CN114282323B - Flow distribution prediction method for turbine blade laminate cooling structure - Google Patents
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Abstract
The invention discloses a flow distribution prediction method of a turbine blade laminate cooling structure, relates to the technical field of aeroengine design, and solves the problems that an existing laminate structure flow evaluation method is complex in calculation, time-consuming and difficult to simplify into a low-dimensional network structure; according to the invention, the main flow field, the cavity/partition scheme and the cooling structure parameters of the turbine blade are used as inputs, and the flow evaluation of the structure can be completed within a few seconds. The output result is the flow of each exhaust film hole, the flow of the impact hole and the crossflow in the laminate. The invention uses the flat model to test, the average relative error of the flow is controlled within 10%, and the excellent prediction effect is obtained. The invention has very high efficiency of predicting the flow of the laminate, and only a few seconds are needed for obtaining the flow distribution prediction result.
Description
Technical Field
The invention relates to the technical field of aeroengine design, in particular to a flow distribution prediction method of a turbine blade laminate cooling structure
Background
In the design process of an aeroengine, increasing the turbine inlet gas temperature is an important way to improve the performance of the aeroengine. Under the same engine size, the thrust can be improved by about 10% when the temperature of the gas at the inlet of the turbine is increased by 55 ℃. Currently, the gas temperature at the turbine inlet of the world advanced military aircraft engine can reach 1970K, and the temperature is not bearable by the blade materials. And the increasing speed of the temperature of the gas at the inlet of the turbine is far higher than that of the temperature resistant degree of the material. Therefore, there is a need to design advanced cooling structures to accommodate the ever increasing turbine front temperature.
At present, the current research situation and development trend of the turbine cooling structure at home and abroad mainly aims at designing the laminated turbine cooling blade. According to calculation, the cooling efficiency can be improved by 20-30% by using the double-wall turbine blade, and the temperature before the turbine is improved by 222-333 ℃. We are developing high performance five-generation blades, even the more advanced next generation blades, double-walled turbine blades are fundamental structures with significant potential.
The amount of cold air flow is an important factor affecting the cooling effect of the laminate structure. However, current general methods for flow assessment of double-walled turbine blades using numerical methods can be categorized into CFD calculations and fluid network methods. The double-wall turbine blade is complex in general structure, and a large amount of time is consumed for research by using a CFD calculation method; fluid network methods generally calculate faster, but laminate structures with complex internal arrangements tend to be difficult to reduce to low-dimensional network structures. On the other hand, artificial intelligence algorithms have been widely used in the field of aeroengine design and have achieved great success. Therefore, the flow distribution prediction model of the large-area laminate cooling structure is established by using an artificial intelligent algorithm. The method solves the problem of rapid prediction of the flow distribution of the laminate structure.
Disclosure of Invention
The invention provides a flow distribution prediction method of a turbine blade laminate cooling structure, which aims to solve the problems that an existing laminate structure flow evaluation method is complex in calculation, consumes time and is difficult to simplify into a low-dimensional network structure.
