# Numerical Simulation of Impact Loads of Main Fan Blades in Gas Explosion

Authors: Jianliang Gao; Jingzhang Ren; Xuebo Zhang; Jiajia Liu; Chunxia Wang
Journal: Shock and Vibration
 (2020)

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## Abstract

The shock wave generated by a severe gas explosion accident can damage the main fan, and the toxic and harmful gases in the well cannot be discharged in time, leading to the expansion of disaster accidents. Therefore, it is meaningful to study impact loads of main fan blades in gas explosion. In this paper, a full-scale three-dimensional numerical simulation model has been established based on No. 2 Yangchangwan Coal Mine in China. The propagation of shock wave in shaft and air tunnel and the dynamic process of main fan blade subjected to shock load when gas explosion of different volume occurs in heading face have been simulated. The overpressure on the blade at different times, the overpressure distribution on the blade, and the relationship between the overpressure and the explosion intensity have been obtained. The results showed that the time when the explosion shock wave reached, each blade of the wind turbine was basically the same, and the time when each blade reached, the maximum overpressure was basically the same. With the increase of gas explosion volume, occurrence time of overpressure and maximum overpressure time on the fan blade were shortened, and the time interval between them was also shortened. There is a little difference in the overpressure of each blade. Fan blade directly above the hub was subject to the highest overpressure, and fan blade directly below the hub was subject to the lowest overpressure. The overpressure of the maximum overpressure blade was 5.44% to 6.77% higher than that of the minimum overpressure blade. The distribution of overpressure on each fan blade was uneven, and the overpressures on blade edges were the lowest. The overpressure on the fan blades showed a corrugated distribution along the radial direction. There was 12.06% to 15.40% difference between the maximum and minimum overpressure section on the fan blade.


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## Body

## 1. Introduction

The frequent occurrence of coal mine gas accidents, especially large gas explosions, poses a great threat to the safety of national property and people and seriously affects the healthy development of the coal industry. Gas explosions in laneway are a significant concern because of the extent to which they may harm personnel, equipment, and the production process [1]. Especially, explosion can turn deflagration into detonation in certain conditions [2–5], which would lead to much destruction. After the explosion in a coal mine, a large amount of toxic gases such as carbon monoxide will be generated. The explosion shock wave propagates along the return air route, which may cause the destruction of the main fan blades, resulting in airflow disorder of the entire ventilation system, and a large number of people in the underground will be poisoned or suffocated. Therefore, it is of great significance to study the propagation process of the blast wave in shaft and wind tunnel and the dynamic process of main fan blades under impact load when gas explosion occurs in the underground working face.Xu et al. carried out the tunnel test research of gas explosion propagation in the mine [6]. Zhang et al. [7, 8] used numerical simulation method and explored the law of shock wave propagation through laneway bend and pressure distribution. The result showed that the attenuation of peak overpressure with distance did not obey the exponent law when the air shock wave goes through the laneway bend. The distribution of overpressure in the bending area was uneven. Hou et al. [9] studied the propagation and attenuation of shock waves in simplex turn roadway during gas explosion by numerical simulation and showed that the parameters of the shock wave in the turning roadway were attenuated during the propagation process. Jia et al. [10] carried out a study on the propagation characteristics of the gas explosion shock wave at the corner of the roadway. The result showed that when the shock wave went through the corner of the pipe, a complex flow field was generated. The greater the angle of the pipe bend and the greater the initial pressure of the shock wave, the more complex the reflection of the shock wave and the faster the shock wave attenuation. Lin and others simulated the tunnel structure and wall conditions of underground bifurcations, turns, and so on and conducted a systematic study on the propagation characteristics of flame waves and explosion waves in a gas explosion [11–13]. Zhu et al. [14] studied three angles of bending, and the results showed that the smaller the bending angle, the stronger the reflection of the shock wave, the stronger the turbulence caused, and the greater the peak overpressure formed. Blanchard et al. [15] studied the explosions in pipes containing baffles and a 90 bend. The results show that a 90 bend in a long tube has the ability to enhance flame speeds and overpressures and shorten the run-up distance to DDT to a varying degree for a number of gases. Ma et al. [16] studied the propagation characteristics of methane explosions in pipe networks using numerical simulation methods. The result showed that, in the parallel pipe network, the peak overpressure increased significantly at the intersection point, while the flame speed decreased at the junction. The above research shows that the current research methods can be divided into experimental methods and numerical simulation methods. Previous research has focused on the explosion of methane-air mixtures in small-scale vessels and their parameters [17–20], and the propagation of gas explosion shock waves in the tunnel has a scale effect [21, 22]. Large-scale tests are not easy to carry out under the influence of conditions. Due to the improvement of computer’s computing capabilities, the numerical simulation method has the characteristics of flexible settings, fewer consumables, and the ability to simulate wells and lanes of different sizes. At present, there are more studies on the propagation law of gas explosion shock waves in wells and lanes and little research on the shock load of main fans in gas explosions. FLUENT is now a popular commercial CFD software package in the international market. As long as it involves engineering issues, fluids, heat transfer, and chemical reactions can be explained [23]. In this paper, a full-scale three-dimensional numerical simulation model is established. The dynamic process of fan blades subjected to shock loads is simulated. Through simulation analysis, the change rule of the overpressure of the fan blades with time was the same. We determined the largest and smallest blades withstanding to overpressure and obtained the distribution characteristics of overpressure along the blade.


