CN113051840B - Grid generation method for changing geometry of blade tip of compressor - Google Patents

Grid generation method for changing geometry of blade tip of compressor Download PDF

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CN113051840B
CN113051840B CN202011552895.1A CN202011552895A CN113051840B CN 113051840 B CN113051840 B CN 113051840B CN 202011552895 A CN202011552895 A CN 202011552895A CN 113051840 B CN113051840 B CN 113051840B
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grid
blade
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CN113051840A (en
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姜涛
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AVIC Jincheng Nanjing Engineering Institute of Aircraft Systems
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    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F30/00—Computer-aided design [CAD]
    • G06F30/20—Design optimisation, verification or simulation
    • G06F30/28—Design optimisation, verification or simulation using fluid dynamics, e.g. using Navier-Stokes equations or computational fluid dynamics [CFD]
    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F2113/00—Details relating to the application field
    • G06F2113/08—Fluids
    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F2119/00—Details relating to the type or aim of the analysis or the optimisation
    • G06F2119/14—Force analysis or force optimisation, e.g. static or dynamic forces

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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 correspondingly adapted grid program is generated after the blade tip geometry is changed, and the grid generated after the blade tip geometry is changed is poured into commercial software to perform numerical simulation, thereby realizing the compensation of the grid generation program function of the commercial software.

