CN117932824A - Rotary inclusion type engine combustion chamber configuration parameterization design method - Google Patents
Rotary inclusion type engine combustion chamber configuration parameterization design method Download PDFInfo
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Abstract
The invention discloses a rotary inclusion type engine combustion chamber configuration parameterization design method, which belongs to the technical field of engines and comprises the following steps: step 1, determining the geometric constitution of a combustion chamber and selecting basic parameters of quantitative description sections; step 2, calculating other parameters by using the basic parameters according to the related geometric constraint relation; step 3, calculating to obtain the volume of the combustion chamber according to each parameter of the section obtained by solving; and 4, screening out any more feasible combustion chamber parameterized design schemes by using an exhaustion method. The invention provides a parameterized design method for a combustion chamber configuration of a rotary inclusion type engine, which can realize quantitative description of the geometric configuration of the combustion chamber by using parameters and formulas by determining basic coordinate parameters of the configuration, quantitatively representing other parameters by using the basic parameters and calculating the volume of a space of the combustion chamber, and simultaneously achieve the purpose of obtaining parameterized design schemes of the combustion chamber configuration meeting various geometric constraints.
Description
Technical Field
The invention belongs to the technical field of engines, and particularly relates to a rotary inclusion type engine combustion chamber configuration parameterization design method.
Background
The combustion chamber of the engine is an important part for forming power output, fuel oil and air undergo severe chemical reaction in the combustion chamber to generate high-temperature high-pressure gas and push the piston to do work outwards, so that heat-work conversion is completed. The structural shape of the combustion chamber has important influence on the heat-power conversion process of oil-gas mixing, combustion and the like, and finally the output performance of the engine is influenced. The combustion chamber is properly designed in configuration, and the fuel oil and the air are mixed more fully, so that the combustible mixed gas can be distributed in the combustion chamber according to the design of research personnel, the combustion efficiency is improved, the fuel oil wall attachment is reduced, and the heat efficiency and the fuel oil economy are further improved. Therefore, the research and study on the new configuration of the combustion chamber is beneficial to improving the comprehensive performance of the whole machine.
Traditional development modes of combustion chamber configuration tend to have certain limitations and inefficiencies, as the combustion chamber volume is often already limited by overall metrics such as compression ratio, which is a fixed value. After the configuration profile composition is determined, the dimensions of the configuration are selected so that the corresponding volume of the combustion chamber meets the predetermined value, and the traditional mode of establishing a geometric model of the configuration of the combustion chamber through three-dimensional modeling software can only calculate the volume in a forward direction, but cannot acquire the configuration design scheme according to the corresponding volume value and other constraints; even if the combustion chamber model can be built by using a manual heuristic method and the volume of the combustion chamber model is measured by using three-dimensional modeling software to obtain a plurality of feasible configuration design schemes, the process is obviously inefficient, and a great deal of time is required to be spent on adjusting each dimension parameter of the configuration, which is not beneficial to the design and development process.
The parameterized design of the combustion chamber configuration is beneficial to accurately and quantitatively describing the combustion chamber; by combining with a computer program, a large number of combustion chamber configurations meeting various geometric constraints (particularly volume value constraints) can be rapidly screened out, which has great significance for engineering practice and scientific research; in engineering practice application, a three-dimensional simulation technology is utilized, so that the feasible configuration of the combustion chamber with the best oil-gas mixing and combustion effects can be effectively solved; in the scientific research process, the influence of configuration on the process and effect of oil-gas mixing and combustion is explored.
Disclosure of Invention
The invention aims to provide a parameterized design method for a combustion chamber configuration of a rotary inclusion type engine, which solves the problems that the traditional combustion chamber configuration in the prior art is low in efficiency and a great deal of time is required to be consumed in adjusting each dimensional parameter of the configuration.
In order to achieve the above purpose, the invention provides a rotary inclusion type engine combustion chamber configuration parameterization design method, which comprises the following steps:
step1, determining the geometric constitution of a combustion chamber and selecting basic parameters for quantitatively describing the configuration section of the combustion chamber;
step 2, calculating coordinates and equation parameters of each important point and line of the combustion chamber configuration section based on the basic parameters;
dividing the cross section of the combustion chamber into a plurality of geometric figures, respectively solving the area and centroid coordinates of each block according to the parameters obtained by calculation in the steps to obtain the cross section area and centroid position of the combustion chamber, and finally calculating the volume of the combustion chamber by using the Golgi theorem;
And 4, screening out a plurality of combustion chamber parameterized design schemes by using an exhaustion method.
