Purdue University Purdue e-pubs International Compressor Engineering Conference School of Mechanical Engineering 24 Three-Dimension Numerical Simulation of Discharge Flow in a Scroll Air Compressor Jian Mei Feng i'an Jiaotong University Zong Chang Qu i'an Jiaotong University in Wei Lin i'an Jiaotong University Follow this and additional works at: http://docs.lib.purdue.edu/icec Feng, Jian Mei; Qu, Zong Chang; and Lin, in Wei, "Three-Dimension Numerical Simulation of Discharge Flow in a Scroll Air Compressor" (24). International Compressor Engineering Conference. Paper 1647. http://docs.lib.purdue.edu/icec/1647 This document has been made available through Purdue e-pubs, a service of the Purdue University Libraries. Please contact epubs@purdue.edu for additional information. Complete proceedings may be acquired in print and on CD-ROM directly from the Ray W. Herrick Laboratories at https://engineering.purdue.edu/ Herrick/Events/orderlit.html
C44, Page 1 THREE-DIMENSION NUMERICAL SIMULATION OF DISCHARGE FLOW IN A SCROLL AIR COMPRESSOR Jian Mei Feng 1, Zong Chang Qu 2, in Wei Lin 3 School of Energy and Power Engineering, i an Jiaotong University, i an 7149, China Tel: +86(29) 82668985; Fax: +86(29) 82668691 E-mail address: 1 jmfeng@mail.xjtu.edu.cn 2 zchqu@mail.xjtu.edu.cn 3 lxw5837@mail.xjtu.edu.cn ABSTRACT Scroll compressor is being recognized by power industry as being high competitive with conventional compressors. Plenty of publications on this subject prove an interest of the researchers as well. Further increases in efficiency may be realized if the flow losses, particularly in the final compression and discharge region are reduced. Detailed understandings of the flow processes occurring in the discharge region are necessary to analysis and reduce the discharge flow losses, which become more serious with operation at large discharge. Due to the complexity of the processes, the only one way to get the results is solving the equations of continuity and momentum using the numerical method. During the past decade, a number of investigations have been conducted on the performance of the scroll compressor. However, relatively little information are available on the details of the fluid flow characteristics within the scroll compressor chamber. In this paper, in the light of the characteristics of a discharge process, reasonable simplification of actual physical model is made and the three-dimension quasi-steady turbulent flow numerical simulation is carried out to study the flow field in the discharge region in a scroll air compressor. Three dimensional distributions of velocity and pressure and typical flow patterns that exits in the discharge region are presented, which gives good understanding about the physical processes in the scroll air compressor. 1. INTRODUCTION Scroll compressors are applied widely in the refrigeration, air conditioning and power field as being competitive advantages in terms of high efficiency, reduced part requirement, lower noise, and reduced vibration levels. There exist various losses when a scroll compressor is running, such as moving resistance losses of the orbiting scroll and Oldham, friction losses and flow losses. The discharge flow loss is the main part of these losses (approximately 3 percent of the input power is consumed due to flow losses (Hirano. T., et al., 1989)), especially at large discharge. Understanding of the flow processes occurring in the discharge and the final compression region is necessary to reduce these flow losses, which become more pronounced with operation at increasing speed and large discharge. Therefore, three dimension numerical simulation of discharge flow in scroll air compressor with modified top profile is carried out. The important flow patterns that exist in the discharge and final compression region are presented. The analysis results supply the theory basis for finding the sources caused discharge losses and designing the discharge port of scroll compressor, particularly at large discharge. A scroll air compressor of 1.6m 3 /min discharge is studied in this paper. The top profile is modified with symmetrical arcs and the discharge port is kidney-shape port. The basic parameters and modified parameters of scroll tips are shown in the table 1. Figure 1 shows the schematic of discharge region of the scroll compressor. Table 1: The basic parameters and modified parameters of scroll tips p h t β (rad) R r θ* (rad) A (m 2 ).28.52.45 3.473.164.69 22.5366 247.552e-6 International Compressor Engineering Conference at Purdue, July 12-15, 24
C44, Page 2 Figure 1: Schematic of scroll compressor discharge region. 2. PHSICAL MODEL AND NUMERICAL METHOD 2.1 Physical model The gas is driven and compressed by squish motion of the orbiting scroll wrap, and this results that an unsteady compressible viscous flow occurs within the scroll compressor working chamber. Due to high rotating speed and steep velocity gradient near the wrap wall, the turbulence characteristics have to be considered. But the orbiting wall speed is small compared to the gas flow velocities, for example, the wall speed is approximately 5 percent of the average velocity of the discharge flow in a scroll air compressor at 1.6m 3 /min discharge studied in this paper, so it appears justified that the quasi-steady approach is made to treat the flow field with stationary wall. That is, to ignore the moving of orbiting scroll wall is justified. Therefore, three dimension steady-state turbulence calculations are performed to predict the flow field in the final compression and discharge region. Air is injected from two sides