method of encrypting a tip rounding, and a method of encrypting a tip chamfer.
The method for encrypting the cutting of the top side of the blade comprises the following steps:
one end of the blade top under the original condition is a point O, the initial point of blade tip deformation is a point A, the end point of blade tip deformation is a point C, the transition point of blade tip deformation is a point B, wherein AO is 3 times of clearance, and OC is 1/3 times of the thickness of the local blade; in the grid generating process, the OA section first layer grid line is translated towards the OC direction, and the translation distance d and the distance x between a certain point and the distance O satisfy the following relation:
and after the first layer of grid lines are determined, calculating the rest grids according to the encryption rule among the original grids.
The method for rounding and encrypting the tip comprises a method for rounding and encrypting a pressure surface of the tip rounding and a method for rounding and encrypting a suction surface of the tip rounding, and the method for rounding and encrypting the pressure surface of the tip rounding is the same as the method for rounding and encrypting the suction surface of the tip rounding.
The method for rounding and encrypting the top rounding pressure surface comprises the following steps:
one end of the blade top under the original condition is a point O, the initial point of blade tip deformation is a point A, the end point of blade tip deformation is a point C, and the possible point of the blade tip under the original condition is defined as a point B;
translating a certain point B of a first layer grid line at the OA end near the leaf top, wherein the translation direction is OC direction, and the translation distance d satisfies the following relational expression:
wherein R is the fillet radius of the AC arc; and after the first layer of grid lines are determined, calculating the rest grids according to the encryption rule among the original grids.
The blade top chamfer encryption method comprises a blade top chamfer pressure surface chamfer encryption method and a blade top chamfer suction surface chamfer encryption method, and the blade top chamfer pressure surface chamfer encryption method is the same as the blade top chamfer suction surface chamfer encryption method.
The method for encrypting the chamfer angle of the pressure surface of the chamfer angle at the blade top comprises the following steps:
one end of the blade top under the original condition is a point O, the initial point of blade tip deformation is a point A, the end point of blade tip deformation is a point C, and the possible point of the blade tip under the original condition is defined as a point B;
translating a certain point B of a first layer grid line at the OA end near the leaf top, wherein the translation direction is OC direction, and the translation distance d satisfies the following relational expression:
d＝l(OB)·tanα，
wherein alpha is the angle of the chamfer; and after the first layer of grid lines are determined, calculating the rest grids according to the encryption rule among the original grids.
Common commercial software is NUMCAA software, and the grid files are saved in the PIot 3D format.
Another embodiment of the present invention is described below with reference to the drawings.
The specific embodiment of the present invention is shown in fig. 1. The conventional grid structure is first generated by NUMECA software, and the grid files are saved in the Plot3D format. In an autonomously developed program, this is done in blocks. Firstly, calling a grid data reading program, setting a parameter file by the second step of reading the program, and reading parameters related to geometric changes of the blade tip; and thirdly, locally encrypting the grids at the position of the modified blade tip geometry according to the set parameters, and reflecting the blade tip geometry by using enough grids to form a grid form shown in the OA section of the figure 2.
And thirdly, selecting a blade tip geometric transformation mode according to needs, and calling a processing program correspondingly. The processing procedure here is to change the coordinate value of the first layer grid according to the method of the above technical solution, and the first layer grid line is the blade profile. After the first layer of grid lines are determined, the rest grids are calculated according to the encryption rule among the original grids, namely the distance between the nth layer of grids and the (n-1) th layer of grids is equal to the distance between the nth layer of grids and the (n-1) th layer of grids. (i.e., the magnification change between mesh layers is the same)
The fourth step outputs the Plot3D grid file and the program ends.
The grid generation program related to the invention is mainly carried out aiming at three blade tip geometric changes: the tip side cutting (fig. 2), tip rounding (fig. 3), tip chamfering (fig. 4) patterns, three tip geometry changes are described below.
As shown in fig. 2, which is a schematic view of the tip in the case of tip-side cutting, the tip end is at point O in the original case, where AO is 3 times the clearance and OC is 1/3 times the local blade thickness. In the grid generating process, the OA section first layer grid line is translated towards the OC direction, and the translation distance d and the distance x between a certain point and the distance O satisfy the following relation:
and after the first layer of grid lines are determined, calculating the rest grids according to the encryption rule among the original grids.
For the tip rounding and chamfering cases, this may be discussed together because the two mesh generation methods are approximate. As shown in fig. 3, when rounding the tip, rounding of both the pressure and suction sides is required, and only the pressure side portion will be described.
Similar to the previous grid generation method, a certain point B of the first layer grid line of the OA end near the leaf top is translated, the translation direction is OC direction, and the translation distance d satisfies the following relational expression:
where R is the fillet radius (AC arc).
For the case of blade top chamfering, as with the rounding method, the translation distance d of a certain point B of the first layer grid line meets the following relation:
d＝l(OB)·tanα
wherein α is the angle of the chamfer, and fig. 4 is a schematic diagram of the grid after the tip of the blade is chamfered.