A flow distribution prediction method of a turbine blade laminate cooling structure aims at a double-layer-wall blade laminate cooling structure, and solves the problem of flow distribution prediction of a multi-row air film hole and an impact hole into local flow prediction and integral flow correction; the prediction method is realized by a local flow prediction module and a whole flow correction module; the specific implementation steps are as follows:
Step one, taking the main flow pressure field of a turbine blade, a blade cavity/partition scheme and geometric parameters of a cooling structure as inputs of the local flow prediction module;
step two, setting no cross flow in the cold air interlayer of the laminate structure, wherein the flow of all air films/impact holes depends on the geometric parameters of the local cooling structure and the local internal and external pressure difference of the laminate;
the local flow prediction module splits the laminate structure into a plurality of local units, and for each local unit, the diameter of the air film hole and the pressure difference between the inside and the outside of the laminate structure are input as the local flow prediction module, and the flow of the air film/impact hole without cross flow is output as the local flow prediction module;
training BP neural network, and establishing the association between the input and output of the local flow prediction module; inputting the output flow of the cross flow-free air film/impact hole to the integral flow correction module;
Step three, the local flow prediction module takes the flow of the main flow pressure field of the turbine blade, the blade cavity/partition scheme, the geometric parameters of the cooling structure and the non-cross flow air film/impact hole as the input of the integral flow correction module;
analyzing the data input in the step three by the integral flow correction module, establishing a flow transportation model in the cold air interlayer of the laminate structure, and dividing the flow transportation model into a free cross flow layer and a sectional correction layer;
Extracting a part of data of the flow rate of the impact holes in the free cross flow layer, carrying out weighted average according to the diameters of the impact holes, and distributing the data to each impact hole;
And further correcting the exhaust film/impingement hole flow rate of each hole in the sectional correction layer according to the cross flow intensity and the flow characteristic of the cold air, and outputting the air film Kong Paileng air flow rate, the impingement hole exhaust cold air flow rate and the cold air flow direction and intensity of different areas in the laminate.
The invention has the beneficial effects that: according to the invention, the main flow field, the cavity/partition scheme and the cooling structure parameters of the turbine blade are used as inputs, and the flow evaluation of the structure can be completed within a few seconds. The output result is the flow of each exhaust film hole, the flow of the impact hole and the crossflow in the laminate.
Compared with the CFD calculation method for predicting the cool air distribution of the cooling structure of the turbine blade laminate at present, the invention has the following advantages:
(1) The invention uses the flat model to test, the average relative error of the flow is controlled within 10%, and the excellent prediction effect is obtained.
(2) The invention has very high efficiency of predicting the flow of the laminate, and only a few seconds are needed for obtaining the flow distribution prediction result.
Drawings
FIG. 1 is a schematic diagram of a flow distribution prediction method for a turbine blade laminate cooling structure in accordance with the present invention;
FIG. 2 is a schematic diagram of a cold air sandwich structure;
FIG. 3 is a graph showing the effect of non-uniform external pressure conditions on a laminate structure;
FIG. 4 is a topological structure diagram of a cold air transportation model.
Detailed Description
In the first embodiment, a flow distribution prediction method of a turbine blade laminate cooling structure is described with reference to fig. 1 to 4, and the flow distribution prediction problem of a multi-row gas film hole and an impingement hole is disassembled into two parts, namely, local flow prediction and overall flow correction, for a double-wall blade laminate cooling structure. The method comprises the following specific steps:
Step one, taking the main flow pressure field of the turbine blade, the blade cavity/partition scheme and the geometric parameters of the cooling structure as the input of the local flow prediction module. The main flow pressure field of the turbine blade can be obtained by carrying out simulation calculation on the solid blade without the cooling structure, and the blade cavity/partition scheme is provided by blade designers. In general, the vane cavity/partition scheme needs to consider various factors such as vane strength, vane outer surface pressure distribution and the like, and is complex. While the vane chambered/partitioned embodiment has no impact on the flow distribution predictions described in this invention, it is directly used herein as a known quantity input and will not be discussed in any great detail.
And secondly, the local flow prediction module assumes that no cross flow exists in the cold air interlayer of the laminate, and the flow of all air films/impact holes only depends on the geometric parameters of a local cooling structure and the local internal and external pressure difference of the laminate. Taking the variables such as the diameter of the air film hole, the pressure difference between the inside and the outside of the laminate structure and the like as input, taking the flow of the air film/impact hole when the cold air interlayer of the laminate structure is crossflow as output, training a BP neural network, and establishing the association between the input and the output of the local flow prediction module; inputting the output flow of the cross flow-free air film/impact hole to the integral flow correction module;
and step three, merging the integral input turbine blade main flow pressure field, the blade cavity/partition scheme, the geometric parameters of the cooling structure and the flow of the air film/impact hole under the condition of no cross flow output by the local flow prediction module, and taking the merged air film/impact hole as the input of the integral flow correction module.
