Structure and Topology Analysis of Separated Vortex in Forward-Swept Blade

Flow separation commonly affects the stability of turbomachines, especially under low-flowrate conditions. Compared with conventional blades, a forward-swept blade is more efficient at high flowrates. However, experiments and numerical simulations show that a forward-swept blade produces an unstable region under low flowrate. In this paper, the topological analysis is used to analyze the structure and size of flow separation in forward swept blades. Three-dimensional structure and formation mechanism of vortices in forward-swept blades are analyzed using the cross-section flow pattern method. For forward-swept blades, flow separation mainly occurs at the blade tip and corner, accompanied by clear velocity fluctuations, the break-up of shed vortices, and diffusion. With decreasing flowrate, the shedding vortices move forward and the speed of vortex annihilation gradually decreases. In addition, the number of singularities in the rotor passage increases with the decrease of flow rate, and the region affected by shedding vortex increases. The rotating direction of internal vortex in turbomachinery is fixed. The pressure surface, passage vortex, and concentrated shedding vortex were found to rotate clockwise, whereas the suction surface, corner vortex, and shedding vortex rotate in a counterclockwise direction.

Introduction

With the development of manufacturing technology and numerical analysis software, three-dimensional blades are being increasingly used in axial turbomachines. Since the 1960s, the blade curve formation theory proposed by References (Filippov and Wang, 1962; Wang et al., 1981; Wang, 1999) has provided theoretical guidance for the design of three-dimensional blades. More recently, forward-swept blades have been mentioned (Wennerstrom and Puterbaugh, 1984; Wennerstrom, 1990) in the context of experimental transonic compressors. Experimental results show that forward-swept blades maintain high efficiency at the tip of the cascade at high speeds. Mohammed and Raj (1977) designed forward-swept blades for a low-speed compressor rotor, optimizing the flow separation at the tip of the suction surface and improving the characteristics of the compressor. Vad et al. (2015) comprehensively described the characteristics of forward-swept blades. Combining straight blades and forward-swept blades can increase the efficiency of the fan by 2–3%, although for free-vortex rotors, there is little improvement in efficiency(He et al., 2018; Kaya et al., 2018).

Flow separation, which frequently occurs in the flow around various objects, is a complex flow phenomenon in fluid mechanics, and has been extensively studied along with its associated flow characteristics. Three-dimensional flow separation theory, first proposed by Maskell (1955) and Lighthill (1963), represents the cornerstone of such studies. Thereafter, bubble separation, free vortex separation, open separation, and closed separation configurations were investigated. References (Zhang and Deng, 1992; Zhang, 1994; Zhang, 1997) obtained the flow distributions of multiple cross-sections from experiments and calculations, and derived distribution rules for semi-singularities on cross-sectional contour lines and topological rules for determining the total number of different flows. Surana et al. (2006) developed a three-dimensional steady separation and reattachment theory using nonlinear dynamical systems, and obtained the separation point and separation line criteria under no-slip boundary conditions in a compressible flow. Gbadebo et al. (2005) adopted the limit streamline topology method and nonlinear dynamics to obtain the relationship between the inlet angle, boundary layer, and separation point. This method provided a new way of interpreting and researching flow separation theory.

The internal flow, boundary layer separation, and stall/instability conditions of turbomachines can be studied using experimental methods and numerical simulations. Karyakin et al. (2018); Zhang et al. (2018) used the tuft method and oil-flow method, respectively, to conduct experiments on flow separation control around isolated airfoils. However, few studies have applied these experimental methods to rotor flow separation. Taking the oil-flow method as an example, the uniform paint applied on the blade is subjected to two forces, namely the shear force from the airflow and the inertial centrifugal force ${\omega }^2\overrightarrow{R}$ from the rotation of the blade itself. By using sophisticated numerical simulations, detailed flow field information can be revealed. Zhang et al. (2007) used the NUMECA numerical calculation software to analyze the separation characteristics and vortex structure of the front bending cascade of an axial compressor at different incidence angles. In addition, References (Chen et al., 2013; Ye et al., 2013; Jongwook et al., 2016;Pogorelov et al., 2016; Luo et al., 2017) have conducted detailed analyses of the flow field characteristics of axial flow turbomachines. Drózdz (2021) from the view of boundary layer, the relationship between Reynolds number and flow separation is discussed. Cao (2019) studied the effect of flow rate on flow separation of last stage blade of steam turbine. The results show that the flow separation vortices appear near last stage blade at 30% of the rated volume flow. With the decrease of volume flow, the flow separation vortices gradually spread to the root of blade.

