International Journal of Rotating Machinery

Volume 2012, Article ID 340439, 11 pages

http://dx.doi.org/10.1155/2012/340439

## Effects of a Nonuniform Tip Clearance Profile on the Performance and Flow Field in a Centrifugal Compressor

^{1}Department of Mechanical Engineering, Pohang University of Science and Technology (POSTECH), San 31, Hyoja-dong, Nam-gu, Pohang 790-784, Republic of Korea^{2}Department of Mechanical Engineering, Myongji University, Yongin 449-728, Republic of Korea^{3}The 7th R&D Institute, Agency for Defense Development, Daejeon 305-152, Republic of Korea

Received 14 February 2012; Accepted 27 June 2012

Academic Editor: Meinhard Taher Schobeiri

Copyright © 2012 Yohan Jung et al. This is an open access article distributed under the Creative Commons Attribution License, which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited.

#### Abstract

This paper presents a numerical investigation of the effects of a nonuniform tip clearance profile on the performance and flow field in a centrifugal compressor with a vaneless diffuser. This study focuses in particular on the magnitude and location of the wake. Six impellers with different tip clearance profiles were tested in the flow simulations. The accuracy of the numerical simulations was assessed by comparing the experimental data with the computational results for a system characterized by the original tip clearance. Although the performance improved for low tip clearances, a low tip clearance at the trailing edge improved the compressor performance more significantly than a low tip clearance at the leading edge. The flow field calculated for a system characterized by a low tip clearance at the trailing edge produced a more uniform velocity distribution both in the circumferential and in the axial directions at the impeller exit because the wake magnitude was reduced. As a consequence, this impeller provided a better potential for diffusion processes inside a vaneless diffuser.

#### 1. Introduction

Centrifugal compressors used in aeronautical and industrial applications are required to function at high pressure ratios and over wide operating ranges. A better understanding of the flow mechanism underlying the secondary flow fields inside compressors is essential for the design of centrifugal compressors with improved performance and extended operational ranges [1]. The main flow in centrifugal compressors is sensitive to secondary flows generated by the channel curvature as well as the centrifugal and Coriolis forces. As a result, jet-wake flow patterns form at the impeller exit, and these patterns govern the flow field in the diffuser [2, 3]. In the jet-wake model, flow in the jet region near the pressure surface of the blade is nearly loss-free, whereas flow in the wake region near the suction surface of the blade generates large total pressure losses. The classical jet-wake model ignores the influence of the tip clearance flow and the spanwise flow variations. The model, therefore, does not adequately describe the outlet flow of an unshrouded impeller with tip clearance, and the model must be revised. In unshrouded impellers, the tip clearance flow significantly affects the performance and flow field because it causes pressure losses over the tip clearance and strengthens the secondary flows.

The influence of the tip clearance flow on the performance and flow structure in centrifugal compressors has been studied by many researchers [4–14]. In previous studies, it was found that the swirling flows and vortex motions within unshrouded impellers are sensitive to the tip clearance flow. Consequently, these flows produce high losses and degrade performance if the tip clearance is large. The nonuniformity of the impeller outlet flow due to the tip clearance flow significantly affects the diffuser inlet flow conditions and causes large flow separations inside the diffuser. The overall compressor performance may be improved by enhancing the uniformity of the impeller outlet flow in the circumferential and axial directions. Most previous numerical studies of the tip clearance effects have assumed a uniform tip clearance with a constant height. Few studies have considered a nonuniform tip clearance.

The main objective of this work is to numerically investigate the effects of various nonuniform tip clearance specifications on the performance and flow field in a centrifugal compressor, particularly focusing on the magnitude and location of the wake region. Numerical simulations were conducted for six centrifugal compressor impellers in which the tip clearance height varied linearly from the leading to the trailing edge. The numerical results were compared with experimental data to assess the accuracy of the numerical predictions.

#### 2. Test Compressor Description

The compressor used in this study is known as the “Radiver” in the literature. Radiver test case measurements were conducted at the Institute of Jet Propulsion and Turbomachinery at RWTH Aachen, Germany. The investigations were funded in part by the Deutsche Forschungsgemeinschaft (DFG). The experimental data were made available to the public for broad use in computational fluid dynamics (CFD) validation studies. The compressor stage consists of an unshrouded impeller with 15 backswept blades and a vaneless diffuser. Under the design condition with a specific speed of 0.69, the maximum total pressure ratio and the maximum corrected mass flow rate through the impeller are 4.07 and 2.5 kg/s, respectively. The tip clearance height is 0.7 mm for the stationary impeller, and the vaneless diffuser has a constant meridional height of 11.1 mm. The geometrical specifications are summarized in Table 1, and a schematic diagram of the meridional plane is shown in Figure 1, where the sections 2 M and 2M′ indicate the measurement positions. A complete description of the geometrical configurations and operating conditions can be found in Ziegler et al. [15–17].