of the central chamber with the instantaneous flow rate at various crank angles. The volume flow rate at various crank angles during the discharge process is shown in figure 2. The figure 3 shows a computational model at a certain crank angle after onset of discharge. Volume flow rate dv/dθ ( cm 3 /deg).7.6.5.4.3.2.1. -.1 6 12 18 24 3 36 orbiting discharge crank angle θ /(deg) Figure2: Volume flow rate with orbiting discharge crank angle Figure3: Three dimensional computation model 2.2 Numerical method Turbulent flow exists in the scroll configurations considered and was treated using a normal k ε turbulence model. The governing equations were discretized using finite volume method. The SIMPLE algorithm (Patankar S V, Spalding D B, 1972) was employed in order to correct the pressure field. Near the wall, the improved wall function method (Wang unliang, et al., 1993) was employed. The discretization scheme of convection item and diffusion item are respectively the second-order upwind scheme and the central difference scheme. Tao (21) shows the details of discretization method. In the light of the geometrical characteristics of computational domain, the geometry scale of different parts of the whole domain differs greatly; the block structure gird method (Tao Wenquan, 2) was employed to generate grids of the whole domain being separated into several parts, in which grids were generated by the body-fitted coordinate grid system (Thompson J.F., et al., 1985). Grids are so fine that the International Compressor Engineering Conference at Purdue, July 12-15, 24
C44, Page 3 numerical results are grid independent. The computational domains at different crank angles are different, so the grids were generated separately. The boundary conditions are as the followings: (a) Inlet The mass flow rate on each of two inlets is the same and equal to the instantaneous volume change rate multiplied by the density. (b) Outlet The outlet is set on the location far away as 5 times of height of discharge port in order to guarantee the constant pressure. The discharge pressure is provided on outlet. (c) Wall Non-slip boundary condition for velocity is provided on walls. Advanced wall function method is employed to treat the near wall domain. 3. NUMERICAL RESULTS In this paper, θ is defined as the orbiting discharge crank angle. At the discharge moment, that is the crank angle θ= θ (θ is the discharge crank angle), θ is taken as zero. Then, θ is changing from to 36 degree during the whole process of discharge. According to this definition, for example, at crank angle of 45 degree after the onset of discharge is described asθ= 45. In this paper, for the convenience of description, location of the z coordinate equal to zero is defined as the inlet of discharge port and is named as the low surface of the fixed scroll. Location of the z coordinate equal to h (the height of scroll wrap) is named as the top surface of the fixed scroll. The flow field and its discharge from the central chamber region at several crank angles that correspond to 45, 9, 18 degree after the onset of discharge is studied. Flow velocity vectors in different axial sections and three dimensional velocity vectors are detailedly analyzed. 3.1θ= 45 The calculated velocity fields in different axial sections are shown in figure 4 (a)-(c) at orbiting discharge crank angle of 45 degree. The flow velocity vectors in fig.4 indicate that flow being injected in the rear of each half central chamber, being turned as it impinges on the opposing wall of orbiting scroll or fixed scroll and proceeding towards the central region of the central chamber. In the central region, flow enters from both half central chamber, passing through throat region formed by the orbiting and fixed scroll tips and proceeds driven by the inertia. Two large scale vortexes develops in the central region near the scroll tips and some small scale vortexes develops in the rear of central chamber near the outer surface of scroll tips. Compared fig 4 (a), (b) with (c), it is shown that vortex flow develops in all different axial sections and number and scale and location of vortex are different in different axial sections. That is to say this basic vortex flow pattern persists in this region throughout the entire axial extent of central chamber. Three dimensional velocity vectors shown in fig 5 indicate clearly the distribution of axial velocity component. The three dimensional flow tends to move vertically downwards as it approaches the central region of the central chamber which is directly upon the discharge port. The axial velocity component is very large at a small axial distance of -1mm from the discharge port (when the height of the profile is 52mm). The axial velocity by the order of magnitude is greater than the radial velocity. In contrast, within the rear regions of the central chamber, the flow is essentially two dimensional. From the fig 4 and fig 5, it can be seen that the velocity vectors in the mid axial section characterize the general nature of the flow within the entire central chamber. The flow vectors indicate both the two dimensional and the three dimensional nature of the flow depending upon the location. So, only the velocity vectors in the mid plane are analyzed below. International Compressor Engineering Conference at Purdue, July 12-15, 24