Numerical simulations and experimental methods cannot, however, fully explain the law of flow separation, especially for forward-swept blade flow separation, which is still at the early stages of investigation. In this paper, the Navier–Stokes equations for internal flow in turbomachines are analyzed and the flow field on the blade surface of a forward-swept fan is investigated. The singularity characteristics of the blade surface separation are analyzed using a topological approach. The flow separation is explored in three-dimensional space using a topological-mapping method. The aim of this work is to determine the influence of forward-swept blades on the flow separation of axial flow turbomachines, and to provide a foundation for studying the control of flow separation.

Mathematical Model

In the study of Lighthill (1963), the limit streamline is equal to the friction line:

$\frac{\text{d}y}{\text{d}x}=\frac{v}{u}=\frac{{\tau }_{wy}}{{\tau }_{wz}}(1)$

As can be seen from Eq. 1, the direction of the limit streamline is the same as that of the friction line. The limit streamline and the friction line are considered to be equivalent in most studies. In cascade experiments, the oil-flow method and the surface silk-line method can reveal the boundary layer flow state to an adequate degree of accuracy. The frictional line can be transformed into:

$\{ \begin{array}{c}\frac{\text{d}x}{\text{d}t}=\frac{\partial {\tau }_{xw}}{\partial x}x+\frac{\partial {\tau }_{xw}}{\partial y}y\\ \frac{\text{d}y}{\text{d}t}=\frac{\partial {\tau }_{yw}}{\partial x}x+\frac{\partial {\tau }_{yw}}{\partial y}y\end{array}=\left[\begin{array}{cc}\frac{\partial {\tau }_{xw}}{\partial x}& \frac{\partial {\tau }_{xw}}{\partial y}\\ \frac{\partial {\tau }_{yw}}{\partial x}& \frac{\partial {\tau }_{yw}}{\partial y}\end{array}\right]\left[\begin{array}{c}x\\ y\end{array}\right](2)$

According to the theory of phase-plane analysis for ordinary differential equations, the shape and type of friction lines at critical points depend on the properties of the eigenvalues of the 2 × 2 Jacobian matrix. The critical points can be classified by the surface streamlines nearby, which are determined by trace p and det q of the matrix. The characteristic roots ${\lambda }_{\mathrm{1,2}}$ vary with position; in theory, all the critical points can occur. The singularities in the $\left(p,q\right)$ phase space are mainly composed of saddle points (S), nodes (N), and focus points (F). A change in position causes a change in $\nabla \tau$ and, correspondingly, modifies the positive and negative distributions of the eigenvalues and the terms of the discriminant $\Delta =\sqrt{p^2-4q}$, leading to a different singularity distribution, as shown in Figure 1. The quantities $p$, $q$, and ${\lambda }_{\mathrm{1,2}}$ are given by:

$p=\frac{\partial {\tau }_{xw}}{\partial x}+\frac{\partial {\tau }_{yw}}{\partial y}(3)$

$q=\frac{\partial {\tau }_{xw}}{\partial x}\frac{\partial {\tau }_{yw}}{\partial y}-\frac{\partial {\tau }_{xw}}{\partial y}\frac{\partial {\tau }_{yw}}{\partial x}(4)$

${\lambda }_{\mathrm{1,2}}=\left(p\pm \sqrt{p^2-4q}\right)/2(5)$

FIGURE 1

FIGURE 1. $\left(p,q\right)$ phase space.

Figure 1 shows an idealized linear phase space diagram with all of the patterns and distribution of limit streamlines that can appear on the object surface: when $q<0$, the singularities are node points, when $q>0$ and $p^2-4q>0$, they are saddle points, and when $p^2-4q<0$, they are focus points.

