CN110008516B - Asymmetric design method for axial-flow compressor hub with controllable pressure gradient - Google Patents

Asymmetric design method for axial-flow compressor hub with controllable pressure gradient Download PDF

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CN110008516B
CN110008516B CN201910173258.4A CN201910173258A CN110008516B CN 110008516 B CN110008516 B CN 110008516B CN 201910173258 A CN201910173258 A CN 201910173258A CN 110008516 B CN110008516 B CN 110008516B
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李志平
李秋实
潘天宇
张亚飞
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Beihang University Sichuan International Center For Innovation In Western China Co ltd
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Abstract

The present disclosure provides a method of asymmetric end wall modeling to control a pressure gradient, comprising: constructing a molding line in the blade channel, wherein the molding line is constructed according to physical flow characteristics in the blade channel, and is a non-axisymmetric curve so as to reduce transverse pressure gradient in the blade channel, and the shape of the molding line is determined by control parameters; obtaining an end wall modeling curved surface by sweeping a modeling line; and carrying out combined optimization on the control parameters according to the target parameters, and determining the end wall modeling curved surface when the target parameters obtain extreme values as a target end wall modeling curved surface.

Description

Asymmetric design method for axial-flow compressor hub with controllable pressure gradient
Technical Field
The present disclosure relates to a method of asymmetric end wall modeling to control pressure gradients.
Background
With the tremendous development of aeronautical technology, researchers are exploring the limits of the performance of various parts of the engine. As one of the engine core components, the design and optimization of the compressor is a topic of continued interest to researchers. The modeling of the end wall of the compressor is taken as an effective means for improving the internal flow of the compressor, and is one of the hot spots in the current research along with the improvement of design technology.
Different from the traditional impeller machinery end wall design, the compressor end wall design respectively introduces an axial and circumferential concave-convex modeling technology, namely an axisymmetric end wall modeling technology and an asymmetric end wall modeling technology. Compared with the axisymmetric end wall modeling technology, the asymmetric end wall modeling starts later. This design concept originates from the turbine component and is primarily used to reduce the turbine secondary flow. The Rolls-Royce company has applied asymmetric end wall modeling techniques to improve the high pressure turbine secondary flow losses of Trent500 engines. The test results of the components show that: the non-axisymmetric end wall shaping increases the high pressure turbine efficiency by 0.59% at design conditions.
However, because of the different flow conditions within the turbine and compressor, the application of asymmetric end wall modeling to compressor end wall design has a certain difficulty, mainly because the compressor internal flow is mainly a reverse pressure gradient flow, which can greatly reduce the effectiveness of the asymmetric end wall modeling in suppressing angular separation and reducing secondary flow losses. The inventors have recognized that the asymmetric design approach of the compressor end wall suffers from low timeliness, randomness, or reliance on the level of experience of the designer.
Disclosure of Invention
To solve at least one of the above technical problems, the present disclosure provides an asymmetric end wall modeling method of controlling a pressure gradient, comprising: constructing a molding line in the blade channel, wherein the molding line is constructed according to physical flow characteristics in the blade channel, and is a non-axisymmetric curve so as to reduce transverse pressure gradient in the blade channel, and the shape of the molding line is determined by control parameters; obtaining an end wall modeling curved surface by sweeping a modeling line; and carrying out combined optimization on the control parameters according to the target parameters, and determining the end wall modeling curved surface when the target parameters obtain extreme values as a target end wall modeling curved surface.
According to another embodiment of the present disclosure, the molding line is constructed from a modeling function including a first trigonometric function and a second trigonometric function. Wherein the first trigonometric function builds a first portion of the molding line and the second trigonometric function builds a second portion of the molding line.
According to a further embodiment of the present disclosure, the first portion is adjacent to the suction side of the blade channel and the first portion is concave; and a second portion adjacent the pressure face of the vane passage, and the second portion being convex.
According to yet another embodiment of the present disclosure, the first portion is 1/4 period long; and the second portion is also 1/4 of a period long.