## 2. Materials and Methods

### 2.1. Mathematical Model

The blast wave generated after the gas explosion on the driving face propagates along the return airway to the shaft and then in the shaft to the wind tunnel and acts on the fan blades. During the entire propagation process, there are both flame propagation and pressure waves in the section near the explosion source. Generally, the shaft is far away from the driving face. When a gas explosion occurs at the underground face, the flame can only propagate a certain distance, the flame cannot reach the shaft. Therefore, only shock wave propagates in return air tunnel, shaft, and wind tunnel. The author numerically simulated the explosion process of the gas at the driving face and the propagation process of the shock wave from the driving face along the return air into vertical shaft. The distribution of the explosion shock wave on the shaft section of the vertical shaft and the law of its variation with time were obtained. Based on this, this paper took Yangchangwan No. 2 return air shaft as an example to study the propagation process of gas explosion shock wave from the driving face to the shaft, along the shaft to the air tunnel, main fans, and the dynamic process of fan blades bearing shock loads. Therefore, the governing equations followed by shock wave propagation include continuity equations and momentum equations. The turbulence model is selected from the widely used standardk-ε model, and its expression as follows.The continuity equation is written as follows:(1)∂ρ∂t+∂∂xiρui=0.The momentum conservation equation is written as follows:(2)∂∂xiρuiuj=−∂p∂xi+∂∂xiμ+μt∂uj∂xi+∂ui∂xj.Thek equation is written as follows:(3)∂ρk∂t+∂ρkui∂xi=∂∂xjμ+μtσk+Gk−ρε.Theε equation is written as follows:(4)∂ρεt+∂ρεui∂xi=∂∂xjμ+μtσε+C1εεkGk−C2ερε2k,μt=Cuρk2ε,where xi is the coordinates in the directions x, y, and z, m; ui is the flow velocity x, y and z, m/s; ρ is roadway’s gas density (kg/m3), P is effective turbulent pressure, Pa; μ is the laminar flow viscosity coefficient, Pa·s; Gk is turbulent energy generation rate induced by time-averaged velocity gradient %; μt is the turbulent flow viscosity coefficient, Pa·s; k is turbulent energy (J), ε is the turbulent dissipation rate %C1ε, C2ε, Cu, σk, and σε is empirical constant (C1ε=1.44, C2ε=1.92, Cu = 0.09, σε=1.3, and σk=1.0).


### 2.2. Physical Model

The driving working face of 020611 return air tunnel of Yangchangwan No. 2 well was 518 m away from the bottom of the return air shaft, the depth of the return air shaft was 556 m, and the diameter of the shaft was 6 m. The vertical distance from the lower end of the connection between the wind tunnel and the shaft to the explosion-proof cover was 9.02 m. The fan model of the installed main fan was ANN-2660/1440, with a total of 16 blades, and the installation angle of the fan blades was 45°. The vertical distance of the fan blade from the outer wall of the well was 16.44 m. The geometric model is shown in Figures13.Figure 1
Geometric model of the heading face to the explosion-proof door and the wind shaft.Figure 2
Geometric dimension of wind tunnel (unit: mm). (a). (b).
(a)(b)Figure 3
Schematic diagram of three-dimensional full-scale geometric model.Ansys Fluent commercial software was used to numerically simulate the process of gas explosion wave propagation. The fan blades were static during the numerical simulation. The geometry model of wind shaft, wind tunnel, and explosion-proof door was built and meshed by Ansys 17.2 Workbench. In the process of simulation and settlement, unstructured grid was used for the irregular areas such as wind tunnel and fan, and structural grid was used for the shaft area.


