CN113530851A - Simulation method for high-low pressure stage compressor of two-stage supercharging system - Google Patents
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Abstract
The invention discloses a simulation method of a high-low pressure stage compressor of a two-stage supercharging system, which has the advantages of simple steps and reasonable setting conditions; in actual work, the high-pressure stage compressor and the low-pressure stage compressor of the two-stage supercharging system have mutual influence, the method can accurately simulate the influence of coupling distortion of a non-uniform flow field at the outlet of the low-pressure stage compressor and an interstage bent pipeline on the performance of the high-pressure stage compressor, realize quantitative and qualitative analysis on the influence, and guide improvement on how to weaken the influence based on an analysis result; further improving the performance of the engine matched with the two-stage supercharging system.
Description
Technical Field
The invention belongs to the field of simulation of impeller mechanical supercharging technology, and particularly relates to a simulation method of a high-low pressure stage compressor of a two-stage supercharging system.
Background
Compared with a single-stage supercharging system, the two-stage supercharging system promotes the development of the engine technology. Nowadays, the research on the condition of uniform air intake of a high-low pressure stage compressor in a two-stage supercharging system is mostly based on the condition of uniform air intake, namely, the inlet of the low-pressure stage compressor adopts uniform air intake parameters. However, in the actual working process, the conventional uniform air inlet mode has obvious limitation.
In a high-pressure stage compressor and a low-pressure stage compressor of a two-stage supercharging system, because of the influence of factors such as the whole structure, space, weight and the like, a complex bending pipeline is required to be adopted between the two stages of compressors, and the phenomenon that the inlet section of the high-pressure stage compressor generates distorted airflow is caused by the special geometric shape in the air inlet pipeline; meanwhile, the flow at the outlet of the low-pressure compressor has the characteristic of uneven distribution of pneumatic parameters, and the characteristic is coupled with flow distortion caused by an interstage bent pipeline, so that the flow condition at the inlet of the high-pressure compressor is more complicated, and the performance and the stable working range of the high-pressure compressor are obviously influenced. Therefore, the research on the influence of the complex flow conditions on the performance of the high-pressure stage compressor is carried out aiming at the two-stage supercharging system, and the method has important significance for improving the performance of the engine matched with the two-stage supercharging system.
How to carry out quantitative and qualitative analysis on the influence and further guide realization and weaken the influence becomes a problem to be solved urgently by practitioners of the same profession.
Disclosure of Invention
In view of the defects of the prior art, the invention provides a simulation method of a high-low pressure compressor of a two-stage supercharging system, which can simulate the influence of a non-uniform flow field at the outlet of the low-pressure compressor and a compressor interstage zigzag pipeline on the performance of the high-pressure compressor, and further guide the realization of weakening the influence.
In order to achieve the purpose, the invention adopts the technical scheme that:
the embodiment of the invention provides a simulation method of a high-low pressure stage compressor of a two-stage supercharging system, which comprises the following steps:
s10, constructing simulation models of the high-low pressure stage compressor and the interstage pipeline in the two-stage supercharging system, setting basic calculation boundary conditions, and checking and verifying the established simulation models;
s20, after the simulation model is verified to be qualified, three-dimensional numerical calculation is carried out on the low-pressure stage compressor through CFD software, and pressure distribution data of a non-uniform flow field at the outlet of the low-pressure stage compressor are obtained;
s30, setting uniform air inlet conditions for an inlet of the high-pressure stage air compressor, and performing three-dimensional numerical calculation on the high-pressure stage air compressor through CFD software to obtain a simulation result of the high-pressure stage air compressor under the uniform air inlet conditions;
s40, setting pressure distribution data of the uneven flow field at the outlet of the low-pressure stage compressor in the step S20 on the inlet of the high-pressure stage compressor, and performing three-dimensional numerical calculation on the high-pressure stage compressor through CFD software to obtain a simulation result of the high-pressure stage compressor under the uneven air inlet condition;
s50, comparing the simulation result of the high-pressure stage compressor under the uniform air inlet condition in the step S30 with the simulation result of the high-pressure stage compressor under the non-uniform air inlet condition in the step S40 to obtain a comparative analysis result of the high-pressure stage compressor under the uniform air inlet condition and the non-uniform air inlet condition, and obtaining the influence of the complex flow condition on the performance of the high-pressure stage compressor.