Experimental Model and Research Method

Experimental Model

An experimental device is often used to evaluate the performance of axial flow fans. Pressure sensors are installed at the outlet of the collector and the entrance of the fan. A data collector is used to record pressure signals and motor parameters. The hub ratio of the fan is 0.4, the speed is 980–990 rpm, the outer diameter is 1,600 mm, the length of the intake duct is 4,000 mm, and the measuring length is 4,815 mm. We designed and manufactured the forward-swept blades ourselves, with the blade parameters shown in Figure 2 and Table 1. The total height of blade is 480 mm, of which 60% is straight blade, 40% is swept forward blade, and forward swept angle is 20°.

FIGURE 2

FIGURE 2. Parameters of the forward-swept blade.

TABLE 1

TABLE 1. Specific blade parameter values.

Numerical model

ANSYS computational fluid dynamics X (ANSYS CFX) was used to simulate the whole flow passage at the fan. The physical model was divided into three areas: the inlet and outlet ducts and the experimental fan itself. The blade was meshed using Auto-Grid. An H-block was adopted for the inlet and outlet parts, with an O-block for the blade part, as shown in Figure 3. The quality of the grid is an important factor in the accuracy of the simulation results, and $y^{+}$ is an important parameter for measuring how well the grid and the turbulence model coordinate with each other. The thickness of the first layer grid was calculated to be $\Delta \text{s}=0.6\times {10}^{-3}\text{mm}$, ensuring that the $y^{+}$ value was less than 1. The boundary conditions, turbulence model, solution accuracy, and convergence criterion are presented in Table 2.

FIGURE 3

FIGURE 3. Computational mesh of forward-swept fan.

TABLE 2

TABLE 2. Boundary conditions and convergence criteria for computation.

To eliminate the influence of the number of grid cells on the numerical results, four different grid resolutions were selected for calculation. The SST $\text{k}-\omega$ model includes a modified turbulent viscosity formula to simulate the transport effect caused by turbulent shear stress, and a reasonably accurate solution can be obtained for separated flow. Therefore, the SST $\text{k}-\omega$ model was selected as the basis of the flow separation calculations under low-flowrate conditions. For this grid independence verification, the shear-stress transport (SST) $\text{k}-\omega$ turbulence model was used and the $Q_v-P_{total}$ curves were plotted under different conditions. As shown in Figure 4A, as the number of grid cells increases, the calculated total pressure of the fan gradually increases. When the number of grid cells reaches 220, 000, this upward trend is no longer obvious. This indicates that the number of grid cells no longer has an impact on the calculation results. Thus, the final number of grid cells was set to 220, 000. As shown in Figure 4B, the maximum error between the experimental results and the numerical simulation results is less than 5%, which meets the requirements of model validation.

FIGURE 4

FIGURE 4. Model validation (A) Mesh independent verification (B) Numerical simulation and experimental data.

Results and Analysis

Topological Analysis of Flow Separation

From Figure 1, it can be seen that the singularity type of the phase space diagram formed by the surface streamlines is independent of the time term, but is related to the eigenvalue $\left(p,q\right)$. Therefore, to study the distribution of the phase space diagram formed by the surface streamline equation, the streamline distribution is analyzed at a fixed time. Figure 5 shows the numerical results for the forward-swept blade with a flowrate of 0.65 Q_v. at T = 0.165 s.

FIGURE 5

FIGURE 5. Streamline at single channel region in (A) leading edge and trailing edge, (B) hub and blade, and (C) top of blade.

Because of the relative motion between the blade and the flow field, the streamline aligns well with the wall and no flow separation occurs on the pressure surface of the blade. The streamline is significantly deflected by the suction surface of the blade; this is caused by the change of flow direction and the circumferential pressure gradient at the suction surface. According to the separation morphology, the separation starting point lies on the hub and cannot be seen, and closed separation occurs for the passage vortices. The starting point of the separation on the suction surface is a saddle point, and the subsequent separation is a free vortex separation, which is close to open separation. The flow separates at a position 35% along the chord length and enters the mainstream before forming a vortex downstream; coupling of the hub and wall fluid boundary layers also occurs.

The hydrodynamic system in the rotor is nonlinear due to the unsteady working conditions. Many singularities appear on the hub and suction surface, and these influence the detailed fluid motion. Taking the local single passage in the rotor region as an example, the fluid enters from a large distance and no singularity appears on the separation line at the hub. The first group of singularities (saddle nodes) appears at the leading edge of the blade. There is a large corner separation coupling area between the suction surface and the hub, which affects the suction surface of the blade and the streamline at the hub. On the pressure surface, the streamline begins to shift upward from the middle position, and saddle point S2 appears. The limit friction line terminates at the trailing edge of the blade, as shown in Figure 5A. The starting point of separation in this region is saddle point S2, and the separation terminates at tail edge node N2. As they are affected by the corner separation vortices, the larger separation vortices appear at the position where the suction surface streamline deviates, and the separation vortices form focus point F3 on the streamline at the hub.

