CN117036645A - Rapid construction method of impeller mechanical single-channel fluid calculation domain - Google Patents
Rapid construction method of impeller mechanical single-channel fluid calculation domain Download PDFInfo
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Abstract
The application discloses a rapid construction method of a single-channel fluid calculation domain of an impeller machine, which comprises the following steps: designating a key surface; creating a full-cycle impeller fluid domain; generating sampling points according to a certain spatial resolution in a meridian plane of the impeller machine; rotating around the rotating shaft by each sampling point, creating a space arc, and calculating the intersection points of all the space arcs and the designated blade surface; constructing a curved surface by using grids formed by all the intersection points, generating a middle surface of the blade, and then extending the middle surface of the blade towards the key surface to obtain a reference segmentation surface; rotating the reference dividing plane twice around the rotation axis to generate first and second periodic dividing planes; and dividing the whole circumferential impeller fluid domain by adopting the first and second periodic dividing planes to obtain a single-channel blade calculation domain. The periodic dividing surface constructed by the application has the same distance with the adjacent blades, can not intersect with the complex blade surfaces, and can quickly generate the periodic dividing surface meeting the requirements without complex curved surface parameter adjustment.
Description
Technical Field
The application belongs to the technical field of impeller machinery simulation, and particularly relates to a rapid construction method of a single-channel fluid calculation domain of an impeller machinery.
Background
Aeroengines are used as the "heart" of aircraft operation, and their high complexity and precision have created their reputation of "bright beads on crowns". With the development of the aviation industry, the design process of the aero-engine integrates CFD flow field simulation and finite element structure simulation to a high degree. The CFD simulation technology has the advantages of low cost and short design period, and overcomes the disadvantages of the traditional fluid dynamic test to a great extent, so that the CFD simulation technology is widely applied to the field of design of aeroengine impeller machines.
The core components of an aircraft engine include compressor wheels and turbine wheels of each stage, with turbine blades being critical components that determine engine performance and life. The design process of the turbine blade comprises a plurality of links such as aerodynamic performance, heat transfer performance, structural strength and the like, key parameters of the blade structure can be repeatedly modified in a plurality of iterations of the design process, the model also needs to be frequently re-created, and accordingly, a CFD simulation flow field model is required to be established aiming at the modified blade model.
When the CFD flow field and the structure simulation are carried out on the impeller machine, as all blades are identical in the whole circumference, the angle offset exists only in the circumferential direction, and the geometric structure has the periodic symmetry characteristic. Meanwhile, the upstream incoming flow condition is generally uniform axial airflow and has axisymmetric characteristics, so that the flow field structure, the flow variables such as temperature and pressure, and the structural parameters such as stress and deformation of the impeller machine can also be considered to have periodic symmetry.
In order to reduce the consumption of computing resources, improve the computing speed and quickly obtain the simulation result, a single-channel blade computing domain after periodic segmentation is generally adopted to replace a whole-cycle blade computing domain when CFD simulation is carried out. In creating a single channel blade computation domain with periodic symmetry, the creation of a periodic split surface is a critical step, which is also the most time-consuming step of the design process. The current common method for creating the periodic dividing surface generally comprises the following steps:
(1) A simple plane is adopted to replace a curved surface to be used as a periodic dividing surface;
(2) Manually creating an inner curved surface curve, and then extending the surface normal;
(3) Manually creating surface curves at a plurality of radial positions, and constructing a curved surface by utilizing the function of the curve group;
the above method of creating periodic split surfaces generally creates a slow speed or a poor split effect, requiring repeated adjustments by the designer. For example, a segmented surface with unsuitable curved surface parameters may be too close to an adjacent blade, and may intersect with structures such as blade body and rounding, so that the segmented computational domain does not have periodic symmetry characteristics and cannot be used in the CFD simulation process.
Disclosure of Invention
Aiming at the technical problems in the background technology, the application provides a rapid construction method of a single-channel fluid calculation domain of an impeller machine.