Further, still include:
and S60, adding a corresponding flow guide grid structure at the inlet of the high-pressure stage compressor according to the comparative analysis result in the step S50, and improving the inlet flow field of the compressor.
Further, in step S10, setting a basic calculation boundary condition includes:
the inlet of the low-pressure stage compressor is set to be in an atmospheric condition, and the outlet surface is set to be in static pressure;
the inlet of the high-pressure stage compressor is provided with the total pressure average value of the outlet of the low-pressure stage compressor, and the outlet is provided with flow to ensure that the flow of the high-pressure stage compressor and the flow of the low-pressure stage compressor are consistent;
the fixed wall surface is provided with a heat insulation non-slip boundary, corresponding rotating speeds of the rotor blade and the hub are set, and the rest wall surfaces are static wall surfaces.
Further, the comparing and analyzing result in the step S50 includes:
the efficiency characteristic change data of the high-pressure compressor under the uniform air inlet condition and the non-uniform air inlet condition;
and the internal entropy increase distribution data of the high-pressure compressor stage impeller under the uniform air inlet condition and the non-uniform air inlet condition.
Further, the designing and optimizing of the air fence structure in the step S60 includes:
the design of the flow guide grid structure is as follows: designing a T-shaped flow deflector in a local high static pressure area corresponding to the bent pipeline, performing simulation analysis on an outlet flow field of the interstage pipeline by using CFD (computational fluid dynamics) software, and comparing an obtained simulation result with a simulation result without adding a flow guide grid structure;
optimizing the structure of the flow guide grid: according to the comparison of simulation results obtained in the design of the flow guide grid structure, the flow guide grid structure is optimized, and the number of the fins is increased; and performing simulation analysis on the outlet flow field of the interstage pipeline by using CFD software, and comparing the obtained simulation result with the simulation result without adding a flow guide grid structure.
Compared with the prior art, the invention has the following beneficial effects:
the simulation method of the high-low pressure stage compressor of the two-stage supercharging system provided by the embodiment of the invention has the advantages of simpler steps and reasonable setting conditions; in actual work, the high-pressure stage compressor and the low-pressure stage compressor of the two-stage supercharging system have mutual influence, the method can accurately simulate the influence of coupling distortion of a non-uniform flow field at the outlet of the low-pressure stage compressor and an interstage bent pipeline on the performance of the high-pressure stage compressor, realize quantitative and qualitative analysis on the influence, guide improvement on the basis of an analysis result to weaken the influence, and further improve the performance of an engine matched with the two-stage supercharging system.
Drawings
Fig. 1 is a flowchart of a simulation method of a high-low pressure stage compressor of a two-stage supercharging system according to an embodiment of the present invention;
fig. 2 is a high-low pressure stage compressor model of a two-stage supercharging system according to an embodiment of the present invention;
FIG. 3 is a schematic diagram of establishing a compressor grid model according to an embodiment of the present invention;
fig. 4a is a comparison graph of pressure ratio characteristic curves of a simulation result and an actual experiment result of the gas compressor provided by the embodiment of the invention;
FIG. 4b is a graph comparing efficiency characteristics of simulation results and actual experimental results of the compressor provided by the embodiment of the invention;
fig. 5 is pressure distribution data of a non-uniform flow field at an outlet of a low-pressure stage compressor according to an embodiment of the present invention;
FIG. 6 is a comparison graph of efficiency characteristic curves of a high-pressure stage compressor under uniform air intake and non-uniform air intake conditions, provided by an embodiment of the invention;
FIG. 7 is an entropy increase cloud diagram at 90% of the blade height of a high-pressure stage compressor impeller under uniform air intake conditions and non-uniform air intake conditions, provided by an embodiment of the invention;
FIG. 8 is a model of a flow grid structure according to an embodiment of the present invention;
fig. 9 is an optimized air guide grid model designed according to the embodiment of the present invention.