The separation eddy line comes from two directions: the streamline near the suction leading edge of the blade and saddle point S3 at the hub on the trailing edge of the blade. During the analysis process, saddle point S4 was only found at the trailing edge of the blade and no matching singularity was found, which is inconsistent with the theoretical analysis. By encrypting the streamlines, a separate focus point F4 was found at the junction of the pressure surface and suction surface on the trailing edge of the blade. Finally, the separation at the tip of the blade covers the region from the beginning of saddle point S5 in the middle of the blade to the end of focus point F5 near the trailing edge.

According to the principle of topological invariance, separated saddle points and attachment points (S1–N1) appear near the leading edge of the hub in a single passage near the blade. A saddle–node combination (S2–N2) is formed between saddle point S2 on the trailing edge and node N2 on the trailing edge. A saddle point–focus point pairing (S3–F3) occurs in the mainstream of the suction surface, and finally focus point F4 and saddle point S4 (S4–F4) combine near the root of the trailing edge of the blade. A separation saddle point S5 from the tip of the blade connects with focus point F5 at the trailing edge to form a saddle point–focus point pairing (S5–F5). Through analysis of the topological structure, it is found that the numbers of saddle and node pairs are the same in the single passage region, which is in good agreement with the theory of topological invariance.

Singularity Distribution on Forward-Swept Blade

When the limit streamline is a separation line, the distribution and coordination mode of the singularities on the separation line can be obtained by Taylor expansion. The frictional line equations can be expanded based on Taylor’s formula at the origin of the object surface:

$\{\begin{array}{c}\left(\partial u/\partial z\right)=xg+o^3\\ \left(\partial v/\partial z\right)=xh+f+o^3\end{array}(6)$

$\{\begin{array}{l}g=a_0+a_{1}x+a_{2}y\hfill \\ f=b_0+b_{2}y+b_5{y}^2\hfill \\ h=b_1+b_{3}x+b_{4}y\hfill \end{array}(7)$

$\begin{array}{ccc}{a}_0=\frac{{\partial }^{2}u}{\partial x\partial z}& a_1=\frac{1}{2}\frac{{\partial }^{3}u}{\partial x^2\partial z}& a_2=\frac{{\partial }^{3}u}{\partial x\partial y\partial z}\\ b_0=\frac{\partial v}{\partial z}& b_1=\frac{{\partial }^{2}v}{\partial x\partial z}& b_2=\frac{{\partial }^{2}v}{\partial y\partial z}\\ b_3=\frac{{\partial }^{3}v}{\partial x^2\partial z}& b_4=\frac{{\partial }^{3}v}{\partial x\partial y\partial z}& b_5=\frac{{\partial }^{3}v}{\partial y^2\partial z}\end{array}(8)$

$\frac{\text{d}y}{\text{d}x}\mathrm{=}\frac{xh\mathrm{+}f}{xg}(9)$

The singularity of the solution to the surface friction line is given by:

$\{\begin{array}{c}x=0\\ f=0\end{array},\{\begin{array}{c}g=0\\ xh+f=0\end{array}(10)$

$\{\begin{array}{c}{y}_1=C_1=\frac{-b_2+\sqrt{b_2^2-4b_0{b}_5}}{2b_5}\\ y_2=C_2=\frac{-b_2-\sqrt{b_2^2-4b_0{b}_5}}{2b_5}\end{array}(11)$

In Eq. 10, when $f=0$, $y$ has different combinations and distributions of solutions. Along the separation streamline, the phase space diagram of the singularities will change with position. By analyzing the changes in the discriminant and solution $C_{\mathrm{1,2}}$, the solution distribution and spatial topological structure can be determined, as shown in Figure 6.

FIGURE 6

FIGURE 6. Nonlinear solutions and singularity combinations when (A)$\Delta >0,b_2>0$, (B)$\Delta >0,b_2<0$, and (C)$\Delta <0,b_2>0$.