And step four, the whole flow correction module operates according to the received data. And according to theoretical analysis results, splitting the flow transport model in the cold air interlayer of the integral laminate structure into a free cross flow layer and a sectional correction layer. Extracting a part of the flow of the impact hole in the free cross flow layer, and carrying out weighted average according to the diameter of the impact hole; the exhaust film/impingement hole flow rate of each hole is further modified in the segment modification layer according to the intensity of the cross flow and the flow characteristics of the cold air.
When the maximum intensity of the cross flow between the laminates is equal to the local impact hole flow, further correcting the hole discharge; the specific process is as follows:
setting the flow resistance in the free cross flow layer to be equal to 0, wherein the free cross flow layer does not influence the flow of the air film hole; the total flow of the free cross flow layer flows in from each row of impact holes, and the inflow depends on the flow and the diameter ratio of the local air film holes;
The total flow of the free cross flow layer is obtained after the inflow of each hole row is accumulated, the total flow is set to evenly flow through each row of impact holes, and the total flow of the free cross flow layer is evenly distributed according to the residual area of the local impact holes, so that the correction of the free cross flow layer is realized; and finding out the maximum position of the cross flow in the laminate according to the output result of the free cross flow layer, and determining the range of different areas of the sectional correction layer.
In this embodiment, 0to 90% of the flow rate of the impingement holes is extracted from the free-flow layer, specifically: the ratio of extraction depends on the ratio k of the local impingement hole diameter to the film hole diameter;
When k is more than or equal to 1 and less than or equal to 2, extracting the flow of 90 percent X (k-1) 0.5 of the impact hole;
when k >2, 90% of the flow of the impingement holes is extracted.
A second embodiment is described with reference to fig. 1 to 4, which are examples of a flow distribution prediction method for a turbine blade laminate cooling structure according to the first embodiment. In this embodiment: to achieve the prediction of the flow distribution of the laminate structure, first the inputs and outputs of the program are determined. For the application scene of the invention, the input of the program is the geometric structure parameter and boundary condition of the calculation model, and the output is the flow distribution result of the laminate whole. The composition of the whole system is shown in figure 1.
1. A local flow prediction module;
and verifying the influence of different geometric parameters on the flow through numerical calculation. Preliminary results may prove the following conclusions:
(1) The influence of the air film hole angle on the local flow is negligible;
(2) When the diameter of the impact hole is larger than that of the air film hole, the diameter of the air film hole is a main factor for determining local flow, and the diameter of the impact hole is a secondary factor.
(3) The pressure difference between the inside and the outside of the laminate structure is the final decisive factor influencing the flow of the local structure.
According to the conclusion, three variables of internal and external pressure differences of the local structure, the diameter of the air film hole and the diameter ratio of the impact hole to the air film hole are preliminarily selected to construct a training data set of the BP neural network. The variable number varies from 16 to 3 according to the importance of the variable, and 448 sets of data are summed (384 sets of data are calculated and counted at present). The specific scheme of the training dataset is shown in the following table.
And counting the flow of the data sets, and establishing the data sets. And then training a neural network model, and establishing the mapping from the data set variables such as internal and external pressure differences, the diameter of the air film holes and the like to the local flow.
2. Integral flow correction module
And combining the input of the whole program and the output of the local flow prediction module to be used as the input of the whole flow correction module. The module performs a large number of flow heat exchange analyses on the hole row structure of the large-area laminate. Finally, according to different flow forms, the flow in the laminate is divided into two layers: impact zone a near the target surface and zone B near the intake plate, as shown in fig. 2.
When the external pressure conditions of the laminate structure are not uniform, lateral flow occurs between different areas within the laminate. When the pressure outside the laminate structure was monotonically varied, the lateral flow of zones a and B was analyzed as shown in fig. 3. And dividing the area A into a development section, a stabilization section and a reflux section according to the transportation form of cooling gas in the laminate.