Detailed Description
In order to make the technical means, the creation characteristics, the achievement purposes and the effects of the invention easy to understand, the invention is further described with the specific embodiments.
In the description of the present invention, it should be noted that the terms "upper", "lower", "inner", "outer", "front", "rear", "both ends", "one end", "the other end", and the like indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience of description and simplicity of description, but do not indicate or imply that the referred device or element must have a specific orientation, be constructed in a specific orientation, and be operated, and thus, should not be construed as limiting the present invention. Furthermore, the terms "first" and "second" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.
In the description of the present invention, it is to be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "disposed," "connected," and the like are to be construed broadly, such as "connected," which may be fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art.
The invention provides a simulation method of a high-low pressure stage compressor of a two-stage supercharging system, which refers to fig. 1 and comprises the following steps:
s10, constructing simulation models of the high-low pressure stage compressor and the interstage pipeline in the two-stage supercharging system, setting basic calculation boundary conditions, and checking and verifying the established simulation models;
s20, after the simulation model is verified to be qualified, three-dimensional numerical calculation is carried out on the low-pressure stage compressor through CFD software, and pressure distribution data of a non-uniform flow field at the outlet of the low-pressure stage compressor are obtained;
s30, setting uniform air inlet conditions for an inlet of the high-pressure stage air compressor, and performing three-dimensional numerical calculation on the high-pressure stage air compressor through CFD software to obtain a simulation result of the high-pressure stage air compressor under the uniform air inlet conditions;
s40, setting pressure distribution data of the uneven flow field at the outlet of the low-pressure stage compressor in the step S20 on the inlet of the high-pressure stage compressor, and performing three-dimensional numerical calculation on the high-pressure stage compressor through CFD software to obtain a simulation result of the high-pressure stage compressor under the uneven air inlet condition;
s50, comparing the simulation result of the high-pressure stage compressor under the uniform air inlet condition in the step S30 with the simulation result of the high-pressure stage compressor under the non-uniform air inlet condition in the step S40 to obtain a comparative analysis result of the high-pressure stage compressor under the uniform air inlet condition and the non-uniform air inlet condition, and obtaining the influence of the complex flow condition on the performance of the high-pressure stage compressor.
In the embodiment, the simulation method has simpler steps and reasonable setting conditions; in actual work, the high-pressure stage compressor and the low-pressure stage compressor of the two-stage supercharging system have mutual influence, the method can accurately simulate the influence of coupling distortion of a non-uniform flow field at the outlet of the low-pressure stage compressor and an interstage bent pipeline on the performance of the high-pressure stage compressor, realize quantitative and qualitative analysis on the influence, guide improvement on the basis of an analysis result to weaken the influence, and further improve the performance of an engine matched with the two-stage supercharging system.
Further, the method further comprises: and S60, adding a corresponding flow guide grid structure at the inlet of the high-pressure stage compressor according to the comparative analysis result in the step S50, and improving the inlet flow field of the compressor. This effect can be eliminated and the engine performance matched to the two-stage supercharging system is improved.
The above steps are described in detail below:
in the step S10, a model of the high-low pressure stage compressor and the interstage pipeline of the two-stage supercharging system is established through three-dimensional modeling software and CFD software, and referring to fig. 2, in the embodiment of the present invention, a simulation model is established through CFD software by taking the side a high-low pressure stage compressor as an example.