### 2.3. Initial and Boundary Conditions

#### 2.3.1. Initial Conditions

(1)
The initial pressureP0 of the entire calculation area is 0 Pa relative to the atmospheric pressure(2)
The initial temperatureT0 is 298 K(3)
The initial speedV0 of the entire area is 0 m/s(4)
The entire area is filled with air


#### 2.3.2. Boundary Conditions

(1)
The outlet of the fan diffuser is set to pressure outlet, and the outlet pressure is set to 0 Pa relative to the atmospheric pressure.(2)
The bottom of the shaft is set to pressure inlet. Through the numerical simulation of the propagation process of the shock wave from the driving face along the return airflow to the shaft when the gas explosion occurred in the driving face, the distribution of the blast wave on the section of the shaft and the change rule with time under the condition of different gas explosion volume were obtained. The pressure distribution and time-varying rules are used as the boundary conditions of the inlet.(3)
Near wall surface used standard wall function.The grid size and time step size have great influence on the results of numerical simulation. In order to verify the accuracy of the CFD model, grid independence analysis and time independence verification should be carried out [24–27]. The overpressure distribution on the fan blades is not uniform. The average overpressure on the blade is denoted as P, and the maximum value of P with time is recorded as Pmax. The blade directly above the hub was chosen as the research object, and the changes of its Pmax under different grid sizes and time steps were studied. In this paper, four grid numbers were conducted to verify the grid independence, including 4143528, 6617838, 8884708, and 12048764. The time independence verification was conducted for four time steps of 0.0005 s, 0.001 s, 0.005 s, and 0.01 s.As we can see in Figure4, with the increase of grid numbers, Pmax increases gradually, but the increasing range decreases gradually. It can be assumed that the grid number of 6617838 reached grid independence. Therefore, in this paper, considering the computational efficiency, storage space, and accuracy, the grid number of 6617838 has been chosen as the calculation grid. It can be seen from Figure 5 that, as the time step decreases, Pmax between time steps gets closer and closer. And considering the amount of calculation, the time step size was selected as 0.001 s.Figure 4
Grid independence verification diagram.Figure 5
Time independence verification diagram.


## 2.1. Mathematical Model

The blast wave generated after the gas explosion on the driving face propagates along the return airway to the shaft and then in the shaft to the wind tunnel and acts on the fan blades. During the entire propagation process, there are both flame propagation and pressure waves in the section near the explosion source. Generally, the shaft is far away from the driving face. When a gas explosion occurs at the underground face, the flame can only propagate a certain distance, the flame cannot reach the shaft. Therefore, only shock wave propagates in return air tunnel, shaft, and wind tunnel. The author numerically simulated the explosion process of the gas at the driving face and the propagation process of the shock wave from the driving face along the return air into vertical shaft. The distribution of the explosion shock wave on the shaft section of the vertical shaft and the law of its variation with time were obtained. Based on this, this paper took Yangchangwan No. 2 return air shaft as an example to study the propagation process of gas explosion shock wave from the driving face to the shaft, along the shaft to the air tunnel, main fans, and the dynamic process of fan blades bearing shock loads. Therefore, the governing equations followed by shock wave propagation include continuity equations and momentum equations. The turbulence model is selected from the widely used standardk-ε model, and its expression as follows.The continuity equation is written as follows:(1)∂ρ∂t+∂∂xiρui=0.The momentum conservation equation is written as follows:(2)∂∂xiρuiuj=−∂p∂xi+∂∂xiμ+μt∂uj∂xi+∂ui∂xj.Thek equation is written as follows:(3)∂ρk∂t+∂ρkui∂xi=∂∂xjμ+μtσk+Gk−ρε.Theε equation is written as follows:(4)∂ρεt+∂ρεui∂xi=∂∂xjμ+μtσε+C1εεkGk−C2ερε2k,μt=Cuρk2ε,where xi is the coordinates in the directions x, y, and z, m; ui is the flow velocity x, y and z, m/s; ρ is roadway’s gas density (kg/m3), P is effective turbulent pressure, Pa; μ is the laminar flow viscosity coefficient, Pa·s; Gk is turbulent energy generation rate induced by time-averaged velocity gradient %; μt is the turbulent flow viscosity coefficient, Pa·s; k is turbulent energy (J), ε is the turbulent dissipation rate %C1ε, C2ε, Cu, σk, and σε is empirical constant (C1ε=1.44, C2ε=1.92, Cu = 0.09, σε=1.3, and σk=1.0).