Preferably, the combustion chamber is a spatial revolution body and is formed by a space swept by a plane closed geometric figure which rotates 180 degrees around a symmetry axis, the plane closed geometric figure is an axisymmetric figure, and the outline is formed by a piston axis BF, a straight line FE which is perpendicular to the piston axis BF, an EC which is perpendicular to the straight line FE, a circular arc section CA which takes a point C as a starting point and a tangent line AB which takes a point A as a tangent point.
Preferably, the basic parameters of the cross-section include throat diameter D, overall combustion chamber height H, combustion chamber pit radius R, and entrance angle α.
Preferably, the specific calculation process of the coordinates and equation parameters of each important point, line of the combustion chamber configuration section in the step 2 is as follows:
S21, calculating the coordinate of the circle center P corresponding to the arc section CA according to the geometric relationship ) Included angle between line segment PA and vertical direction/>The following are provided:
；
；
；
Wherein D is the overall diameter of the combustion chamber, and the unit is mm; r is the pit radius of the combustion chamber; the unit is mm; the included angle between the tangent line AB and the vertical direction is the entrance angle;
s22, calculating the slope k of the tangent line AB according to the relation between the tangent line AB and the included angle of the transverse axis and the longitudinal axis, wherein the slope k is specifically calculated as follows:
；
In the middle of Is the slope of tangent line AB;
S23, calculating the distance from the point C to the horizontal line passing through the center P according to the Pythagorean theorem The following are provided:
；
In the method, in the process of the invention, The unit is mm for the abscissa of the circular arc section CA corresponding to the circle center P; d is the diameter of the laryngeal opening in mm;
S24, calculating the intercept b of the tangent line AB on the vertical axis according to a formula of the point-to-line distance, wherein the intercept b is as follows:
；
Wherein k is the slope of the tangent line AB; the unit is mm for the ordinate of the circular arc section CA corresponding to the circle center P;
S25, calculating the distance from the point C to the upper top surface of the combustion chamber according to the geometric relationship And the angle between the straight line CP and the horizontal lineThe following are provided:
；
；
wherein H is the total height of the combustion chamber, and the unit is mm; the distance from the point C to a horizontal line passing through the center P is in mm;
s26, calculating the abscissa of the point C according to the geometric relationship, wherein the abscissa is as follows:
；
；
In the method, in the process of the invention, The distance from the point C to the upper top surface of the combustion chamber is in mm;
S27, calculating the coordinate of the tangent point A according to the formula of the distance from the tangent point to the circle center, wherein the distance from the tangent point to the circle center is equal to the radius, and the formula of the distance from the tangent point to the straight line ) The following are provided:
；
；
In the method, in the process of the invention, The unit is mm for the abscissa of the circular arc section CA corresponding to the circle center P; b is the intercept of the tangent line AB on the longitudinal axis in mm; r is the pit radius of the combustion chamber; the unit is mm; k is the slope of tangent line AB.
Preferably, the specific process of step 3 is as follows:
S31, dividing the section of the combustion chamber into 5 parts, wherein the parts comprise a No. 1 block CEF, a No. 2 block BCF, a No. 3 block BPC, a No. 4 block BPA and a No. 5 block PAC;
S32, calculating the area and the total cross-section area of each block, wherein the method specifically comprises the following steps:
area of the No. 1 blocked CEF section: ；
area of the No. 2 blocked BCF cross section: ；
Area of the BPC section No. 3 block: ；
Area of BPA section No. 4 block: ；
area of the PAC cross section of No. 5 block: ；
Total area of combustion chamber cross section: ；
S33, calculating the centroid abscissa of each segmented section and the centroid abscissa of the total section, wherein the centroid abscissa is as follows:
centroid abscissa of block CEF section No. 1: ；
centroid abscissa of No.2 blocked BCF cross section: ；
centroid abscissa of No. 3 block BPC section: ；
centroid abscissa of BPA section No. 4 block: ；
centroid abscissa of No. 5 block PAC cross section: Wherein, the method comprises the steps of, wherein, ；
Combustion chamber cross section centroid abscissa:；
S34, calculating the volume V of the combustion chamber, wherein the method specifically comprises the following steps:
V==/>。
Preferably, the specific process of step 4 is as follows: setting a value set of each basic parameter so as to form an exhaustion space; traversing each group of parameters in the exhaustion space and calculating the volume of the combustion chamber, judging whether the geometric magnitude meets the constraint condition given in advance within the tolerance range, if so, recording the parameter combination of the round, and entering the next group of parameter combinations; if not, directly entering the calculation and judgment of the next group of parameters; after exhaustion, a plurality of combustion chamber configurations meeting design constraints are obtained.