In the embodiment of the invention, a grid model of a compressor impeller is established, referring to fig. 3, the embodiment is divided into 5 subareas from the inlet section of an interstage pipeline to the outlet section of a compressor volute, wherein 1 is an inlet of a bending and twisting pipeline; 2 is an impeller inlet; 3 is an impeller outlet; 4 is the diffuser outlet; 5, a volute outlet, wherein the volute outlet section is filled by adopting a grid block due to relatively uniform geometric change; for the area between the volute outlet section and the section 0, a grid block is also adopted for filling so as to carry out independent control;
setting of basic boundary conditions: in the embodiment, Perfect air and S-A turbulence models are selected, and A complete non-matching mixing plane method is adopted for an interface; the conditions for the inlet and outlet and the wall fixing surface are as follows: the inlet of the low-pressure stage compressor is set to be in an atmospheric condition, and the outlet surface is set to be in static pressure; the inlet of the high-pressure stage compressor is loaded with the total pressure average value of the outlet of the low-pressure stage compressor, and the flow rate of the flow is loaded at the outlet, so that the flow rate of the high-pressure stage compressor and the flow rate of the low-pressure stage compressor are consistent; the fixed wall surface is given with a heat insulation non-slip boundary, the corresponding rotating speeds of the rotor blade and the hub are given, and the other wall surfaces are static wall surfaces.
Checking and verifying the established simulation model: in the embodiment of the invention, CFD software is used for carrying out three-dimensional numerical calculation to obtain a simulation result which is compared with an actual experiment result, and referring to a pressure ratio characteristic curve of FIG. 4a, the curves are respectively under the conditions of 60kr/min, 70kr/min and 80kr/min, so that the maximum deviation between a flow simulation value and an experiment value is about 6 percent; referring to an efficiency characteristic curve of fig. 4b, the maximum deviation of the efficiency simulation value and the experimental value is about 5% under the conditions of 60kr/min, 70kr/min and 80kr/min respectively, which indicates that the accuracy of the simulation result of the gas compressor is higher; in this embodiment, for example, the maximum deviation between the simulated value of the flow rate and the experimental value is within 7%, and the maximum deviation between the simulated value of the efficiency and the experimental value is within 6%, and the simulation model is determined to be qualified; the threshold value of the simulation model which is qualified in verification can be adjusted according to the actual situation.
In the step S20, three-dimensional numerical calculation is performed on the low-pressure stage compressor through CFD software to obtain pressure distribution data of the uneven flow field at the outlet of the low-pressure stage compressor;
in the embodiment of the invention, the inlet of the low-pressure stage compressor is set to be in an atmospheric condition, the outlet adopts static pressure and flow boundary, and the obtained pressure distribution data of the uneven flow field at the outlet of the low-pressure stage compressor is referred to fig. 5.
In the step S30, a uniform air intake condition is set for the inlet of the high-pressure stage compressor, and three-dimensional numerical calculation is performed on the high-pressure stage compressor through CFD software to obtain a simulation result of the high-pressure stage compressor under the uniform air intake condition.
In the step S40, the pressure distribution data of the uneven flow field at the outlet of the low-pressure stage compressor in the step S20 is set at the inlet of the high-pressure stage compressor, and three-dimensional numerical calculation is performed on the high-pressure stage compressor through CFD software to obtain a simulation result of the high-pressure stage compressor under the uneven air intake condition.
In the step S50, the simulation result of the high-pressure stage compressor under the uniform air intake condition in the step S30 is compared with the simulation result of the high-pressure stage compressor under the non-uniform air intake condition in the step S40, so as to obtain a comparative analysis result of the high-pressure stage compressor under the uniform air intake condition and the non-uniform air intake condition, and the influence of the complex flow condition on the performance of the high-pressure stage compressor is explored.