The application is realized by the following technical scheme:
the application provides a rapid construction method of a single-channel fluid calculation domain of an impeller machine, which comprises the following steps:
designating critical surfaces including an inlet surface, an outlet surface, an upper end wall, a lower end wall, and a single vane surface of the turbomachine fluid domain;
creating a whole-cycle impeller fluid domain according to the appointed key surface;
constructing a middle surface of the blade, and extending the middle surface of the blade facing the inlet surface, the outlet surface, the upper end wall and the lower end wall to obtain a reference dividing surface;
the reference dividing plane is rotated forwards around a rotating shaft by an angle of 0.5 alpha to generate a first periodic dividing plane p1, and the reference dividing plane is rotated reversely around the rotating shaft by an angle of 0.5 alpha to generate a second periodic dividing plane p2; wherein the alpha angle is a single-channel periodic angle;
and dividing the whole-cycle impeller fluid domain G by adopting the first cycle dividing plane p1 and the second cycle dividing plane p2 to obtain a single-channel blade calculation domain.
As a further illustration of the present application, said creating a full-perimeter impeller fluid field from said designated critical surface comprises:
constructing a whole-week computing domain Z by utilizing the key surface;
and carrying out Boolean difference operation on the whole-cycle calculation domain Z and the impeller structure solid domain Y to obtain a whole-cycle impeller fluid domain G.
As a further illustration of the application, the build blade midsurface comprises:
generating sampling points according to a certain spatial resolution in a meridian plane of the impeller machine;
rotating around a rotating shaft by each sampling point, creating a space arc, and calculating the intersection points of all the space arcs and the designated blade surface;
and constructing a curved surface by using grids formed by all the intersection points, and generating the middle surface of the blade.
As a further illustration of the application, when calculating the intersection of all of the spatial arcs with a given blade surface, if there are two intersections of the same arc with the blade surface, the average is taken.
As a further explanation of the present application, the mode of extending the middle surface of the blade is selected to be curvature extending or the mode of specifying the tangential surface, so that the extended curved surface can completely divide the whole circumference impeller fluid field G.
Compared with the prior art, the application has the following advantages:
the period division surface constructed by the method has the same distance with the adjacent blades, can not intersect with the complex blade surfaces, does not need user intervention, does not need complex curved surface parameter adjustment, and can quickly generate the period division surface meeting the requirements.
Drawings
FIG. 1 is a flow chart of a method for quickly constructing a single-channel fluid computational domain of an impeller machine according to an embodiment of the present application;
FIG. 2 is a full-circle computing field Z provided by an embodiment of the present application;
FIG. 3 is a graph of a set of curves for constructing a mid-blade surface provided by an embodiment of the present application;
FIG. 4 is a reference parting plane constructed from a mid-plane of a blade provided in an embodiment of the application;
FIG. 5 shows first and second periodic split surfaces p1 and p2 according to an embodiment of the present application;
fig. 6 is a single-channel blade calculation domain provided by an embodiment of the present application.
Description of the embodiments
The following description of the embodiments of the present application will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present application, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the application without making any inventive effort, are intended to be within the scope of the application.
In creating a single channel blade computation domain with periodic symmetry, the creation of a periodic split surface is a critical step, which is also the most time-consuming step of the design process. The current common method for creating the periodic dividing surface generally comprises the following steps:
(1) A simple plane is adopted to replace a curved surface to be used as a periodic dividing surface;
(2) Manually creating an inner curved surface curve, and then extending the surface normal;
(3) Manually creating surface curves at a plurality of radial positions, and constructing a curved surface by utilizing the function of the curve group;
the above method of creating periodic split surfaces generally creates a slow speed or a poor split effect, requiring repeated adjustments by the designer. For example, a segmented surface with unsuitable curved surface parameters may be too close to an adjacent blade, and may intersect with structures such as blade body and rounding, so that the segmented computational domain does not have periodic symmetry characteristics and cannot be used in the CFD simulation process.
In view of the above technical problems, the present application provides a method for quickly constructing a single-channel fluid calculation domain of an impeller machine, as shown in fig. 1, the method includes the following steps:
step 1: the key face is specified. The following critical surfaces are selected, including the inlet face, outlet face, upper end wall, lower end wall, and single vane surface of the turbomachine fluid domain.
Step 2: creating a full-circumference impeller fluid field G. The method specifically comprises the following steps:
step 201: constructing a whole-cycle calculation domain Z by using the designated key surface;
step 202: and carrying out Boolean difference operation on the whole-cycle calculation domain Z and the impeller structure solid domain Y to obtain a whole-cycle impeller fluid domain G.
Step 3: the blade mid-plane is constructed. The method specifically comprises the following steps:
step 301: generating sampling points according to a certain spatial resolution in a meridian plane of the impeller machine; the spatial resolution thereof may be, for example, 3x3, 5x5,7x7, etc.