Preferably, the constraints are designed to satisfy a volume equal to a predetermined design volume of the combustion chamber.
Therefore, the rotary inclusion type engine combustion chamber configuration parameterization design method has the following beneficial effects:
(1) The combustion chamber structure shape is quantitatively described by parameters, so that the determination of the structure is more accurate;
(2) The calculation method of the volume of the combustion chamber is provided, repeated modeling in three-dimensional modeling software is avoided, the design process is simplified, and the labor intensity is reduced;
(3) Enough feasible design schemes are efficiently screened out, so that the optimal configuration is facilitated;
(4) The method is easy to realize self-programming and reduces the calculation cost.
The technical scheme of the invention is further described in detail through the drawings and the embodiments.
Drawings
FIG. 1 is a schematic illustration of a cross-sectional profile of a combustion chamber of a rotary inclusion engine of the present invention;
FIG. 2 is a schematic view of the cross-section parameterization of the combustion chamber of the present invention;
FIG. 3 is a schematic illustration of the division of the present invention when solving for the cross-sectional area of the combustion chamber;
FIG. 4 is a block flow diagram of the present invention for exhaustive screening of feasible parameter combinations;
Fig. 5 is a three-dimensional perspective view of a rotary body combustion chamber formed by rotary cutting of a piston crown according to the present invention.
Detailed Description
The following detailed description of the embodiments of the invention, provided in the accompanying drawings, is not intended to limit the scope of the invention, as claimed, but is merely representative of selected embodiments of the invention. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
Referring to fig. 1-4, a method for parameterizing the configuration of a combustion chamber of a rotary inclusion engine includes the following steps:
Step 1, determining the geometric constitution of a combustion chamber and selecting basic parameters for quantitatively describing the configuration section of the combustion chamber; the combustion chamber is a space revolution body and is formed by a space swept by a plane closed geometric figure which rotates 180 degrees around a symmetry axis, the plane closed geometric figure is an axisymmetric figure, and the outline consists of a piston axis BF, a straight line FE which is perpendicular to the piston axis BF, an EC which is perpendicular to the straight line FE, a circular arc section CA which takes a point C as a starting point and a tangent line AB which takes a point A as a tangent point; the basic parameters of the cross section comprise throat diameter D, overall diameter D of the combustion chamber, overall height H of the combustion chamber, pit radius R of the combustion chamber and entrance angle alpha;
Step 2, calculating coordinates and equation parameters of each important point and line of the combustion chamber configuration section based on the basic parameters; the specific calculation process is as follows:
S21, calculating the coordinate of the circle center P corresponding to the arc section CA according to the geometric relationship ) Included angle between line segment PA and vertical direction/>The following are provided:
；
；
；
Wherein D is the overall diameter of the combustion chamber, and the unit is mm; r is the pit radius of the combustion chamber; the unit is mm; the included angle between the tangent line AB and the vertical direction is the entrance angle;
s22, calculating the slope k of the tangent line AB according to the relation between the tangent line AB and the included angle of the transverse axis and the longitudinal axis, wherein the slope k is specifically calculated as follows:
；
In the middle of Is the slope of tangent line AB;
S23, calculating the distance from the point C to the horizontal line passing through the center P according to the Pythagorean theorem The following are provided:
；
In the method, in the process of the invention, The unit is mm for the abscissa of the circular arc section CA corresponding to the circle center P; d is the diameter of the laryngeal opening in mm;
S24, calculating the intercept b of the tangent line AB on the vertical axis according to a formula of the point-to-line distance, wherein the intercept b is as follows:
；
Wherein k is the slope of the tangent line AB; the unit is mm for the ordinate of the circular arc section CA corresponding to the circle center P;
S25, calculating the distance from the point C to the upper top surface of the combustion chamber according to the geometric relationship And the angle between the straight line CP and the horizontal lineThe following are provided:
；
；
wherein H is the total height of the combustion chamber, and the unit is mm; the distance from the point C to a horizontal line passing through the center P is in mm;
s26, calculating the abscissa of the point C according to the geometric relationship, wherein the abscissa is as follows:
；
；
In the method, in the process of the invention, The distance from the point C to the upper top surface of the combustion chamber is in mm;
S27, calculating the coordinate of the tangent point A according to the formula of the distance from the tangent point to the circle center, wherein the distance from the tangent point to the circle center is equal to the radius, and the formula of the distance from the tangent point to the straight line ) The following are provided:
；
；
In the method, in the process of the invention, The unit is mm for the abscissa of the circular arc section CA corresponding to the circle center P; b is the intercept of the tangent line AB on the longitudinal axis in mm; r is the pit radius of the combustion chamber; the unit is mm; k is the slope of tangent line AB.