The comparative analysis result of the high-pressure compressor under the uniform air inlet condition and the non-uniform air inlet condition obtained in the embodiment of the invention is as follows:
fig. 6 is a characteristic curve of the efficiency of the high-pressure stage under the uniform air intake and non-uniform air intake conditions, and it can be seen that the uniform air intake and non-uniform air intake conditions in the embodiment have little influence on the efficiency and the pressure ratio of the high-pressure stage, the difference between the efficiencies is about 0.65%, and the difference between the pressure ratios is about 0.26%. In order to study the performance of the high-pressure stage, the flow condition inside the high-pressure stage compressor needs to be studied deeply.
The embodiment of the invention continuously analyzes the internal flow of the high-pressure stage compressor: FIG. 7 is an entropy cloud diagram of a high pressure stage compressor wheel at 90% of the blade height under uniform and non-uniform inlet conditions. It can be seen that the leakage flow loss is large at 90% of the leaf height. Comparing the entropy increase distribution under the uniform air intake and non-uniform air intake conditions, the range size and intensity of the high-entropy area are very close, which shows that the loss size difference between the two is very small. However, for non-uniform inlet conditions, the high entropy region is shifted to the right in its entirety by a distance of one-half of the vane channel, indicating that non-uniform inlet conditions can affect the location of the distribution of the high entropy region upstream of the vane channel.
In step S60, in order to improve the performance of the high-pressure stage compressor, it is considered to add a corresponding structure to the inlet of the high-pressure stage compressor, so as to improve the inlet flow field of the compressor. In the embodiment of the invention, a method of adding the flow guide grid in the high static pressure area of the inlet of the high-pressure compressor is adopted, and the flow velocity of the airflow is increased and the pressure is reduced by reducing the flow cross section area of the airflow, so that the range of the high static pressure area caused by an interstage bent pipeline is effectively reduced, the circumferential asymmetric flow field of the inlet caused by the bent pipeline is improved, and the performance of the high-pressure compressor is improved.
The initially designed flow guide grid structure of the embodiment of the invention is called as a model 1, and is characterized in that T-shaped flow guide sheets are designed in a local high static pressure area corresponding to a bent pipeline, the flow guide sheets are installed at an inlet of a high-pressure stage compressor and an outlet of an interstage pipeline, CFD software is used for carrying out numerical analysis on the high-pressure stage compressor with the flow guide grid of the model 1 to obtain a simulation result, and referring to a table 1, the efficiency and the pressure ratio of the high-pressure stage compressor are improved to a certain extent after the designed flow guide grid is adopted, wherein the efficiency is improved by 1.16%, and the pressure ratio is improved by 0.53%.
TABLE 1 comparison of simulation results of high-pressure stage compressor with model 1 added and original model
| Model (model) | Efficiency improvement (%) | Pressure ratio boost (%) |
| Original high- |
0 | 0 |
| High-pressure stage compressor with |
1.16 | 0.53 |
The embodiment of the invention optimizes the flow guide grid to a certain extent by changing the number of the fins. Referring to fig. 9, model 2 and model 3 are referred to, respectively. The CFD software is used for carrying out numerical analysis on the high-pressure compressor with the models 2 and 3 of the guide grids to obtain a simulation result, referring to the table 2, the influence of the two models on the performance of the guide grids is different, the improvement effect of the model 3 on the performance of the high-pressure compressor is more obvious, and the influence of the change of the number of the guide grid grids on the performance of the high-pressure compressor is shown.
Table 2 comparison of simulation results of the high-pressure stage compressor after adding the models 2 and 3 with those of the original model
| Model (model) | Efficiency improvement (%) | Pressure ratio boost (%) |
| Original high- |
0 | 0 |
| High-pressure stage compressor with model 2 | 1.6 | 0.96 |
| High-pressure stage compressor with added |
2.81 | 1.52 |
The simulation method of the high-low pressure stage compressor of the two-stage supercharging system provided by the embodiment of the invention has the advantages of simple and convenient steps and reasonable setting conditions; in actual work, the high-pressure stage compressor and the low-pressure stage compressor of the two-stage supercharging system have mutual influence, the method can accurately simulate the influence of coupling distortion of a non-uniform flow field at the outlet of the low-pressure stage compressor and an interstage bent pipeline on the performance of the high-pressure stage compressor, realize quantitative and qualitative analysis on the influence, and guide improvement on how to weaken the influence based on an analysis result; further improving the performance of the engine matched with the two-stage supercharging system.