## 2.2. Physical Model

The driving working face of 020611 return air tunnel of Yangchangwan No. 2 well was 518 m away from the bottom of the return air shaft, the depth of the return air shaft was 556 m, and the diameter of the shaft was 6 m. The vertical distance from the lower end of the connection between the wind tunnel and the shaft to the explosion-proof cover was 9.02 m. The fan model of the installed main fan was ANN-2660/1440, with a total of 16 blades, and the installation angle of the fan blades was 45°. The vertical distance of the fan blade from the outer wall of the well was 16.44 m. The geometric model is shown in Figures13.Figure 1
Geometric model of the heading face to the explosion-proof door and the wind shaft.Figure 2
Geometric dimension of wind tunnel (unit: mm). (a). (b).
(a)(b)Figure 3
Schematic diagram of three-dimensional full-scale geometric model.Ansys Fluent commercial software was used to numerically simulate the process of gas explosion wave propagation. The fan blades were static during the numerical simulation. The geometry model of wind shaft, wind tunnel, and explosion-proof door was built and meshed by Ansys 17.2 Workbench. In the process of simulation and settlement, unstructured grid was used for the irregular areas such as wind tunnel and fan, and structural grid was used for the shaft area.


## 2.3. Initial and Boundary Conditions

### 2.3.1. Initial Conditions

(1)
The initial pressureP0 of the entire calculation area is 0 Pa relative to the atmospheric pressure(2)
The initial temperatureT0 is 298 K(3)
The initial speedV0 of the entire area is 0 m/s(4)
The entire area is filled with air


### 2.3.2. Boundary Conditions

(1)
The outlet of the fan diffuser is set to pressure outlet, and the outlet pressure is set to 0 Pa relative to the atmospheric pressure.(2)
The bottom of the shaft is set to pressure inlet. Through the numerical simulation of the propagation process of the shock wave from the driving face along the return airflow to the shaft when the gas explosion occurred in the driving face, the distribution of the blast wave on the section of the shaft and the change rule with time under the condition of different gas explosion volume were obtained. The pressure distribution and time-varying rules are used as the boundary conditions of the inlet.(3)
Near wall surface used standard wall function.The grid size and time step size have great influence on the results of numerical simulation. In order to verify the accuracy of the CFD model, grid independence analysis and time independence verification should be carried out [24–27]. The overpressure distribution on the fan blades is not uniform. The average overpressure on the blade is denoted as P, and the maximum value of P with time is recorded as Pmax. The blade directly above the hub was chosen as the research object, and the changes of its Pmax under different grid sizes and time steps were studied. In this paper, four grid numbers were conducted to verify the grid independence, including 4143528, 6617838, 8884708, and 12048764. The time independence verification was conducted for four time steps of 0.0005 s, 0.001 s, 0.005 s, and 0.01 s.As we can see in Figure4, with the increase of grid numbers, Pmax increases gradually, but the increasing range decreases gradually. It can be assumed that the grid number of 6617838 reached grid independence. Therefore, in this paper, considering the computational efficiency, storage space, and accuracy, the grid number of 6617838 has been chosen as the calculation grid. It can be seen from Figure 5 that, as the time step decreases, Pmax between time steps gets closer and closer. And considering the amount of calculation, the time step size was selected as 0.001 s.Figure 4
Grid independence verification diagram.Figure 5
Time independence verification diagram.