Dividing the cross section of the combustion chamber into a plurality of geometric figures, respectively solving the area and centroid coordinates of each block according to the parameters obtained by calculation in the steps to obtain the cross section area and centroid position of the combustion chamber, and finally calculating the volume of the combustion chamber by using the Golgi theorem; the specific process is as follows:
S31, dividing the section of the combustion chamber into 5 parts, wherein the parts comprise a No. 1 block CEF, a No. 2 block BCF, a No. 3 block BPC, a No. 4 block BPA and a No. 5 block PAC;
S32, calculating the area and the total cross-section area of each block, wherein the method specifically comprises the following steps:
area of the No. 1 blocked CEF section: ；
area of the No. 2 blocked BCF cross section: ；
Area of the BPC section No. 3 block: ；
Area of BPA section No. 4 block: ；
area of the PAC cross section of No. 5 block: ；
Total area of combustion chamber cross section: ；
S33, calculating the centroid abscissa of each segmented section and the centroid abscissa of the total section, wherein the centroid abscissa is as follows:
centroid abscissa of block CEF section No. 1: ；
centroid abscissa of No.2 blocked BCF cross section: ；
centroid abscissa of No. 3 block BPC section: ；
centroid abscissa of BPA section No. 4 block: ；
centroid abscissa of No. 5 block PAC cross section: Wherein, the method comprises the steps of, wherein, ；
Combustion chamber cross section centroid abscissa:；
S34, calculating the volume V of the combustion chamber, wherein the method specifically comprises the following steps:
V==/>。
Step 4, screening out a plurality of combustion chamber parameterized design schemes by using an exhaustion method; the specific process is as follows: setting a value set of each basic parameter so as to form an exhaustion space; traversing each group of parameters in the exhaustion space and calculating the volume of the combustion chamber, judging whether the geometric magnitude meets the constraint condition given in advance within the tolerance range, taking the designed configuration of the constraint condition to meet the requirement that the volume is equal to the design volume of the combustion chamber given in advance, and recording the parameter combination of the round if the geometric magnitude meets the requirement, and entering the next group of parameter combination; if not, directly entering the calculation and judgment of the next group of parameters; after exhaustion, a plurality of combustion chamber configurations meeting design constraints are obtained.
Examples
As shown in fig. 5, the engine combustion chamber is formed by a part of the top of a cylinder piston which is cut away by rotation, the configuration of which almost determines the shape of the combustion chamber, the combustion chamber configuration being a spatial revolution body, and being constituted by a space swept by a certain planar closed geometry rotated 180 ° about its symmetry axis (i.e. the piston axis). The plane closed graph is an axisymmetric graph, and the outline of the plane closed graph only comprises a straight line segment and an arc segment. The profile configuration is as follows: the piston axis intersects with the point B from the point A by a tangential line section d. Together, the above-described line segments a, b, c, d and their 4 line segments symmetrical about the piston axis, form the combustion chamber configuration cross-sectional profile of the parameterized design of the present invention. In this context, the combustion chamber is referred to as a recessed portion of the piston crown. It is not difficult to find that the combustion chamber geometrically belongs to a revolution body, i.e. a defined plane pattern is rotated 360 ° around a coplanar fixed axis. The defined plane pattern is shown in fig. 1, and its outline is composed of only straight lines and circular arcs, and is also an axisymmetric pattern.
Combustor parameterization refers to the quantitative and unique description of combustor configuration using limited parameters. From the above, it follows that, in the case of the combustion chamber formation rule determination, the parameterization of the combustion chamber configuration is equivalent to the parameterization of the section shown in fig. 1, and, due to the symmetry of the combustion chamber section, the parameterization of the section shown in fig. 1 is equivalent to the parameterization of the section shown in fig. 2.
More specifically, the parameterization of the combustion chamber configuration is achieved by the following four steps. In addition, by means of the advantages of uniqueness, accuracy and the like of parameterization calculation, a sufficient and feasible parameterization design scheme of the combustion chamber configuration can be finally obtained efficiently.
Step1, determining the geometric constitution of a cross section of a combustion chamber and selecting basic parameters;
geometric composition refers to points, lines and their corresponding topological relationships describing the cross-sectional profile of the combustor design. The basic parameters refer to a group of variables (geometric meaning is generally length, coordinates, angles and the like) which can uniquely determine a certain combustion chamber configuration and are mutually independent, and the mutually independent refers to any basic parameter which cannot be calculated by the geometric constraint relation of other basic parameters. The number of basic parameters may be referred to as degrees of freedom. For a defined configuration, the degree of freedom is fixed, but the selection of basic parameters is not unique and can be determined by means of research requirements.