According to yet another embodiment of the present disclosure, the modeling line has a modeling function of
In the formula (1), the upper formula is a first trigonometric function, the lower formula is a second trigonometric function, R is the distance between a modeling point on a modeling line and the center of a compressor, and R is 1 For the radius of the hub of the air compressor, theta is the rotating angle of any modeling point relative to the modeling starting point, and theta 1 Is the intersection point of the first part and the second part, theta 0 For the angle rotated from the modeling start point to the modeling end point, A 1 For the amplitude of the first trigonometric function, A 2 Is the amplitude of the second trigonometric function, where θ 1 、A 1 And A 2 Is a control parameter of the molding line.
According to yet another embodiment of the present disclosure, the molding line includes 3, and the 3 molding lines axially divide the blade channel into 4 equal parts with the start line and the end line of the blade channel.
According to yet another embodiment of the present disclosure, a method of asymmetric end wall modeling for controlling a pressure gradient includes: and reducing the number of the control parameters according to constraint conditions, wherein the constraint conditions are that the physical flow area of the blade channel is kept unchanged.
According to yet another embodiment of the present disclosure, the constraint is that
Obtained according to formula (2)
Wherein A is 1 And A 2 Is a control parameter of the molding line.
According to yet another embodiment of the present disclosure, the target parameter is the adiabatic efficiency of the compressor.
According to yet another embodiment of the present disclosure, the combinatorial optimization is performed by a multi-island genetic algorithm.
Drawings
The accompanying drawings, which are included to provide a further understanding of the disclosure and are incorporated in and constitute a part of this specification, illustrate exemplary embodiments of the disclosure and together with the description serve to explain the principles of the disclosure.
FIG. 1 is a flow diagram of an asymmetric end wall modeling method of controlling a pressure gradient in accordance with at least one embodiment of the present disclosure.
Fig. 2 is a schematic view of an asymmetric end wall region in accordance with at least one embodiment of the present disclosure.
Fig. 3 is a schematic view of a molding line according to at least one embodiment of the present disclosure.
FIG. 4 is a flow chart of control parameter combination optimization of an asymmetric end wall modeling method of controlling a pressure gradient in accordance with at least one embodiment of the present disclosure.
Fig. 5 is a graph of adiabatic efficiency of a compressor after optimization of an asymmetric end wall modeling method for controlling pressure gradients in accordance with at least one embodiment of the present disclosure.
Fig. 6 is a graph of total pressure ratio of a compressor after optimization of an asymmetric end wall modeling method for controlling pressure gradients in accordance with at least one embodiment of the present disclosure.
FIG. 7 is a graph of circumferential pressure coefficients of a flow channel after optimization of an asymmetric end wall modeling method for controlling pressure gradients in accordance with at least one embodiment of the present disclosure.
Detailed Description
The present disclosure is described in further detail below with reference to the drawings and the embodiments. It is to be understood that the specific embodiments described herein are merely illustrative of the relevant content and not limiting of the present disclosure. It should be further noted that, for convenience of description, only a portion relevant to the present disclosure is shown in the drawings.
In addition, embodiments of the present disclosure and features of the embodiments may be combined with each other without conflict. The present disclosure will be described in detail below with reference to the accompanying drawings in conjunction with embodiments.
The method comprises the steps of dispersing modeling areas of the end wall of the compressor on the basis of deeply knowing the flow of the end area of the compressor, constructing a modeling function based on transverse pressure gradient of the control end wall by combining physical flow characteristics, selecting proper constraint conditions and target parameters, and carrying out combined optimization on all modeling points.
The core of the asymmetric end wall modeling for improving the secondary flow development in the turbine channel is to regulate and control the pressure gradient in the turbine channel. Compared with a turbine, the transverse reverse pressure gradient of the blade cascade channel of the air compressor is larger, so that the development of secondary flow is enhanced to a certain extent, and more serious secondary flow loss is caused. Thus, the present disclosure contemplates an asymmetric end wall modeling function that, by adjusting modeling function parameters, further control adjusts the lateral pressure gradients of the compressor cascade channels, ultimately achieving a reduction in secondary flow losses. Different from the traditional method, the method adds a combined optimizing process, and obtains the optimal modeling by carrying out combined optimizing on the modeling function.