## 2.3.1. Initial Conditions

(1)
The initial pressureP0 of the entire calculation area is 0 Pa relative to the atmospheric pressure(2)
The initial temperatureT0 is 298 K(3)
The initial speedV0 of the entire area is 0 m/s(4)
The entire area is filled with air


## 2.3.2. Boundary Conditions

(1)
The outlet of the fan diffuser is set to pressure outlet, and the outlet pressure is set to 0 Pa relative to the atmospheric pressure.(2)
The bottom of the shaft is set to pressure inlet. Through the numerical simulation of the propagation process of the shock wave from the driving face along the return airflow to the shaft when the gas explosion occurred in the driving face, the distribution of the blast wave on the section of the shaft and the change rule with time under the condition of different gas explosion volume were obtained. The pressure distribution and time-varying rules are used as the boundary conditions of the inlet.(3)
Near wall surface used standard wall function.The grid size and time step size have great influence on the results of numerical simulation. In order to verify the accuracy of the CFD model, grid independence analysis and time independence verification should be carried out [24–27]. The overpressure distribution on the fan blades is not uniform. The average overpressure on the blade is denoted as P, and the maximum value of P with time is recorded as Pmax. The blade directly above the hub was chosen as the research object, and the changes of its Pmax under different grid sizes and time steps were studied. In this paper, four grid numbers were conducted to verify the grid independence, including 4143528, 6617838, 8884708, and 12048764. The time independence verification was conducted for four time steps of 0.0005 s, 0.001 s, 0.005 s, and 0.01 s.As we can see in Figure4, with the increase of grid numbers, Pmax increases gradually, but the increasing range decreases gradually. It can be assumed that the grid number of 6617838 reached grid independence. Therefore, in this paper, considering the computational efficiency, storage space, and accuracy, the grid number of 6617838 has been chosen as the calculation grid. It can be seen from Figure 5 that, as the time step decreases, Pmax between time steps gets closer and closer. And considering the amount of calculation, the time step size was selected as 0.001 s.Figure 4
Grid independence verification diagram.Figure 5
Time independence verification diagram.


## 3. Results and Discussion

Blade 1 was directly above the hub. The shock wave generated by the gas with the concentration of 9.5% with a volume of 311.64 m3 propagated to the fan blade after the explosion of the driving face, and the distribution of shock wave overpressure on fan blades at different times was shown in Figure 6. It can be seen that when the shock wave propagated to the blades, the overpressure of 16 blades was not equal, and the change rule of the overpressure of 16 blades with time was basically the same.Figure 6
Cloud diagram of the overpressure change of the fan blade with time (V = 311.64 m3). (a) t = 0 m·s. (b) t = 153 m·s. (c) t = 193 m·s. (d) t = 204 m·s.
(a)(b)(c)(d)


### 3.1. Overpressure on Blades Changes with Time

The moment when overpressure starts to appear on the blades is recorded asT1. The moment when Pmax appears is recorded as T2, and T3 is the time interval between T2 and T1. The variation of P on blades 1, 5, 9, and 13 with time is shown in Figure 7. Variation of P on blades 1 with time under different gas explosion volume is shown in Figure 8.Figure 7
Variation ofP on blades 1, 5, 9, and 13 with different gas explosion volumes over time. (a) Volume = 31.16 m3. (b) Volume = 62.33 m3. (c) Volume = 115.82 m3. (d) Volume = 311.64 m3. (e) Volume = 779.11 m3.
(a)(b)(c)(d)(e)Figure 8
Time-varying graph ofP on blade 1 under different gas explosion volumes.It is not so hard to see from Figure7 that occurrence time of overpressure and maximum overpressure time on each blade were basically the same. Figure 8 shows that T1 and T2 decrease with the increase of gas explosion volume. As the intensity of gas explosion increases, the width of the peak becomes narrower and narrower, that is, T3 decreases as the volume of gas explosion increases. It is because that the shock wave generated by the larger gas explosion volume is stronger, and the shock wave speed is faster. The earlier the time T1 on the fan blade, the earlier the time T2 and the shorter the time interval T3 between T1 and T2