Step 302: rotating around the rotating shaft by each sampling point, creating a space arc, and calculating the intersection points of all the space arcs and the designated blade surface;
when calculating the intersection points of all the spatial circular arcs and the designated blade surface, if two intersection points exist between the same circular arc and the blade surface, the average value is taken.
Step 303: and constructing a curved surface by using grids formed by all the intersection points, and generating the middle surface of the blade.
Step 4: a reference segmentation plane is created. Extending the surfaces facing the inlet surface, the outlet surface, the upper end wall and the lower end wall of the blade to obtain a reference dividing surface;
the mode of extending the middle surface of the blade selects the mode of curvature extension or designating the tangential surface, so that the extended curved surface can be ensured to completely divide the whole circumference impeller fluid domain G.
Step 5: a first period split plane p1 and a second period split plane p2 are created. Forward rotating the reference dividing plane around the rotation axis by an angle of 0.5 alpha to generate a first periodic dividing plane p1; reversely rotating the reference dividing plane around the rotating shaft by an angle of 0.5 alpha to generate a second periodic dividing plane p2; where the angle α is the periodic angle of a single channel.
Step 6: a single channel blade computation domain is generated. And dividing the whole Zhou Shelun fluid domain G by adopting the first periodic dividing plane p1 and the second periodic dividing plane p2 to obtain a single-channel blade calculation domain.
According to the method, a method based on meridian plane sampling points is adopted, the middle plane of the blade is rapidly generated, and a periodic segmentation plane capable of completely segmenting the whole circumference calculation domain is obtained through different curved surface extension modes.
According to the method, the key surface is designated, the middle surface of the blade is automatically and rapidly created, and the periodic segmentation surface of the computation domain is created according to the key surface, so that the whole periphery of the impeller machinery fluid domain is segmented, and finally, the single-channel blade fluid computation domain with periodic symmetry is obtained, and is used for the follow-up CFD flow field and structure simulation process.
It should be noted that in this document, terms such as "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus.
Although embodiments of the present application have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made therein without departing from the principles and spirit of the application, the scope of which is defined in the appended claims and their equivalents.
Claims (5)
1. A method for quickly constructing a single-channel fluid calculation domain of an impeller machine, which is characterized by comprising the following steps:
designating critical surfaces including an inlet surface, an outlet surface, an upper end wall, a lower end wall, and a single vane surface of the turbomachine fluid domain;
creating a whole-cycle impeller fluid domain according to the appointed key surface;
constructing a middle surface of the blade, and extending the middle surface of the blade facing the inlet surface, the outlet surface, the upper end wall and the lower end wall to obtain a reference dividing surface;
the reference dividing plane is rotated around a rotating shaft in the forward direction by an angle of 0.5 alpha to generate a first periodic dividing plane; reversely rotating the reference dividing plane around the rotating shaft by an angle of 0.5 alpha to generate a second periodic dividing plane; wherein the alpha angle is a single-channel periodic angle;
and dividing the whole-cycle impeller fluid domain by adopting the first cycle dividing surface and the second cycle dividing surface to obtain a single-channel blade calculation domain.
2. The method of claim 1, wherein creating a full-perimeter impeller fluid domain from the specified key surface comprises:
constructing a whole-week computing domain by utilizing the key surface;
and carrying out Boolean difference operation on the whole-cycle calculation domain and the impeller structure solid domain to obtain the whole-cycle impeller fluid domain.
3. The method of claim 1, wherein said constructing a blade mid-plane comprises:
generating sampling points according to a certain spatial resolution in a meridian plane of the impeller machine;
rotating around a rotating shaft by each sampling point, creating a space arc, and calculating the intersection points of all the space arcs and the designated blade surface;
and constructing a curved surface by using grids formed by all the intersection points, and generating the middle surface of the blade.
4. A method of quickly constructing a single channel fluid computation domain of a turbomachine according to claim 3, characterized in that, when calculating the intersection of all the spatial arcs with a given blade surface, the average is taken if there are two intersections of the same arc with the blade surface.
5. The method for quickly constructing a single-channel fluid computing domain of an impeller machine according to claim 1, wherein the mode of extending the middle surface of the blade selects a mode of curvature extension or a designated tangent plane, so that the extended curved surface can completely divide the whole-cycle impeller fluid domain.
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