The foregoing shows and describes the general principles and broad features of the present invention and advantages thereof. It will be understood by those skilled in the art that the present invention is not limited to the embodiments described above, which are described in the specification and illustrated only to illustrate the principle of the present invention, but that various changes and modifications may be made therein without departing from the spirit and scope of the present invention, which fall within the scope of the invention as claimed. The scope of the invention is defined by the appended claims and equivalents thereof.
Claims (4)
1. A simulation method for a high-low pressure stage compressor of a two-stage supercharging system is characterized by comprising the following steps:
s10, constructing simulation models of the high-low pressure stage compressor and the interstage pipeline in the two-stage supercharging system, setting basic calculation boundary conditions, and checking and verifying the established simulation models;
s20, after the simulation model is verified to be qualified, three-dimensional numerical calculation is carried out on the low-pressure stage compressor through CFD software, and pressure distribution data of a non-uniform flow field at the outlet of the low-pressure stage compressor are obtained;
s30, setting uniform air inlet conditions for an inlet of the high-pressure stage air compressor, and performing three-dimensional numerical calculation on the high-pressure stage air compressor through CFD software to obtain a simulation result of the high-pressure stage air compressor under the uniform air inlet conditions;
s40, setting pressure distribution data of the uneven flow field at the outlet of the low-pressure stage compressor in the step S20 on the inlet of the high-pressure stage compressor, and performing three-dimensional numerical calculation on the high-pressure stage compressor through CFD software to obtain a simulation result of the high-pressure stage compressor under the uneven air inlet condition;
s50, comparing the simulation result of the high-pressure stage compressor under the uniform air inlet condition in the step S30 with the simulation result of the high-pressure stage compressor under the non-uniform air inlet condition in the step S40 to obtain a comparative analysis result of the high-pressure stage compressor under the uniform air inlet condition and the non-uniform air inlet condition, and obtaining the influence of the complex flow condition on the performance of the high-pressure stage compressor.
2. The simulation method of the high-low pressure stage compressor of the two-stage supercharging system according to claim 1, further comprising:
and S60, adding a corresponding flow guide grid structure at the inlet of the high-pressure stage compressor according to the comparative analysis result in the step S50, and improving the inlet flow field of the compressor.
3. The simulation method of the high-low pressure stage compressor of the two-stage supercharging system according to claim 1, wherein the comparative analysis result in the step S50 includes:
the efficiency characteristic change data of the high-pressure compressor under the uniform air inlet condition and the non-uniform air inlet condition;
and the internal entropy increase distribution data of the high-pressure compressor stage impeller under the uniform air inlet condition and the non-uniform air inlet condition.
4. The simulation method of the two-stage supercharging system high-low pressure stage compressor according to claim 2, wherein the design and optimization of the flow guide grid structure in the step S60 includes:
the design of the flow guide grid structure is as follows: designing a T-shaped flow deflector in a local high static pressure area corresponding to the bent pipeline, performing simulation analysis on an outlet flow field of the interstage pipeline by using CFD (computational fluid dynamics) software, and comparing an obtained simulation result with a simulation result without adding a flow guide grid structure;
optimizing the structure of the flow guide grid: according to the comparison of simulation results obtained in the design of the flow guide grid structure, the flow guide grid structure is optimized, and the number of the fins is increased; and performing simulation analysis on the outlet flow field of the interstage pipeline by using CFD software, and comparing the obtained simulation result with the simulation result without adding a flow guide grid structure.
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