### 3.2. Maximum and Minimum Overpressure Blades

For different explosion gas volumes, when the gas explosion shock wave propagated to the fan blades, the maximum overpressurePmax experienced by each blade is shown in Figure 9. The maximum Pmax of the 16 blades was recorded as Pm, and the minimum Pmax was recorded as Pn. The Pm value and Pn value under different gas explosion volumes are shown in Table 1.Figure 9
Pmax on fan blades under different gas explosion volumes.Table 1
Pm and Pn under different gas explosion volumes.
Gas explosion volume (m3)Pm (Pa)Pn (Pa)Difference (%)33.16190417945.7862.33397337086.67155.8213701129555.44311.6421626203475.91779.1130832287816.65From Figure9 and Table 1, it can be seen that Pmax on each fan blade had little difference, blade 1 directly above the hub bore the maximum overpressure, and blade 9 directly below the hub bore the minimum overpressure, which was caused by the change of the propagation direction of the shock wave in the wind tunnel. Pm was 5.44–6.77% higher than Pn under different explosion gas volumes.The variation ofPm and Pn with explosion volume is shown in Figure 10. It can be seen that Pm and Pn increase with the increase of gas explosion volume, but the magnitude of the increase gradually decreases.Figure 10
Relationship betweenPm and Pn and gas explosion volume.


### 3.3. Distribution of Overpressure on the Blade

When the gas concentration was 9.5% and the explosion volume was 311.64 m3, the shock wave overpressure distribution at different moments on blade 1 located directly above the hub is shown in Figure 11. It can be seen that the distribution of overpressure on the blade was very uneven, and the blade edge bore the lowest overpressure and gradually increased from the edge to the inside.Figure 11
Cloud chart of pressure change with time of blade 1 when gas explosion volume was 311.64 m3. (a) t = 0 m·s. (b) t = 153 m·s. (c) t = 193 m·s. (d) t = 204 m·s.
(a)(b)(c)(d)The blade was divided into 10 segments from the root to the tip in the radial direction (the total length of the bladeH is 630 mm, and the length of each segment h is 63 mm). The overpressure value of the segment with the highest overpressure was recorded as PLM, and the overpressure value of the segment with the lowest overpressure was recorded as PLN. When blade 1 reached Pmax, the distribution of the overpressure on the blade along the radial direction is shown in Figure 12, and PLM and PLN on the blade 1 under different gas explosion volumes are shown in Table 2.Figure 12
Overpressure distribution in the radial direction of blade 1 under different explosion volumes.Table 2
PLM and PLN on blade 1 under different gas explosion volumes.
Gas explosion volume (m3)Maximum valueMinimum valueDifference (%)(Pa)(Pa)33.161968167215.0462.334095349614.6377.915606477614.81155.82140441235012.06311.64221541917813.43779.11315832672015.40Figure12 showed that the overpressure on the fan blades showed a corrugated distribution in the radial direction, but the change range was not large. From Table 2, it can be seen that, under different gas explosion volumes, the overpressure value PLM of the segment with the largest overpressure in the radial direction of the fan blade was 12.06% to 15.40% greater than the overpressure value PLN of the segment with the least overpressure.


## 3.1. Overpressure on Blades Changes with Time

The moment when overpressure starts to appear on the blades is recorded asT1. The moment when Pmax appears is recorded as T2, and T3 is the time interval between T2 and T1. The variation of P on blades 1, 5, 9, and 13 with time is shown in Figure 7. Variation of P on blades 1 with time under different gas explosion volume is shown in Figure 8.Figure 7
Variation ofP on blades 1, 5, 9, and 13 with different gas explosion volumes over time. (a) Volume = 31.16 m3. (b) Volume = 62.33 m3. (c) Volume = 115.82 m3. (d) Volume = 311.64 m3. (e) Volume = 779.11 m3.
(a)(b)(c)(d)(e)Figure 8
Time-varying graph ofP on blade 1 under different gas explosion volumes.It is not so hard to see from Figure7 that occurrence time of overpressure and maximum overpressure time on each blade were basically the same. Figure 8 shows that T1 and T2 decrease with the increase of gas explosion volume. As the intensity of gas explosion increases, the width of the peak becomes narrower and narrower, that is, T3 decreases as the volume of gas explosion increases. It is because that the shock wave generated by the larger gas explosion volume is stronger, and the shock wave speed is faster. The earlier the time T1 on the fan blade, the earlier the time T2 and the shorter the time interval T3 between T1 and T2