The profile of the cross-section of the combustion chamber design is shown in fig. 1, and it is evident that the profile consists of only a simple straight line and an arc, wherein the lower inclined straight line segment is tangential to the respective arc segment, and that the cross-section of fig. 1 is rotated 180 ° about its symmetry axis (piston axis) to form a pit in the piston top, i.e. the combustion chamber.
In order to make the parameterization process of the combustion chamber configuration more standard, a plane rectangular coordinate system is established as shown in fig. 2, a transverse axis is tangent to the circular arc of the pit, a tangent point is at the lowest point of the circular arc, a longitudinal axis is collinear with the symmetry axis of the cross section of the combustion chamber, and the intersection point of the longitudinal axis and the symmetry axis is the origin of the coordinate axes. At the same time ensure the inlet angle isThe straight line segment AB of the groove is tangent to the circular arc of the pit, and the tangent point is A; the contour line of the upper top surface is ensured to be parallel to the transverse axis, and the contour lines of the left side plane and the right side plane are vertical to the transverse axis.
The five variables describing the configuration of the combustion chamber, namely the diameter D of the throat, the overall diameter D of the combustion chamber, the overall height H of the combustion chamber, the pit radius R of the combustion chamber and the inlet angle alpha, are selected as the basic parameters, and specific line segments, coordinates and angles are marked as shown in figure 2 (in order to avoid complexity, figure 2 only shows half of the cross section of the combustion chamber about the symmetry axis).
Step 2, describing the configuration of the combustion chamber by using basic parameters;
from the above description, it is clear that the cross-sectional configuration of the combustion chamber is uniquely determined when the value of the basic parameter is legally determined. Thus, the non-essential parameters of the cross section can be obtained by algebraic calculation from the known essential parameters through geometric constraint relations. More specifically, the calculation of each non-essential parameter is as follows:
2-1: calculating the P coordinate of the corresponding circle center of the pit arc according to the simple geometric relation ) Included angle between line segment PA and vertical direction/>The following are provided:
；
；
；
wherein D is a basic variable, the overall diameter of the combustion chamber; the unit is mm; r is a basic variable, and the pit radius of the combustion chamber; the unit is mm; The angle between the straight line section AB and the vertical direction is the basic variable, the entrance angle;
2-2: according to the relation between the included angle of the straight line AB and the transverse axis and the vertical axis, the slope k of the straight line AB is calculated as follows:
；
Wherein k is the slope of the straight line AB;
2-3: according to Pythagorean theorem, calculating the distance from the point D to the horizontal line passing through the center P The following are provided:
；
In the method, in the process of the invention, The unit is mm, d is basic variable, and the diameter of the throat is equal to the abscissa of the circle center corresponding to the pit arc (calculated in the previous step); the unit is mm;
2-4: since the straight line segment AB is tangent to the circle P, the intercept b of the straight line AB on the longitudinal axis is calculated by means of the formula of the point-to-straight line distance in the planar analytic geometry as follows:
；
wherein k is the slope of the straight line AB (calculated in the previous step); The ordinate of the circle center corresponding to the pit arc (calculated in the previous step) is in mm;
2-5: calculating the distance from point C to the upper top surface of the combustion chamber based on a simple geometric relationship Included angle between straight line DP and horizontal line/>The following are provided:
；
；
wherein H is a basic variable, and the overall height of the combustion chamber; the unit is mm; the distance from the point C to the horizontal line passing through the center P (calculated in the previous step) is in mm;
2-6: from the simple geometric relationship, the abscissa of the point C is calculated as follows:
；
；
Wherein: the distance from point C to the upper top surface of the combustion chamber (calculated in the previous step); the unit is mm;
2-7: according to the distance from the tangent point to the circle center being equal to the radius, combining the distance formula from the tangent point to the straight line, listing a unitary quadratic equation, and solving and calculating the coordinate of the tangent point A ) The following are provided:
；
；
Through the steps of the order and the determination, the rest variables can be obtained through calculation through the values of the basic variables. For example, when the basic variables are And calculating the values of the rest parameters by the steps as follows: /(I)，/>，，/>，/>，/>，(Unit: mm).