As shown in Figure 6A, the separation streamline has two singularities: $\left(0,C_1\right)$and $\left(0,C_2\right)$. At this time, $b_5=\left({\partial }^{2}f/\partial y^2\right)>0$, $b_2^2-4b_0{b}_5>0$. Performing a coordinate transformation on points $C_1$ and $C_2$ on the separation streamline (move to the origin, Eq. 12) and substituting into Eq. 2 yields:

$\begin{array}{l}\zeta =x\\ {\eta }_{\mathrm{1,2}}=y-C_1,y-C_2\end{array}(12)$

$\begin{array}{l}\left[\begin{array}{c}{\dot{\eta }}_1\\ \dot{\zeta }\end{array}\right]=\left[\begin{array}{cc}{k}_{11}& k_{12}\\ k_{21}& 0\end{array}\right]\left[\begin{array}{c}{\eta }_1\\ {\zeta }_1\end{array}\right]\\ \left[\begin{array}{c}{\dot{\eta }}_2\\ \dot{\zeta }\end{array}\right]=\left[\begin{array}{cc}{k^{\prime }}_{\mathrm{11}}& {k^{\prime }}_{12}\\ {k^{\prime }}_{21}& 0\end{array}\right]\left[\begin{array}{c}{\eta }_2\\ {\zeta }_2\end{array}\right]\end{array}(13)$

where $k_{11}=b_1+b_4{C}_1$, ${k^{\prime }}_{11}=b_1+b_4{C}_2$, $k_{12}={k^{\prime }}_{12}=b_2$,$k_{21}=a_0+a_2{C}_1$, ${k^{\prime }}_{21}=a_0+a_2{C}_2$. For point $C_1$, $k_{21}=a_0+a_2{C}_1<0$ can be derived from the separation condition. The slope of the curve near point $C_1$ is greater than 0, so ${\text{b}}_2>0$. Substituting this into $q=k_{12}{k}_{21}<0$, it can be inferred that singularity $C_1$ is a saddle point. Figure 6B can be obtained in the same way. The separation line begins at the saddle point and ends at the node or focus point when $\Delta >0,b_2<0$. When the equation has a featureless solution, the separation appears as a featureless critical situation. Figure 6C represents the normal limit friction line when $\Delta <0,b_2>0$.

Flow separation occurs because the boundary layer leaves the blade and enters the mainstream, finally forming a free vortex surface. During the formation and development process, there is a change in the eigenvalues on the suction surface of the blade and hub due to, for example, changes in the wall reverse velocity gradient and the wall separation point. Figure 7 shows the topological structure and reverse flow (blue area) on the hub and blade surface at 0.65 Q_v. The first and second groups of singularities start from a saddle point and end at a node point, which is consistent with the combination form of the singularity in Figure 6B. Combined with Figure 7, it can be seen that saddle points S1 and S2 flow from the blue area to the red area, which means that $\partial w/\partial x$ increases at the saddle point position along the streamline direction, and the saddle point is $C_1$ in Figure 6B. In the same way, we can determine that the node is $C_2$. The third and fourth groups of singular points start from the focus point and move to the saddle point, and the matching mode is consistent with the singularity combination mode in Figure 6A. Combined with Figure 7, it can be observed that the area near point F3 changes from blue to red along the streamline direction—the focus point is $C_2$ in Figure 6A and the saddle point is $C_1$.

FIGURE 7

FIGURE 7. Contours of ${\text{C}}_p$ and limit streamline.

Generally, the separation line is composed of a saddle point and the focus node. The location and type of the singularity can be quickly defined by the velocity gradient and streamline on the surface, as shown in Figure 8. There are three kinds of $\partial \tau /\partial y$ values on the separation line: when the limit streamline has an adverse velocity gradient, the sign of $\partial \tau /\partial y$ changes. Combining the types of separation points on the hub and suction surfaces with Figure 7, we find that the appearance of a reversed velocity gradient on the blade surface indicates the appearance of the singularity. Whether the fluid flows from A to B or from B to A, $\partial \tau /\partial y\mathrm{>}0$ indicates the saddle point and $\partial \tau /\partial y<0$indicates the node point. Therefore, the eigenvalues $\partial \tau /\partial y$ represent the characteristics in the fluid flow.