## 3.2. Maximum and Minimum Overpressure Blades

For different explosion gas volumes, when the gas explosion shock wave propagated to the fan blades, the maximum overpressurePmax experienced by each blade is shown in Figure 9. The maximum Pmax of the 16 blades was recorded as Pm, and the minimum Pmax was recorded as Pn. The Pm value and Pn value under different gas explosion volumes are shown in Table 1.Figure 9
Pmax on fan blades under different gas explosion volumes.Table 1
Pm and Pn under different gas explosion volumes.
Gas explosion volume (m3)Pm (Pa)Pn (Pa)Difference (%)33.16190417945.7862.33397337086.67155.8213701129555.44311.6421626203475.91779.1130832287816.65From Figure9 and Table 1, it can be seen that Pmax on each fan blade had little difference, blade 1 directly above the hub bore the maximum overpressure, and blade 9 directly below the hub bore the minimum overpressure, which was caused by the change of the propagation direction of the shock wave in the wind tunnel. Pm was 5.44–6.77% higher than Pn under different explosion gas volumes.The variation ofPm and Pn with explosion volume is shown in Figure 10. It can be seen that Pm and Pn increase with the increase of gas explosion volume, but the magnitude of the increase gradually decreases.Figure 10
Relationship betweenPm and Pn and gas explosion volume.


## 3.3. Distribution of Overpressure on the Blade

When the gas concentration was 9.5% and the explosion volume was 311.64 m3, the shock wave overpressure distribution at different moments on blade 1 located directly above the hub is shown in Figure 11. It can be seen that the distribution of overpressure on the blade was very uneven, and the blade edge bore the lowest overpressure and gradually increased from the edge to the inside.Figure 11
Cloud chart of pressure change with time of blade 1 when gas explosion volume was 311.64 m3. (a) t = 0 m·s. (b) t = 153 m·s. (c) t = 193 m·s. (d) t = 204 m·s.
(a)(b)(c)(d)The blade was divided into 10 segments from the root to the tip in the radial direction (the total length of the bladeH is 630 mm, and the length of each segment h is 63 mm). The overpressure value of the segment with the highest overpressure was recorded as PLM, and the overpressure value of the segment with the lowest overpressure was recorded as PLN. When blade 1 reached Pmax, the distribution of the overpressure on the blade along the radial direction is shown in Figure 12, and PLM and PLN on the blade 1 under different gas explosion volumes are shown in Table 2.Figure 12
Overpressure distribution in the radial direction of blade 1 under different explosion volumes.Table 2
PLM and PLN on blade 1 under different gas explosion volumes.
Gas explosion volume (m3)Maximum valueMinimum valueDifference (%)(Pa)(Pa)33.161968167215.0462.334095349614.6377.915606477614.81155.82140441235012.06311.64221541917813.43779.11315832672015.40Figure12 showed that the overpressure on the fan blades showed a corrugated distribution in the radial direction, but the change range was not large. From Table 2, it can be seen that, under different gas explosion volumes, the overpressure value PLM of the segment with the largest overpressure in the radial direction of the fan blade was 12.06% to 15.40% greater than the overpressure value PLN of the segment with the least overpressure.


## 4. Conclusion

In this paper, we took Yangchangwan No. 2 return air well as the research object. When the gas explosion occurred in the driving face, the propagation process of the explosion shock wave in the shaft and the air tunnel under different gas explosion volume conditions and the dynamic process of the main fan blades under the impact load were simulated numerically. The overpressure on the blade at different times, the overpressure distribution on the blade, and the relationship between the overpressure and the explosion intensity were obtained, which can be used as a reference for the structural design of fans.(a)
T1 and T2 on each blade were basically the same. With the increase of gas explosion volume, the time when the overpressure appeared on the fan blade was advanced, and the time to reach the maximum overpressure was also advanced. The time interval T3 between T1 and T2 decreased.(b)
There is little difference in overpressure on each blade because of the different angle between the fan blades and the direction of shock wave. The fan blade directly above the hub was subject to the highest overpressure, and directly below the hub was subject to the lowest overpressure. The overpressure of the maximum overpressure blade was 5.44% to 6.77% higher than that of the minimum overpressure blade.(c)
The distribution of overpressure on each fan blade was uneven, and the overpressures on blade edges were the lowest. The overpressure gradually increased from the edge to the inside. The overpressure on the fan blades showed a corrugated distribution in the radial direction. The overpressure value of the maximum overpressure sections of the fan blade was 12.06% to 15.40% larger than the minimum overpressure sections.



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*Source: 8820025-2020-10-30.xml*