In at least one embodiment of the present disclosure, the present disclosure provides a method of asymmetric end wall modeling for controlling a pressure gradient, as shown in fig. 1, comprising the steps of:
s1: constructing a molding line in the blade channel, wherein the molding line is constructed according to physical flow characteristics in the blade channel, and is a non-axisymmetric curve so as to reduce transverse pressure gradient in the blade channel, and the shape of the molding line is determined by control parameters;
s2: obtaining an end wall modeling curved surface by sweeping a modeling line;
s3: and carrying out combined optimization on the control parameters according to the target parameters, and determining the end wall modeling curved surface when the target parameters obtain extreme values as a target end wall modeling curved surface.
Specific steps may be described as follows. Firstly, after the three-dimensional modeling of any air compressor is obtained, the geometric parameters of the blade and the hub are respectively extracted. The single vane passage is then axially divided into four equal divisions by five lines, as shown in fig. 2, which is the non-axisymmetric end wall shaping region of the single vane passage. In order to ensure that the front and rear edges of the compressor blade are free from modeling interruption, the starting line 1 and the ending line 5 of the blade channel are set as fixed lines, namely, the shapes of the lines 1 and 5 are unchanged in the modeling process. The lines 2, 3 and 4 are molding lines, and the endpoints of the molding lines are respectively arranged on the camber lines of the blades, so that no molding interruption occurs in the molding process. Next, by sweeping lines 1, 2, 3, 4 and 5, an entire asymmetric curve is generated at the end wall shaping region. Finally, the pressure gradient variation of the runner is controlled by controlling the curvature and amplitude variation of the molding lines 2, 3 and 4. The construction process of the molding lines 2, 3 and 4 will be described in detail below. The molding line 2 is only taken as an example for illustration, and the construction method of the molding lines 3 and 4 is the same as that of the molding line, and will not be repeated.
According to another embodiment of the present disclosure, the modeling line is constructed from modeling functions including a first trigonometric function and a second trigonometric function, taking into account the internal flow characteristics of the compressor. Wherein the first trigonometric function builds a first portion of the molding line and the second trigonometric function builds a second portion of the molding line.
According to yet another embodiment of the present disclosure, as shown in FIG. 3, the first portion is proximate the suction side of the blade channel and the first portion is concave; and a second portion adjacent the pressure face of the vane passage, and the second portion being convex.
According to yet another embodiment of the present disclosure, as shown in FIG. 3, the first portion is 1/4 period long; and the second portion is also 1/4 of a period long.
FIG. 3 is a plane taken through the molding line 2, R in the drawing 1 For the radius of the hub of the compressor, the black area is the blade of the compressor, the broken line AOB is the molding line 2, which is composed of two trigonometric function curves, wherein AO is the first trigonometric function curve, namely the first part, the length is 1/4 period, and the amplitude is A 1 The method comprises the steps of carrying out a first treatment on the surface of the OB is the second trigonometric curve, i.e. the second part, with a length of 1/4 cycle and an amplitude A 2 . Because the pressure at the suction surface of the blade is lower, an AO trigonometric function curve is arranged to be concave downwards for reducing the speed and boosting the air flow; the pressure at the pressure surface of the blade is higher, so that an OB trigonometric function curve is arranged for increasing and reducing the speed and the pressure of the airflowProtruding upwards. Therefore, the transverse pressure gradient balance of the compressor runner can be realized through the up-and-down concave-convex of the two trigonometric function curves. Similarly, the molding lines 3 and 4 are also respectively composed of two trigonometric function curves similar to the upper and lower concave-convex.