Step 3: calculating combustion chamber volume
The volume of the combustion chamber influences the compression ratio, and the compression ratio plays an important role in the combustion condition in the engine cylinder, so that the performance of the whole engine is influenced. Therefore, calculating the combustion chamber volume during the parameterized design phase is of great importance. As described above, after step 1 is completed, the parameterized definition of the combustion chamber configuration has in fact been completed. In this case, the size of the combustion chamber volume is affected only by the basic variables, so that a functional relation of the combustion chamber volume with respect to each basic variable can be theoretically deduced, but if the primary function of the primary function form cannot be obtained by integration in the solving process, the volumetric functional relation may not be written into an analytical expression, but a process of calculating the combustion chamber volume according to the basic parameters may be realized. The specific calculation process is as follows:
dividing the cross section of the combustion chamber into a plurality of simple geometric figures, respectively solving the area and centroid coordinates of each block according to the parameters obtained by calculation in the steps, further solving to obtain the cross section area and centroid position of the combustion chamber, and finally calculating to obtain the volume of the combustion chamber by using the Golgi theorem. The calculation can be divided into the following sub-steps:
S31, dividing the section of the combustion chamber into 5 parts, wherein the parts comprise a No. 1 block CEF, a No. 2 block BCF, a No. 3 block BPC, a No. 4 block BPA and a No. 5 block PAC;
S32, calculating the area and the total cross-section area of each block, wherein the method specifically comprises the following steps:
area of the No. 1 blocked CEF section: ；
area of the No. 2 blocked BCF cross section: ；
Area of the BPC section No. 3 block: ；
Area of BPA section No. 4 block: ；
area of the PAC cross section of No. 5 block: ；
Total area of combustion chamber cross section: ；
S33, calculating the centroid abscissa of each segmented section and the centroid abscissa of the total section, wherein the centroid abscissa is as follows:
centroid abscissa of block CEF section No. 1: ；
centroid abscissa of No.2 blocked BCF cross section: ；
centroid abscissa of No. 3 block BPC section: ；
centroid abscissa of BPA section No. 4 block: ；
centroid abscissa of No. 5 block PAC cross section: Wherein, the method comprises the steps of, wherein, ；
Combustion chamber cross section centroid abscissa:；
S34, calculating the volume V of the combustion chamber, wherein the method specifically comprises the following steps:
V==/>。
Through the steps of the order and the determination, the cross-sectional area, the centroid coordinates and the combustion chamber volume can be calculated through the values of basic variables. More specifically, when the basic parameters take the last example of step 2, the calculation results in ，/>，，/>，/>，/>(Unit:/>)。
Regarding step 4, the goal is to screen out enough feasible parameterized combinations to achieve parameterized design of the combustion chamber. The logic process is as shown in fig. 4, and a value set is set for each basic parameter, and because the value set can be set arbitrarily, the basic parameters are combined to form a variable space with arbitrarily large capacity. And using a computer to write a program, traversing each parameter combination by using an exhaustion method, calculating related quantities, judging whether a plurality of related quantities meet corresponding constraint conditions to determine whether the parameter combination is feasible, and recording the feasible parameter combination to a final output result.
The basic parameters are mutually independent, namely, any basic parameter cannot be calculated by the rest basic parameters through the geometric constraint relation, and when each basic parameter is determined, the section of the combustion chamber is uniquely determined; description of the combustion chamber configuration refers to representing the geometric elements (points, lines, faces) of the cross-sectional profile of the combustion chamber using only the algebraic terms comprising the basic parameters and other known constants; the combustion chamber volume refers to the volume of the geometry formed in space when the parameterized section in step 2 is rotated 360 ° about its axis of symmetry; a viable combustion chamber parameterized design refers to a set of parameter combinations including basic parameters that uniquely correspond to a certain defined combustion chamber geometry.
Specifically, for each parameter combination, the constraint condition is determined, and the constraint condition includes a geometric constraint condition and a volume value constraint condition, namely, the following three geometric constraint conditions and one volume value constraint condition are determined. First, the intercept of line AB on the y-axis is less than the overall combustor height H; second, the combustor throat diameter D is less than the combustor overall diameter D; third, the distance from point C to the upper top surface of the combustion chamberGreater than 0; fourth, the volume of the combustion chamber calculated according to step 3 is sufficiently close to the volume to be given, in practice by differencing the calculated volume with the target volume if the absolute value of the difference is less than the predetermined tolerance/>(E.g./>)) It can be treated as a set of feasible solutions and recorded. And then calculating and judging the next group of parameter combinations, and repeatedly cycling in this way to finally obtain enough feasible parameterized configuration combinations of the combustion chamber. Therefore, the parameterized design of the combustion chamber configuration is realized, and the subsequent optimization and the selection of the configuration are facilitated.