FIGURE 8

FIGURE 8. Shear stress distribution on the limit streamline.

Spatial Evolution of Separation Vortex Structure

In the steady state, the streamline coincides with the path line. The structure and shape of the separation vortices can gradually be revealed by taking successive cross-sections. Firstly, different planes are selected along the blade height, and the three-dimensional flow field information is obtained by plotting the streamline topology intercepted by each plane. When using the cross-section streamline method to analyze vortex structures away from the wall, the selected surface should be parallel to the surface of study. This paper selects the suction surface and performs a radial translation $\Delta \text{y}$ [the y direction is given in Figure 5B]. The translated surface is input to CFD-Post to observe the surface streamlines. By comparing the dissipation process of the vortex on the hub and the vortex on the tip of the blade, it can be seen that the process of vortex dissipation at the tip of the blade is not accompanied by the rupturing of the vortex, as shown in Figure 9. Note that the dissipation process of the vortex occurs along the mainstream direction.

FIGURE 9

FIGURE 9. Blade streamline topology at (A)$\Delta \text{y}=0\text{mm}$, (B)$\Delta \text{y}=10\text{mm}$, (C)$\Delta \text{y}=20\text{mm}$, and (D)$\Delta \text{y}=30\text{mm}$.

The separation vortex structure on the hub surface can be analyzed by the same method (see Figure 10). On the plane at the hub (0% Span), there is only one shedding vortex at the suction surface, and its core position is 0.23 m away from the fan rotor entrance. With an increase in height (1% Span), two separated vortices grow in the region, located 0.18 and 0.25 m away from the rotor inlet of the fan. When the height reaches 2% Span, the shedding vortices at point B near the suction surface gradually shrink and diffuse into the mainstream. The core of the shedding vortices is at point A, 0.21 m from the rotor inlet, and finally appears at 5% Span; here, the shedding vortices at point B are completely annihilated in the mainstream, leaving only the shedding vortices at point A. The eddy is 0.24 m away from the fan entrance.

FIGURE 10

FIGURE 10. Streamline topology at (A) 0% Span, (B) 1% Span, (C) 2% Span, and (D) 5% Span.

Figure 11 shows the streamlines in the impeller region at 0.625${\text{Q}}_v$. The black part is the streamline on the hub surface and the colored part is the three-dimensional streamline. Two vortices can be observed in the passage through the three-dimensional streamline, in which lines 1 and 2 come from the leading edge and lines 3–8 come from the hub surface. According to Figure 5, lines 1 and 2 are the extensions of a leading-edge horseshoe vortex, which leaves the hub surface near the leading edge and enters the region; lines 3–8 originate from the hub surface and leave the wall at the focus point to form a separation vortex.

FIGURE 11

FIGURE 11. Streamlines in the impeller region.

According to Figures 10, 11, the shedding vortices formed on the hub surface disappear with the mainstream, and the positions of the vortex cores in different sections move along the streamline continuously. The shedding vortices break up and diffuse into the mainstream until they dissipate completely. As the flowrate decreases, the influence of the mainstream on the structure of the vortex gradually weakens, and the velocity and location of the vortex breakdown on the hub wall changes, as shown in Figure 12.

FIGURE 12

FIGURE 12. Eddy dissipation at different flowrates.

Variation of Separated Vortex Structure With Flow Rate

The topological structure of the rotor is not invariant under changes in flowrate, as shown in Figure 13. When the flowrate is 1 Q_v, there are only two groups of singularities in the region (red line). When the flowrate decreases to 0.8 Q_v, singularity F3–S3 grows on the hub and S2–N2 appears on the suction surface. When the flowrate is further reduced to 0.625 Q_v, separation begins at the blade tip and a new singularity S5–F5 appears. When the flowrate is 0.5 Q_v, a new singularity S6–F6 appears on the hub.

FIGURE 13

FIGURE 13. Topology under different flowrates.