According to yet another embodiment of the present disclosure, the modeling line has a modeling function of
In the formula (1), the upper formula is a first trigonometric function, the lower formula is a second trigonometric function, R is the distance between a modeling point on a modeling line and the center of a compressor, and R is 1 For the radius of the compressor hub, θ is the angle through which any modeling point rotates relative to the modeling starting point (point a in fig. 3), θ 1 Corresponding to the intersection point of the first portion and the second portion, i.e. O point, θ in FIG. 3 0 The value of the angle from the modeling start point to the modeling end point is related to the number of blades n, and the formula is:
thus, by constructing two trigonometric curves, the geometric shape can be mapped to the physical flow characteristics. Wherein the amplitude A of the two functions is adjusted 1 And A 2 The amplitude of geometric modeling change of the runner can be adjusted, and subsequent structural strength checking and adjusting are convenient. At the same time, the change of the geometric modeling amplitude also determines the amplitude of the transverse pressure gradient of the flow channel, which also determines the development intensity of the secondary flow to a certain extent. By adjusting theta 1 The distribution of the transverse pressure gradient of the flow channel can be regulated, and the transverse development of the secondary flow can be conveniently controlled. Thus, θ 1 、A 1 And A 2 Is a control parameter of the molding line. Similarly, the amplitudes and theta corresponding to the molding lines 3 and 4 are respectively adjusted 1 The end wall shape of the compressor can be adjusted, and further the development rule and blending of the secondary flow along the axial direction are controlled.
According to the modeling mode, each modeling line corresponds to 3 control parameters, namely theta 1 、A 1 And A 2 The 3 molding lines have 3×3=9 control parameters. In order to perform the optimization design of the asymmetric end wall, the 9 control parameters need to be optimized, which increases the workload of the whole optimization process, and therefore, the control parameters need to be simplified. Considering that the asymmetric end wall modeling changes the flow passage shape of the compressor, the design point of the compressor is offset, and the common working line of the whole engine is affected. Therefore, the core of the asymmetric end wall modeling is to improve the performance of the engine as much as possible under the condition of ensuring that the working point of the compressor is not deviated, and reduce the secondary flow loss, so that proper constraint conditions are required to be added.
According to yet another embodiment of the present disclosure, a method of asymmetric end wall modeling for controlling a pressure gradient includes: the number of control parameters is reduced according to constraint conditions, wherein the constraint conditions are that the physical flow area of the blade channel is kept unchanged, namely, the areas of the concave and the convex of the hub are mutually counteracted, so that the working point of the air compressor is ensured not to deviate as much as possible.
As can be seen from equation (1), the constraint of the modeling function is
In the formula (3), the amino acid sequence of the compound,is the first trigonometric function edge [0, theta ] 1 ]Is the integral of the first part, i.e. the area of the recess,/->Is a second trigonometric function edge [ theta ] 1 ，θ 0 ]I.e. the area of the protrusions of the second part. The convex area and the concave area cancel each other out, so that the physical flow area is kept unchanged. Solving the formula (3) to obtain theta 1 、A 1 And A 2 Relationship between:
thus, the control parameters of one molding line are simplified into two, namely A 1 And A 2 The control parameters of the three molding lines are 6.
To ensure formula applicability, for A 1 And A 2 Carrying out dimensionless treatment to obtain:
then substituting equations (4) and (5) into equation (1) can result in:
in the formula, k can be changed 1 And k 2 And further control the shape of the two trigonometric curves, and also ensure a reduced calculation amount due to fewer parameters. In the following shaping, only the control parameters k of the shaping line 2 need to be optimized 21 And k 22 Control parameter k of moulding line 3 31 And k 32 Control parameter k of moulding line 4 41 And k 42 These 6 control parameters result in an optimized asymmetric end wall profile.
According to yet another embodiment of the present disclosure, the target parameter may be the adiabatic efficiency of the compressor.
According to yet another embodiment of the present disclosure, combinatorial optimization may be performed by a multi-island genetic algorithm.
The initial asymmetric end wall configuration can be obtained by giving the initial values of the control parameters based on design experience. In order to ensure that the best end wall modeling is obtained, the combined optimization of 6 parameters is also needed, and the process is based on numerical simulation. The specific operation process is as shown in fig. 4, firstly, the three-dimensional geometric modeling of the air compressor is obtained, then the three-dimensional geometric modeling is discretized, the initial asymmetric end wall modeling is obtained through the asymmetric end wall modeling method, and the geometric file of the air compressor is rewritten; and then the initial geometric modeling is led into Autogrid5 for grid division, the division process is that firstly grid division is carried out according to the axisymmetric hub, and then the divided grids are attached to the asymmetric end wall, so that the asymmetric end wall grids are formed. After that, the mesh file is imported into the numerca\fine component for the given of boundary conditions, selection of turbulence models, and so on. Then, numerical simulation is carried out, and the characteristics of efficiency, pressure ratio and the like of the air compressor are obtained, so that reference is provided for the next iteration. Through such a cycle, the corresponding compressor characteristics under different control parameters can be obtained. And then adopting a multi-island genetic algorithm, taking 6 control parameters as independent variables and the efficiency of the gas compressor as target parameters, and performing iterative optimization to finally obtain the optimal asymmetric end wall modeling, namely the target end wall modeling.