Therefore, the invention adopts the parameterized design method of the revolving inclusion type engine combustion chamber configuration, and by determining the basic coordinate parameters of the configuration, quantitatively expressing the rest parameters by using the basic parameters and calculating the volume of the combustion chamber space, the geometric configuration of the combustion chamber can be quantitatively described by using the parameters and formulas, and meanwhile, the purpose of obtaining the parameterized design scheme of the combustion chamber configuration meeting various geometric constraints is achieved, thereby having important significance for engineering practice and scientific research.
Finally, it should be noted that: the above embodiments are only for illustrating the technical solution of the present invention and not for limiting it, and although the present invention has been described in detail with reference to the preferred embodiments, it will be understood by those skilled in the art that: the technical scheme of the invention can be modified or replaced by the same, and the modified technical scheme cannot deviate from the spirit and scope of the technical scheme of the invention.
Claims (7)
1. The parameterized design method for the configuration of the combustion chamber of the rotary inclusion type engine is characterized by comprising the following steps of:
step1, determining the geometric constitution of a combustion chamber and selecting basic parameters for quantitatively describing the configuration section of the combustion chamber;
step 2, calculating coordinates and equation parameters of each important point and line of the combustion chamber configuration section based on the basic parameters;
dividing the cross section of the combustion chamber into a plurality of geometric figures, respectively solving the area and centroid coordinates of each block according to the parameters obtained by calculation in the steps to obtain the cross section area and centroid position of the combustion chamber, and finally calculating the volume of the combustion chamber by using the Golgi theorem;
And 4, screening out a plurality of combustion chamber parameterized design schemes by using an exhaustion method.
2. The rotary inclusion engine combustion chamber configuration parameterization design method of claim 1, wherein the method comprises the following steps: the combustion chamber is a space revolution body and is formed by a space swept by a plane closed geometric figure which rotates 180 degrees around a symmetry axis, the plane closed geometric figure is an axisymmetric figure, and the outline is formed by a piston axis BF, a straight line FE which is perpendicular to the piston axis BF, an EC which is perpendicular to the straight line FE, a circular arc section CA which takes a point C as a starting point and a tangent line AB which takes a point A as a tangent point.
3. The rotary inclusion engine combustion chamber configuration parameterization design method of claim 2, wherein the method comprises the following steps: the basic parameters of the cross section include throat diameter D, overall combustion chamber height H, combustion chamber pit radius R, and entrance angle α.
4. The parameterized design method for the combustion chamber configuration of the rotary inclusion engine according to claim 3, wherein the specific calculation process of the coordinates and equation parameters of each important point and line of the combustion chamber configuration section in the step 2 is as follows:
S21, calculating the coordinate of the circle center P corresponding to the arc section CA according to the geometric relationship ) Included angle between line segment PA and vertical directionThe following are provided:
Wherein D is the overall diameter of the combustion chamber, and the unit is mm; r is the pit radius of the combustion chamber; the unit is mm; the included angle between the tangent line AB and the vertical direction is the entrance angle;
s22, calculating the slope k of the tangent line AB according to the relation between the tangent line AB and the included angle of the transverse axis and the longitudinal axis, wherein the slope k is specifically calculated as follows:
In the middle of Is the slope of tangent line AB;
S23, calculating the distance from the point C to the horizontal line passing through the center P according to the Pythagorean theorem The following are provided:
In the method, in the process of the invention, The unit is mm for the abscissa of the circular arc section CA corresponding to the circle center P; d is the diameter of the laryngeal opening in mm;
S24, calculating the intercept b of the tangent line AB on the vertical axis according to a formula of the point-to-line distance, wherein the intercept b is as follows:
Wherein k is the slope of the tangent line AB; the unit is mm for the ordinate of the circular arc section CA corresponding to the circle center P;
S25, calculating the distance from the point C to the upper top surface of the combustion chamber according to the geometric relationship Included angle between straight line CP and horizontal line/>The following are provided:
wherein H is the total height of the combustion chamber, and the unit is mm; the distance from the point C to a horizontal line passing through the center P is in mm;
s26, calculating the abscissa of the point C according to the geometric relationship, wherein the abscissa is as follows:
In the method, in the process of the invention, The distance from the point C to the upper top surface of the combustion chamber is in mm;
S27, calculating the coordinate of the tangent point A according to the formula of the distance from the tangent point to the circle center, wherein the distance from the tangent point to the circle center is equal to the radius, and the formula of the distance from the tangent point to the straight line ) The following are provided:
In the method, in the process of the invention, The unit is mm for the abscissa of the circular arc section CA corresponding to the circle center P; b is the intercept of the tangent line AB on the longitudinal axis in mm; r is the pit radius of the combustion chamber; the unit is mm; k is the slope of tangent line AB.