Z C44, Page 4.3.2.1 -.1 -.2 -.2.2 5m/s.3.2.1 -.1 -.2 -.2.2 2 m/s.1.5 -.5 -.1.1 (a) Top Plane (b) Mid Plane (c) Discharge Plane Figure 4: Velocity fields in different axial sections 2m/s 45 m/s.5.4.3.2.1 -.2 Z.2.2 -.2 θ = 9 Figure 5: Three dimensional velocity vectors 3.2 Similar type of flow calculations have been performed at an intermediate crank angle ( θ= 9 ). It is shown in fig 6. As the discharge process continues in an actual scroll compressor, the orbiting scroll continues to move away from the fixed scroll. This action is associated with a progressively increased opening of the central region to the discharge port. This implies a less occluded opening of the discharge port compared with the throat region atθ= 45. The velocity vectors in axial sections of mid plane and discharge plane are different from those atθ=45 and the magnitude of velocity reduced. A double vortex was predicted to form at the mid axial section and the scale of the vortexes increased to trend to become a larger vortex. 15 m/s 3 m/s.3.2.1 -.1 -.2 -.2.2.1.5 -.5 -.1 -.1.1 (a) Mid Plane (b) Discharge Plane Figure 6: Velocity fields in different axial sections International Compressor Engineering Conference at Purdue, July 12-15, 24
C44, Page 5 3.3 θ= 18 Figure 7 (a)-(b) shows the velocity vectors in the axial sections at orbiting discharge crank angle of 18 degree. From the figure, it is shown that the velocity vectors field is obviously different from those shown in fig. 4 and fig. 6. A large scale vortex was developed in the discharge region as the discharge port is opened fully. In addition, a less constrictive flow passage exits in the region of the scroll tips,the velocity magnitude reduces further. The velocity vector field shows the occurrence of some small scale vortexes at the rear region of the central chamber..2 2 m/s.1.1.5 3 m/s -.1 -.5 -.2 -.2 -.1.1.2 -.1 -.1.1 (a) Mid Plane (b) Discharge Plane Figure 7: Velocity fields in different axial sections 4. NONDIMENSIONAL PRESSURE LOSSES COEFFICIENT To obtain quantitative data characterizing the pressure losses of the final compression and discharge region, nondimensional pressure losses coefficient was defined as below: P Pd ξ = 1% Pd P is the average pressure in the central chamber, Pa; P d is the designed discharge pressure, Pa. The variation of pressure losses coefficient ξ with orbiting discharge crank angle for the whole discharge process under different operation conditions is shown in figure 8. The pressure losses coefficient is very large at orbiting discharge crank angle of -6 degree. For example, the losses coefficient at 45 degree of orbiting discharge crank angle is approximately ten times larger than the loss coefficient at 18 degree, indicating that the flow losses are largest at the onset of discharge. This result is not surprising, since this is also the point of maximum constriction of the flow area. Furthermore, the high rotating speed and discharge pressure corroborate that significant flow losses would exist. With increasing the opening discharge port, losses coefficient is decreasing rapidly. The results indicate that discharge flow losses concentrate at the onset of discharge and reduce quickly with increasing opening discharge port. In addition, these results imply that the open-and-close characteristic of discharge port should be stressed to consider when designing a discharge port, particularly for compressor at large discharge. The easier to open, the better the characteristic of discharge port is. Maximum area of discharge port is possibly not the best. 4 6 5 pressure losses coefficient ξ(%) 3 2 1 P d =8.E+5 Pa N=3 rpm pressure losses coefficient ξ(%) 5 4 3 2 1 P d =8.E+5 Pa N=4 rpm pressure losses coefficient ξ(%) 4 3 2 1 P d =5.E+5 Pa N=3 rpm 6 12 18 24 3 36 orbiting discharge crank angle θ /deg 6 12 18 24 3 36 orbiting discharge crank angle θ /deg 6 12 18 24 3 36 orbiting discharge crank angle θ /deg Figure 8: Nondimensional pressure losses coefficient with orbiting discharge crank angle 5. CONCLUSIONS International Compressor Engineering Conference at Purdue, July 12-15, 24
C44, Page 6 Three dimension numerical simulation of the discharge flow in a scroll air compressor was conducted to provide the characteristic of flow field in the final compression and discharge region. Detailed analysis is made of the flow velocity vectors in different axial sections. The numerical results show that complex vortex flow patterns exist in the discharge region, not only in axial sections, but in radial sections. On the basis of numerical results, the dimensionless pressure losses coefficient is defined and the pressure losses at various crank angles after onset of discharge is analyzed. It is shown that the discharge flow losses is greatly large shortly after the onset of discharge The result shows that, the easier to open, the better the characteristic of discharge port is. Maximum area of discharge port is possibly not the best. REFERENCES 1. Hirano. T., et al., 1989,Development of High Efficiency Scroll Compressor for Heat Pump Air Conditioners, Mitsubishi Heavy Industries, Ltd., Tech. Rev. Vol. 26, No. 3, p: 512-519. 2. Patankar S V, Spalding D B., 1972, A calculation procedure for heat mass and momentum transfer in three-dimensional parabolic flows, Int. J. Heat Transfer, Vol.15, No.11, p: 1787-186. 3. Wang unliang, u Zhong, Miao ongmiao, 1993, Influence of Different Wall Function Methods on turbulent flow fields, Fluid Engineering, Vol.21, No.12, p: 26-29. 4. Tao Wenquan, 21, Numerical Heat Transfer (second version), i an Jiaotong University Press, i an, 152 p. 5. Tao Wenquan, 2, Advanced Numerical Heat Transfer, Science Publishing Company, Beijing, 41 p. 6. Thompson J.F., Warsi Z.U.A., Mastin C.W., 1985, Numerical Grid Generation, Foundation and Application, North_Holland New ork. International Compressor Engineering Conference at Purdue, July 12-15, 24