Claims (9)
1. A method for generating a compressor blade flow field adaptive grid is characterized by comprising the following steps:
step one, generating a conventional grid of a compressor blade by using common commercial software;
extracting the conventional grid data of the compressor blade to be processed;
thirdly, according to the set parameters, local encryption processing is carried out on the grids at the tip modification geometry of the modified compressor blades, and the tip geometry is reflected by enough grids to form the grids of the compressor blades with partially encrypted tips;
and step four, outputting the grid data of the compressor blade with the locally encrypted blade tip.
2. The method for generating the flow field adaptive grid of the compressor blade according to claim 1, wherein in the third step, different encryption processing methods are selected for different geometric transformation modes of the blade tip of the compressor blade.
3. The method for generating the compressor blade flow field adaptation grid according to claim 2, wherein the third step specifically comprises: a method of encrypting a tip side cut, a method of encrypting a tip rounding, and a method of encrypting a tip chamfer.
4. The method of generating a compressor blade flow field adaptation grid according to claim 3, wherein the encryption of the topside cut is:
one end of the blade top under the original condition is a point O, the initial point of blade tip deformation is a point A, the end point of blade tip deformation is a point C, the transition point of blade tip deformation is a point B, wherein AO is 3 times of clearance, and OC is 1/3 times of the thickness of the local blade; in the grid generating process, the OA section first layer grid line is translated towards the OC direction, and the translation distance d and the distance x between a certain point and the distance O satisfy the following relation:
and after the first layer of grid lines are determined, calculating the rest grids according to the encryption rule among the original grids.
5. The method of generating a compressor blade flow field adaptation mesh according to claim 3, wherein the tip blending encryption method includes a tip blending pressure surface blending encryption method and a tip blending suction surface blending encryption method, and the tip blending pressure surface blending encryption method is the same as the tip blending suction surface blending encryption method.
6. The method for generating the compressor blade flow field adaptation grid according to claim 5, wherein the tip rounding pressure surface rounding encryption method comprises the following steps:
one end of the blade top under the original condition is a point O, the initial point of blade tip deformation is a point A, the end point of blade tip deformation is a point C, and the possible point of the blade tip under the original condition is defined as a point B;
translating a certain point B of a first layer grid line at the OA end near the leaf top, wherein the translation direction is OC direction, and the translation distance d satisfies the following relational expression:
wherein R is the fillet radius of the AC arc; and after the first layer of grid lines are determined, calculating the rest grids according to the encryption rule among the original grids.
7. The method of generating a compressor blade flow field adaptation grid according to claim 3, wherein the tip chamfer encryption method comprises a tip chamfer pressure surface chamfer encryption method and a tip chamfer suction surface chamfer encryption method, and the tip chamfer pressure surface chamfer encryption method is the same as the tip chamfer suction surface chamfer encryption method.
8. The method for generating the compressor blade flow field adaptive grid according to claim 7, wherein the blade tip chamfer pressure surface chamfer encryption method comprises:
one end of the blade top under the original condition is a point O, the initial point of blade tip deformation is a point A, the end point of blade tip deformation is a point C, and the possible point of the blade tip under the original condition is defined as a point B;
translating a certain point B of a first layer grid line at the OA end near the leaf top, wherein the translation direction is OC direction, and the translation distance d satisfies the following relational expression:
d＝l(OB)·tanα，
wherein alpha is the angle of the chamfer; and after the first layer of grid lines are determined, calculating the rest grids according to the encryption rule among the original grids.
9. The method for generating the compressor blade flow field adaptive grid according to claim 1, wherein the common commercial software is NUMCA software, and the grid file is stored in a PIot 3D format.
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Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103714246A (en) * | 2013-12-20 | 2014-04-09 | 中国人民解放军海军工程大学 | Wideband spectrum noise forecasting method in cavitation inception state of combined propeller |
| CN107679319A (en) * | 2017-09-29 | 2018-02-09 | 北京航空航天大学 | A kind of Algebra modeling method of circumferential pulsating stress item in through-flow model of turbine |
| CN110851929A (en) * | 2019-11-15 | 2020-02-28 | 中国科学院工程热物理研究所 | Two-dimensional leaf-type optimization design method and device based on self-adaptive grid |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103714246A (en) * | 2013-12-20 | 2014-04-09 | 中国人民解放军海军工程大学 | Wideband spectrum noise forecasting method in cavitation inception state of combined propeller |
| CN107679319A (en) * | 2017-09-29 | 2018-02-09 | 北京航空航天大学 | A kind of Algebra modeling method of circumferential pulsating stress item in through-flow model of turbine |
| CN110851929A (en) * | 2019-11-15 | 2020-02-28 | 中国科学院工程热物理研究所 | Two-dimensional leaf-type optimization design method and device based on self-adaptive grid |
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