5. The parameterized design method for the combustion chamber configuration of the rotary inclusion engine according to claim 4, wherein the specific process of the step 3 is as follows:
S31, dividing the section of the combustion chamber into 5 parts, wherein the parts comprise a No. 1 block CEF, a No. 2 block BCF, a No. 3 block BPC, a No. 4 block BPA and a No. 5 block PAC;
S32, calculating the area and the total cross-section area of each block, wherein the method specifically comprises the following steps:
area of the No. 1 blocked CEF section: ；
area of the No. 2 blocked BCF cross section: ；
Area of the BPC section No. 3 block: ；
Area of BPA section No. 4 block: ；
area of the PAC cross section of No. 5 block: ；
Total area of combustion chamber cross section: ；
S33, calculating the centroid abscissa of each segmented section and the centroid abscissa of the total section, wherein the centroid abscissa is as follows:
centroid abscissa of block CEF section No. 1: ；
centroid abscissa of No.2 blocked BCF cross section: ；
centroid abscissa of No. 3 block BPC section: ；
centroid abscissa of BPA section No. 4 block: ；
centroid abscissa of No. 5 block PAC cross section: Wherein, the method comprises the steps of, wherein, ；
Combustion chamber cross section centroid abscissa:；
S34, calculating the volume V of the combustion chamber, wherein the method specifically comprises the following steps:
V==/>。
6. The parameterized design method for the combustion chamber configuration of the rotary inclusion engine according to claim 5, wherein the specific process of the step 4 is as follows: setting a value set of each basic parameter so as to form an exhaustion space; traversing each group of parameters in the exhaustion space and calculating the volume of the combustion chamber, judging whether the geometric magnitude meets the constraint condition given in advance within the tolerance range, if so, recording the parameter combination of the round, and entering the next group of parameter combinations; if not, directly entering the calculation and judgment of the next group of parameters; after exhaustion, a plurality of combustion chamber configurations meeting design constraints are obtained.
7. The rotary inclusion engine combustion chamber configuration parameterization design method of claim 6, wherein the method comprises the following steps: the constraints are designed to satisfy a volume equal to a predetermined design volume of the combustion chamber.
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Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20180106480A1 (en) * | 2016-10-19 | 2018-04-19 | GTL Company | Scaleable acoustically-stable combustion chamber and design methods |
| US20210209266A1 (en) * | 2020-01-02 | 2021-07-08 | Viettel Group | Aerodynamic designing method of the central section of small size gas turbine engines |
| CN114329829A (en) * | 2021-12-24 | 2022-04-12 | 哈尔滨工程大学 | Automatic generation method and system for piston profile of marine diesel engine |
| CN115168991A (en) * | 2022-06-28 | 2022-10-11 | 北京理工大学 | Parametric design method for opposed-piston double-collision wall oil-spraying combustion chamber |
| CN117077293A (en) * | 2023-10-11 | 2023-11-17 | 中国人民解放军国防科技大学 | Multi-disciplinary coupling performance simulation method and system for solid rocket engine |
| CN117421842A (en) * | 2023-12-18 | 2024-01-19 | 潍柴动力股份有限公司 | Combustion chamber, engine and combustion chamber design method |
| CN117556551A (en) * | 2024-01-11 | 2024-02-13 | 中国人民解放军国防科技大学 | Lightweight design method, device, equipment and medium for engine combustion chamber shell |
-
2024
- 2024-03-22 CN CN202410335271.6A patent/CN117932824B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20180106480A1 (en) * | 2016-10-19 | 2018-04-19 | GTL Company | Scaleable acoustically-stable combustion chamber and design methods |
| US20210209266A1 (en) * | 2020-01-02 | 2021-07-08 | Viettel Group | Aerodynamic designing method of the central section of small size gas turbine engines |
| CN114329829A (en) * | 2021-12-24 | 2022-04-12 | 哈尔滨工程大学 | Automatic generation method and system for piston profile of marine diesel engine |
| CN115168991A (en) * | 2022-06-28 | 2022-10-11 | 北京理工大学 | Parametric design method for opposed-piston double-collision wall oil-spraying combustion chamber |
| CN117077293A (en) * | 2023-10-11 | 2023-11-17 | 中国人民解放军国防科技大学 | Multi-disciplinary coupling performance simulation method and system for solid rocket engine |
| CN117421842A (en) * | 2023-12-18 | 2024-01-19 | 潍柴动力股份有限公司 | Combustion chamber, engine and combustion chamber design method |
| CN117556551A (en) * | 2024-01-11 | 2024-02-13 | 中国人民解放军国防科技大学 | Lightweight design method, device, equipment and medium for engine combustion chamber shell |
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