Description

Grid generation method for changing geometry of blade tip of compressor
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 geometry of the compressor blade tip.
Background
The compressor is used as a main component of the aeroengine, and the performance of the compressor has important influence on the operation of the whole engine. With the development of computer technology, many hydrodynamics researchers use CFD technology to perform numerical simulation on the flow field of the compressor, so that the cost investment in the experimental process is reduced. At present, numerical simulation technology for conventional blades is mature, and comprises grid generation technology, calculation technology and the like.
In the process of processing or using the blade, the geometry of the blade tip can be changed due to the processing error or abrasion, mechanical damage and the like in the actual use process, so that the blade tip clearance performance is affected.
The conventional blade tip shape is a flat blade top, 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 for the blade tip geometry change.
Disclosure of Invention
The purpose of the invention is that: the invention utilizes NUMECA software to generate a conventional blade grid, then utilizes an autonomously developed program to read grid data, changes the geometrical shape of the blade tip, and generates an adaptive grid, so that the grid adapted to the geometrical shape of the blade tip after different changes can be generated, and the numerical simulation of the blade tip after geometrical changes can be realized.
The technical scheme of the invention is as follows:
a method of generating a compressor blade flow field adaptation grid comprising the steps of:
step one, a conventional grid of compressor blades generated by using common commercial software;
step two, extracting conventional grid data of the compressor blade to be processed;
thirdly, carrying out local encryption processing on grids at the tip modification geometric positions of the modified compressor blade according to the set parameters, and reflecting the tip geometric shapes by using enough grids to form grids of the compressor blade with the tip local encryption;
and step four, outputting the local encrypted grid data of the compressor blade at the blade tip.
In the third step, different encryption processing methods are selected for different geometrical transformation modes of the blade tips of the compressor blades.
Further, the third step specifically includes: an encryption method for cutting the top side of a leaf, an encryption method for rounding the top of a leaf, and an encryption method for chamfering the top of a leaf.
Further, the encryption method of the cutting of the top side of the blade is as follows:
the method comprises the following steps that in the original condition, one end of a blade top is an O point, a blade tip deformation starting point is an A point, a blade tip deformation ending point is a C point, a blade tip deformation transition point is a B point, AO is a gap which is 3 times, and OC is 1/3 times of the thickness of a local blade; in the grid generation process, the first layer of the grid line of the OA segment translates towards the OC direction, and the translation distance d and the distance x of a certain point distance O meet the following relation:
after the first layer of grid lines are determined, the remaining grids are calculated according to the encryption rule among the original grids.
Further, the tip rounding encryption method comprises a tip rounding pressure surface rounding encryption method and a tip rounding suction surface rounding encryption method, and the tip rounding pressure surface rounding encryption method is the same as the tip rounding suction surface rounding encryption method.
Further, the top rounding pressure surface rounding encryption method comprises the following steps:
one end of the blade top in the original condition is an O point, the tip deformation starting point is an A point, the tip deformation ending point is a C point, and the possible point of the blade tip in the original condition is defined as a B point;
translating a certain point B of the first layer of grid lines near the top of the leaf at the OA end, wherein the translation direction is OC direction, and the translation distance d meets the following relation:
wherein R is the fillet radius of the AC circular arc; after the first layer of grid lines are determined, the remaining grids are calculated according to the encryption rule among the original grids.
Further, the top chamfer encryption method comprises a top chamfer pressure surface chamfer encryption method and a top chamfer suction surface chamfer encryption method, and the top chamfer pressure surface chamfer encryption method is the same as the top chamfer suction surface chamfer encryption method.
Further, the encryption method for the chamfering of the blade tip chamfering pressure surface comprises the following steps:
one end of the blade top in the original condition is an O point, the tip deformation starting point is an A point, the tip deformation ending point is a C point, and the possible point of the blade tip in the original condition is defined as a B point;
translating a certain point B of the first layer of grid lines near the top of the leaf at the OA end, wherein the translation direction is OC direction, and the translation distance d meets the following relation:
d＝l(OB)·tanα，
wherein alpha is the angle of the chamfer;
after the first layer of grid lines are determined, the remaining grids are calculated according to the encryption rule among the original grids.
Further, the common commercial software is NUMECA software, and the grid file is stored in a Plot3D format.
The invention has the advantages that: the method of the invention realizes that the correspondingly adapted grid program is generated after the blade tip geometry is changed, and the grid generated after the blade tip geometry is changed is poured into commercial software to perform numerical simulation, thereby realizing the compensation of the grid generation program function of the commercial software.
Drawings
FIG. 1 is a schematic flow chart of the present invention;
FIG. 2 is a schematic view of the encryption of the tip side cutting grid of the present invention;
FIG. 3 is a tip rounding grid encryption schematic of the present invention;
FIG. 4 is a schematic illustration of the tip chamfer grid encryption of the present invention.
Detailed Description
This section is an embodiment of the present invention for explaining and explaining the technical solution of the present invention.
A method of generating a compressor blade flow field adaptation grid comprising the steps of:
step one, a conventional grid of compressor blades generated by using common commercial software;
step two, extracting conventional grid data of the compressor blade to be processed;
thirdly, carrying out local encryption processing on grids at the tip modification geometric positions of the modified compressor blade according to the set parameters, and reflecting the tip geometric shapes by using enough grids to form grids of the compressor blade with the tip local encryption;
and step four, outputting the local encrypted grid data of the compressor blade at the blade tip.
And thirdly, selecting different encryption processing methods for different geometrical transformation modes of the blade tips of the compressor blade.
The third step specifically comprises: an encryption method for cutting the top side of a leaf, an encryption method for rounding the top of a leaf, and an encryption method for chamfering the top of a leaf.
The encryption method for cutting the top side of the leaf comprises the following steps:
the method comprises the following steps that in the original condition, one end of a blade top is an O point, a blade tip deformation starting point is an A point, a blade tip deformation ending point is a C point, a blade tip deformation transition point is a B point, AO is a gap which is 3 times, and OC is 1/3 times of the thickness of a local blade; in the grid generation process, the first layer of the grid line of the OA segment translates towards the OC direction, and the translation distance d and the distance x of a certain point distance O meet the following relation:
after the first layer of grid lines are determined, the remaining grids are calculated according to the encryption rule among the original grids.
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, wherein the blade tip rounding pressure surface rounding encryption method is the same as the blade tip rounding suction surface rounding encryption method.
The top rounding pressure surface rounding encryption method comprises the following steps:
one end of the blade top in the original condition is an O point, the tip deformation starting point is an A point, the tip deformation ending point is a C point, and the possible point of the blade tip in the original condition is defined as a B point;
translating a certain point B of the first layer of grid lines near the top of the leaf at the OA end, wherein the translation direction is OC direction, and the translation distance d meets the following relation:
wherein R is the fillet radius of the AC circular arc; after the first layer of grid lines are determined, the remaining grids are calculated according to the encryption rule among the original grids.
The blade top chamfering encryption method comprises a blade top chamfering pressure surface chamfering encryption method and a blade top chamfering suction surface chamfering encryption method, wherein the blade top chamfering pressure surface chamfering encryption method is the same as the blade top chamfering suction surface chamfering encryption method.
The encryption method for the chamfering of the blade top chamfering pressure surface comprises the following steps:
one end of the blade top in the original condition is an O point, the tip deformation starting point is an A point, the tip deformation ending point is a C point, and the possible point of the blade tip in the original condition is defined as a B point;
translating a certain point B of the first layer of grid lines near the top of the leaf at the OA end, wherein the translation direction is OC direction, and the translation distance d meets the following relation:
d＝l(OB)·tanα，
wherein alpha is the angle of the chamfer; after the first layer of grid lines are determined, the remaining grids are calculated according to the encryption rule among the original grids.
The common commercial software is NUMECA software, and the grid file is stored in a Plot3D format.
Another embodiment of the present invention will be described below with reference to the accompanying drawings.
An embodiment of the present invention is shown in fig. 1. Firstly, generating a conventional grid structure through NUMECA software, and storing a grid file into a Plot3D format. In an autonomously developed program, the execution is performed in modules. Firstly, calling a grid data reading program, and setting a parameter file by the second step of reading the program, wherein the parameter of the Guan Shejian geometric change is read; thirdly, according to the set parameters, local encryption is carried out on grids at the geometrical position of the modified blade tip, and the geometrical shape of the blade tip is embodied by enough grids to form a grid form shown in the OA section of FIG. 2.
And thirdly, selecting a blade tip geometric transformation mode according to the requirement, and correspondingly calling a processing program. The processing procedure is to change the coordinate value of the first layer of grid according to the method of the technical scheme, and the first layer of grid line is the blade profile. After the grid lines of the first layer are determined, the rest grids are calculated according to the encryption rule among the original grids, namely the distances between the nth layer of grids and the n-1 th layer of grids are equal to the distances between the nth layer of grids and the n-1 th layer of grids. (i.e., the magnification change between grid layers is the same)
And step four, outputting the Plot3D grid file, and ending the program.
The grid generation program related by the invention is mainly performed for three blade tip geometric changes: tip side cutting (fig. 2), tip rounding (fig. 3), tip chamfering (fig. 4), 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 the point O where AO is 3 times the clearance and OC is 1/3 times the local blade thickness. In the grid generation process, the first layer of the grid line of the OA segment translates towards the OC direction, and the translation distance d and the distance x of a certain point distance O meet the following relation:
after the first layer of grid lines are determined, the rest grids are calculated according to the encryption rule among the original grids.
For tip rounding and chamfering cases, we will discuss here, as both mesh generation methods are similar. When the tip is rounded, as shown in fig. 3, it is desirable that both the pressure and suction surfaces be rounded, only the pressure surface portion will be described.
Similar to the previous grid generation method, firstly, translating a certain point B of the first layer of grid line at the OA end near the top of the leaf, wherein the translation direction is OC direction, and the translation distance d meets the following relation:
wherein R is the corner radius (AC arc).
For the case of leaf top chamfering, as with the rounding method, only the translation distance d of a certain point B of the first layer of grid lines satisfies the following relation:
d＝l(OB)·tanα
where α is the angle of chamfer, and fig. 4 is a schematic view of the grid after tip chamfering.