And (3) establishing a cold air transportation model in the laminate according to the analysis, abstracting a region B of the laminar flow structure into a free cross flow layer of the flow transportation model, abstracting a region A into a sectional correction layer, wherein the topological structure of the sectional correction layer is shown in figure 4.
And then, correcting the discharge quantity of each hole by combining physical analysis based on the flow transport model to obtain a final result. The specific correction method comprises the following steps:
(1) According to the physical and numerical analysis results, the cross flow hardly affects the flow of the air film hole, so that the flow of the impact hole is uniformly distributed, and the flow resistance between the laminates is far smaller than that of the air film hole and the impact hole.
Therefore, the flow resistance in the free cross flow layer is equal to 0, and the free cross flow layer does not influence the air film hole flow. The total flow of the free cross-flow layer is flowed in by each row of impingement holes, and the inflow is dependent on the local air film hole flow and the diameter ratio k. The total flow of the free cross flow layer is obtained by summing the inflow of each row of holes, assuming that these flows evenly flow through each row of impingement holes. And uniformly distributing the total flow of the free cross flow layer according to the residual area of the local impact hole (the area of the local impact hole-the area of the local air film hole), so as to obtain the correction result of the free cross flow layer.
(2) When the maximum intensity of the cross flow between the laminates is equal to the local impingement hole flow, further correction of the hole discharge is needed. And according to the output result of the free cross flow layer, the maximum cross flow position in the laminate can be found, so that the range of different areas of the sectional correction layer is determined.
The area in front of the maximum position of the cross flow is a development section, and the transverse flow is gradually enhanced; the area behind the maximum position of the cross flow is a declining section, and the cross flow is gradually weakened; the decay section can be equally divided into a stabilization section and a reflux section. And respectively extracting physical characteristic quantities in the three areas, and correcting the flow of the air film hole and the impact hole. The specific correction method comprises the following steps:
For the impact/air film flow of the development section, the flow of the impact hole is weighted and averaged further by referring to a method of a free cross flow layer, and the flow of the air film hole with the lowest internal-external pressure difference is halved; the declining section cross flow uniformly flows out through the air film holes, takes one third of the maximum cross flow intensity, and is distributed to each air film hole according to the weighted average of the air film hole diameters;
The steady-stage impingement orifice flow is not corrected. The flow rate of the impingement holes in the return section decreases and the closer to the end of the laminate structure, the greater the proportion of impingement hole flow rate decrease (quadratic distribution). The sum of the reduced flow rates of the impingement holes of the recirculation zone is equal to one third of the maximum cross flow intensity.
The technical features of the above-described embodiments may be arbitrarily combined, and all possible combinations of the technical features in the above-described embodiments are not described for brevity of description, however, as long as there is no contradiction between the combinations of the technical features, they should be considered as the scope of the description.
The above examples illustrate only a few embodiments of the invention, which are described in detail and are not to be construed as limiting the scope of the invention. It should be noted that it will be apparent to those skilled in the art that several variations and modifications can be made without departing from the spirit of the invention, which are all within the scope of the invention. Accordingly, the scope of protection of the present invention is to be determined by the appended claims.