The passage vortex structure can be inferred from the topological structure and cross-section flow pattern distribution, combined with the spatial streamline distribution, as shown in Figure 14B. Along the flow direction, the fluid forms a horseshoe vortex (HV) near the leading edge. According to Figure 9B, the horseshoe vortex is separated into two parts by the leading edge. The bifurcation of the passage vortex on the pressure surface (HP) rotates clockwise [as shown in Figure 14A, Z/C = 0], and finally converges with the passage vortex to form a single structure. Through local magnification, it can be observed that there is a counterclockwise-rotating vortex near the suction surface of the leading edge, which is the bifurcation of the passage vortex on the suction surface (HS). The passage vortex (PV) rotates clockwise and gradually approaches the suction surface as the flowrate decreases. In the vicinity of the suction surface, the corner vortex (CV) formed by the counter current in the region rotates counterclockwise. The shedding vortex (SV) near the trailing edge is caused by the pressure difference when the pressure surface meets the suction surface fluid. The direction of motion is from the pressure surface to the suction surface, and the rotation direction is counterclockwise. A clockwise-rotating concentrated shedding vortex (CSV) is formed by the boundary layer movement in the corner of the suction surface of the blade top.

FIGURE 14

FIGURE 14. Spatial structure of vortex system.

Conclusion

(1) The combinations of different singularities were obtained through a qualitative analysis of the limit friction line on the wall. The method accurately obtains the wake vortices formed by the convergence of the suction surface and pressure surface fluid at the trailing edge of the blade. The flow on the forward-swept blade also follows the principle of topological invariance. The single blade and its adjacent flow passage can be regarded as a closed region. When there is no tip clearance, the Euler characteristic is 0. Through this method, five saddle points, two nodes, and three focus points were found by analyzing the singularities near the runner and the blade.

(2) By taking the Taylor expansion of the governing equation of the limit streamline, the distribution of singular points along the separation line was obtained. Because the change in $f\approx \partial v/\partial z+o^2$ along the y-axis is continuous, there are multiple intersections between $f$ and the y-axis, and the slope $\partial \tau /\partial y$ at the adjacent intersection points must be positive and negative, which leads to changes between saddle points and nodes. When$\partial \tau /\partial y\mathrm{>}0$, a saddle point occurs, and when $\partial \tau /\partial y<0$, a node point occurs. In fluid flow, a change in sign represents the appearance of a countercurrent region. This type of singularity can be obtained by analyzing the intersection point of the countercurrent contour and the limit streamline.

(3) The dynamical state of separation vortices on the hub was analyzed using cross-section streamline analysis. As the height increases, the separation vortices break up and are annihilated, and the position of the vortex core moves along the streamline. Changes in flowrate also affect the suction boundary.

(4) With decreasing flowrate, the number of groups of singularities in the region increases, and the combinations of singularities are more abundant. In addition, the section flow pattern method can be used to infer the vortex structure and rotation direction. Numerical simulations show that larger PV and CV are produced, while the CSV and HV are smaller. The HP, PV, and CSV were found to rotate clockwise, whereas the HS, CV, and SV rotate in a counterclockwise direction.

Data Availability Statement

The original contributions presented in the study are included in the article/Supplementary Material, further inquiries can be directed to the corresponding authors.

Author Contributions

YL and ZZ provided experimental ideas and theoretical guidance. PW and SD provided language guidance and writing guidance.

Funding

This work was supported by the National Natural Science Foundation of China (Grant No. 51776217) and the China Scholarship Council (Grant No. 201806425052).

Conflict of Interest

The authors declare that the research was conducted in the absence of any commercial or financial relationships that could be construed as a potential conflict of interest.

Abbreviations

$C_p$, pressure coefficient $\left(P-P_0\right)/\left(1/2\rho {\stackrel{\rightharpoonup }{U}}^2\right)$; $f$, blade frequency; $\text{F}$, focus points; $L$, chord length; $n$, rotational speed; $\text{N}$, node points; $Q_v$, Mass flowrates; $\text{S}$, saddle points; $u$, velocity component in the x direction; $v$, velocity component in the y direction; $w$, velocity component in the z direction; $y^{+}$, wall function $\left(\rho u_{t}y/\mu \right)$; $Z_Y$, total number of blades; $\alpha$, singular point integral angle; $\lambda$, eigenvalues; $\theta$, installation angle; $\mu$, dynamic viscosity; $\tau$, shear stress; $\omega$, angular velocity; $\eta$, fan efficiency $\left(\left(P_{Total}\cdot Q_v/\mathrm{1,000}\cdot \mathrm{3,600}\right)/\pi \cdot torque\cdot n\cdot \mathrm{360,000}\right)$

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