Claims (6)

1. A method of generating a compressor blade flow field adaptation grid comprising the steps of:
step one, a conventional grid of compressor blades generated by using common commercial software;
step two, extracting conventional grid data of the compressor blade to be processed;
thirdly, carrying out local encryption processing on grids at the tip modification geometric positions of the modified compressor blade according to the set parameters, and reflecting the tip geometric shapes by using enough grids to form grids of the compressor blade with the tip local encryption;
outputting the local encrypted blade grid data of the compressor blade;
in the third step, different encryption processing methods are selected for different geometrical transformation modes of the blade tips of the compressor blade;
the third step specifically comprises: encryption method for cutting the top side of a leaf;
the encryption method for cutting the top side of the leaf comprises the following steps:
one end of the blade top in the original condition is O point, the tip deformation starting point is A point, the tip deformation ending point is C point, the tip deformation transition point is B point, wherein AO is 3 times of gap, OC is 1/3 times of the thickness of the local blade, and B 1 The projection of the point B on the OA line; in the grid generation process, the first layer of grid line of the OA segment translates towards the OC direction, and the translation distance d and the distance x of the O point meet the following relation:
after the first layer of grid lines are determined, the remaining grids are calculated according to the encryption rule among the original grids.
2. The method of generating a compressor blade flow field adaptation grid of claim 1, wherein step three further comprises a tip rounding encryption method, the tip rounding encryption method comprising a tip rounding pressure surface rounding encryption method and a tip rounding suction surface rounding encryption method, the tip rounding pressure surface rounding encryption method being the same as the tip rounding suction surface rounding encryption method.
3. The method of generating a compressor blade flow field adaptation grid according to claim 2, wherein the tip rounding pressure face rounding encryption method is:
one end of the blade top in the original condition is an O point, the tip deformation starting point is an A point, the tip deformation ending point is a C point, and the possible point of the blade tip in the original condition is defined as a B point;
translating the point B on the first layer of grid line of the OA end near the leaf top, wherein the translation direction is OC direction, and the translation distance d meets the following relation:
wherein R is the fillet radius of the AC circular arc; after the first layer of grid lines are determined, the remaining grids are calculated according to the encryption rule among the original grids.
4. The method of generating a flow field adaptation grid for a compressor blade of claim 1, wherein step three further comprises a top chamfer encryption method, the top chamfer encryption method comprising a top chamfer pressure surface chamfer encryption method and a top chamfer suction surface chamfer encryption method, the top chamfer pressure surface chamfer encryption method being the same as the top chamfer suction surface chamfer encryption method.
5. The method for generating a flow field adaptive mesh for a compressor blade of claim 4, wherein the tip chamfer pressure face chamfer encryption method comprises:
one end of the blade top in the original condition is an O point, the tip deformation starting point is an A point, the tip deformation ending point is a C point, and the possible point of the blade tip in the original condition is defined as a B point;
translating the point B on the first layer of grid line of the OA end near the leaf top, wherein the translation direction is OC direction, and the translation distance d meets the following relation:
d＝l(OB)·tanα，
wherein alpha is the angle of the chamfer; after the first layer of grid lines are determined, the remaining grids are calculated according to the encryption rule among the original grids.
6. The method of generating a compressor blade flow field adaptation grid according to claim 1, wherein the common commercial software is NUMECA software and the grid file is saved in a Plot3D format.
CN202011552895.1A 2020-12-24 2020-12-24 Grid generation method for changing geometry of blade tip of compressor Active CN113051840B (en)

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Citations (3)

* Cited by examiner, † Cited by third party
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

Patent Citations (3)

* Cited by examiner, † Cited by third party
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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