In order to control the pressure gradient in the runner, the method adopts an asymmetric end wall modeling, and finally obtains the optimal asymmetric hub modeling by carrying out combined optimization on each control parameter. To verify the technical effect of the present disclosure, a single stage axial flow high pressure compressor was asymmetrically modeled. As shown in fig. 5 and 6, it was found that the adiabatic efficiency of the compressor was improved over the entire operating point range, particularly by 0.61 percent at the design point, by comparison with the original compressor profile, with the compressor pressure ratio remaining unchanged. At the same time, comparing the pressure gradients of the vane passages, as shown in FIG. 7, a significant reduction in the flow passage transverse pressure gradient after optimization can be seen.
The method combines the internal flow characteristics of the compressor, provides a novel asymmetric end wall modeling function, and further realizes the adjustment of the transverse pressure gradient in the compressor channel by adjusting the end wall modeling function.
By combining with the complex flow characteristics of the end region of the air compressor, the modeling region of the end wall of the air compressor is parameterized, proper constraint conditions and optimization targets are given, and the optimal end wall modeling is obtained by carrying out combined optimization on each control parameter, so that the aim of reducing the secondary flow loss is fulfilled.
It will be appreciated by those skilled in the art that the above-described embodiments are merely for clarity of illustration of the disclosure, and are not intended to limit the scope of the disclosure. Other variations or modifications will be apparent to persons skilled in the art from the foregoing disclosure, and such variations or modifications are intended to be within the scope of the present disclosure.

Claims (4)

1. A method of asymmetric end wall modeling for controlling a pressure gradient, the method comprising:
constructing a molding line in a blade channel, wherein the molding line is constructed according to physical flow characteristics in the blade channel, the molding line is a non-axisymmetric curve so as to reduce transverse pressure gradient in the blade channel, and the shape of the molding line is determined by control parameters;
the modeling line is constructed by modeling functions, and the modeling functions of the modeling line are as follows
In the formula (1), the upper formula is a first trigonometric function, the lower formula is a second trigonometric function, R is the distance between a modeling point on the modeling line and the center of the compressor, and R is 1 For the radius of the hub of the air compressor, theta is the rotating angle of any modeling point relative to the modeling starting point, theta 1 Is the intersection point of the first part and the second part, theta 0 For the angle rotated from the modeling start point to the modeling end point, A 1 For the amplitude of the first trigonometric function, A 2 Is the amplitude of the second trigonometric function, where θ 1 、A 1 And A 2 Control parameters for the molding line;
obtaining an end wall modeling curved surface by sweeping the modeling line; and
performing combined optimization on the control parameters according to the target parameters, and determining the end wall modeling curved surface when the target parameters obtain extreme values as a target end wall modeling curved surface;
the asymmetric end wall modeling method for controlling the pressure gradient comprises the steps of reducing the number of the control parameters according to constraint conditions, wherein the constraint conditions are that the physical flow area of the blade channel is kept unchanged;
the constraint condition is that
Obtained according to formula (2)
Wherein A1 and A2 are control parameters of the molding line.
2. The method of claim 1, wherein the molding lines include 3 molding lines, the 3 molding lines dividing the vane passage into 4 equal parts along an axial direction with a start line and a stop line of the vane passage.
3. The method of claim 1, wherein the target parameter is adiabatic efficiency of the compressor.
4. The method of claim 1, wherein the combined optimization is performed by a multi-island genetic algorithm.
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Title
"叶珊非轴对称端壁成形技术的初步研究";李国君等;《工程热物理学报》;20060630;第27卷;第97-100页 *
"非对称端壁对扩压叶栅性能影响的数值研究";王睿;《中国优秀硕士学位论文全文数据库 工程科技Ⅱ辑》;20140615(第 06 期);第C031-46页 *
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