Claims (5)
1. A flow distribution prediction method of a turbine blade laminate cooling structure is characterized by comprising the following steps: the prediction method is realized by a local flow prediction module and a whole flow correction module; the specific implementation steps are as follows:
Step one, taking the main flow pressure field of a turbine blade, a blade cavity/partition scheme and geometric parameters of a cooling structure as inputs of the local flow prediction module;
step two, setting no cross flow in the cold air interlayer of the laminate structure, wherein the flow of all air films/impact holes depends on the geometric parameters of the local cooling structure and the local internal and external pressure difference of the laminate;
the local flow prediction module splits the laminate structure into a plurality of local units, and for each local unit, the diameter of the air film hole and the pressure difference between the inside and the outside of the laminate structure are input as the local flow prediction module, and the flow of the air film/impact hole without cross flow is output as the local flow prediction module;
training BP neural network, and establishing the association between the input and output of the local flow prediction module; inputting the output flow of the cross flow-free air film/impact hole to the integral flow correction module;
Step three, the local flow prediction module takes the flow of the main flow pressure field of the turbine blade, the blade cavity/partition scheme, the geometric parameters of the cooling structure and the non-cross flow air film/impact hole as the input of the integral flow correction module;
analyzing the data input in the step three by the integral flow correction module, establishing a flow transportation model in the cold air interlayer of the laminate structure, and dividing the flow transportation model into a free cross flow layer and a sectional correction layer;
Extracting a part of data of the flow rate of the impact holes in the free cross flow layer, carrying out weighted average according to the diameters of the impact holes, and distributing the data to each impact hole;
And further correcting the exhaust film/impingement hole flow rate of each hole in the sectional correction layer according to the cross flow intensity and the flow characteristic of the cold air, and outputting the air film Kong Paileng air flow rate, the impingement hole exhaust cold air flow rate and the cold air flow direction and intensity of different areas in the laminate.
2. A method of predicting flow distribution for a turbine blade laminate cooling structure in accordance with claim 1, wherein: in the first step, the main flow pressure field of the turbine blade is obtained by performing simulation calculation on a solid blade without a cooling structure, and the blade cavity division/partition scheme is provided by a blade designer.
3. A method of predicting flow distribution for a turbine blade laminate cooling structure in accordance with claim 1, wherein: in the fourth step, 0 to 90 percent of the flow of the impact hole is extracted from the free cross flow layer,
The method comprises the following steps: the ratio of extraction depends on the ratio k of the local impingement hole diameter to the film hole diameter;
When k is more than or equal to 1 and less than or equal to 2, extracting the flow of 90 percent X (k-1) 0.5 of the impact hole;
when k >2, 90% of the flow of the impingement holes is extracted.
4. A method of predicting flow distribution for a turbine blade laminate cooling structure in accordance with claim 1, wherein: step four, when the maximum intensity of the cross flow between the laminates is equal to the local impact hole flow, further correcting the discharge of each hole; the specific process is as follows:
setting the flow resistance in the free cross flow layer to be equal to 0, wherein the free cross flow layer does not influence the flow of the air film hole; the total flow of the free cross flow layer flows in from each row of impact holes, and the inflow depends on the flow and the diameter ratio of the local air film holes;
The total flow of the free cross flow layer is obtained after the inflow of each hole row is accumulated, the total flow is set to evenly flow through each row of impact holes, and the total flow of the free cross flow layer is evenly distributed according to the residual area of the local impact holes, so that the correction of the free cross flow layer is realized; and finding out the maximum position of the cross flow in the laminate according to the output result of the free cross flow layer, and determining the range of different areas of the sectional correction layer.
5. A method of predicting flow distribution for a turbine blade laminate cooling structure in accordance with claim 4, wherein:
The area in front of the maximum position of the cross flow is a development section, and the transverse flow is gradually enhanced; the area behind the maximum position of the cross flow is a declining section, and the cross flow is gradually weakened; the decay section can be equally divided into a stabilization section and a reflux section; respectively extracting physical characteristic quantities in the development section, the stabilization section and the reflux section, and correcting the flow of the air film hole and the impact hole; the specific correction method comprises the following steps:
For the impact/air film flow of the development section, the flow of the impact hole is weighted and averaged further by referring to a method of a free cross flow layer, and the flow of the air film hole with the lowest internal-external pressure difference is halved; the declining section cross flow uniformly flows out through the air film holes, takes one third of the maximum cross flow intensity, and is distributed to each air film hole according to the weighted average of the air film hole diameters;
The flow of the impact hole of the stable section is not corrected; the flow rate of the impact holes of the reflux section is reduced, and the closer to the tail end of the laminate structure, the greater the proportion of the flow rate of the impact holes is reduced; the sum of the reduced flow rates of the impingement holes of the return section is equal to one third of the maximum cross flow intensity.
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