#### 3. Numerical Procedure

Three-dimensional simulations were performed using the commercial CFD code, ANSYS CFX 12.0. Steady calculations were conducted to minimize the computational effort. As numerical scheme for these calculations, a second-order upwind scheme was used in space. The computational domain consisted of a single impeller blade passage and a vaneless diffuser, in which an H-type grid was employed over the regions of the main flow channel and the tip clearance. An O-type grid was used around the impeller blade to improve the grid quality near the leading and trailing edges of the blade. The grid-independence study was performed at three different grid sizes of 103 818, 608 170, and 1 196 420 cells at of 1.0. There was no significant difference (less than 0.2%) between the medium and large grid size regarding total pressure ratio and total efficiency. As a result of the grid-independence study, the medium grid size was selected to perform flow analysis. 15 cells in the spanwise direction were used to study the flow field within the impeller tip clearance region. The total number of computational cells is approximately in the impeller passage and in the diffuser. The computational grid over the entire domain, including the detailed surface grid near the leading and trailing edges of the impeller blade, is shown in Figure 2.

The *k*-*ω* SST model was applied to obtain turbulent quantities, assuming that the flow in the compressor is fully turbulent. In most of the blade surfaces and end walls, + values are less than 2 as required for the use of *k*-*ω* SST model. The design rotational speed was 35 200 rpm. The total pressure, total temperature, and flow direction were specified at the impeller inflow boundary ( Pa and K), and the mass flow rate was specified at the diffuser outflow boundary. Periodic boundary conditions were applied in the circumferential direction, and the walls were treated with the no-slip and adiabatic conditions.

#### 4. Numerical Test Cases

The influences of a nonuniform tip clearance on the performance and flow field were investigated by conducting simulations of impellers with six tip clearance shapes. The tip clearance heights at the leading and trailing edges were selected, and the distribution of the tip clearance varied linearly along the tip. To account for reductions in the tip clearance due to centrifugal forces and temperature variations under hot-running conditions [17], the tip clearances at the leading and trailing edges were varied from 0.7 mm to 0.48 mm or 0.24 mm. The relative clearance ratios, defined as the ratio of the tip clearance height to the blade height at the impeller exit, are 6.4%, 4.4%, and 2.2% for 0.7 mm, 0.48 mm, and 0.24 mm, respectively. Table 2 shows the numerical test cases. The tip clearance at the trailing edge was varied in cases 2 and 3, whereas the tip clearance at the leading edge was varied in cases 4 and 5. The tip clearance both at the leading and trailing edges was varied in case 6. The computational conditions, grid size, and boundary conditions were constant for all test cases except for the tip clearance profile.

#### 5. Validation for Uniform Tip Clearance

Prior to comparing the performance of the test cases, the numerical result for the original tip clearance (0.7–0.7 mm) was validated with the experimental data. Because no experimental data is available under 100% speed condition, all calculations were performed at 80% speed. Measurements were carried out with steady probes and time resolving laser-2-focus velocimeter at sections 2 M and 2M′, respectively. Numerical results were validated by comparing the computed characteristic curves of the mass-averaged static and total pressures in section 2 M with the experimental data, as shown in Figure 3. The CFD results showed satisfactory agreement with the experimental results over the full range of operating conditions. The flow field at section 2M′ near the impeller exit is shown in Figure 4 at of 1.0. The overall flow structure predicted by the numerical simulations, including the jet-wake flow pattern, was qualitatively well captured, as observed by comparison with the experimental results. Some differences were present in the low meridional velocity region near the shroud. The extension of the low meridional velocity region along the axial direction away from the shroud was overpredicted by CFD due to a higher-intensity tip clearance flow, which was caused by a uniform tip clearance. Improved results may be obtained by applying a nonuniform tip clearance height (0.7–0.48 mm) [13].

#### 6. Results

##### 6.1. Performance Prediction

Three-dimensional calculations were performed over the full operating range, from near-stall conditions to choked points. The overall performances were compared.

The static and total pressure ratios at the impeller exit are shown in Figure 5. The static pressures over the entire operating range for all impellers with reduced tip clearances were higher than those in the original case, indicating that reductions in the tip clearance at the leading or trailing edge improved the static pressure rise. The impeller exit total pressure also increased for the impellers with reduced tip clearances. Case 6 had the highest static and total pressures among the test cases, because the tip clearance was reduced both at the leading and trailing edges. At of 1.0, cases 3 and 6 showed 2.5% and 3.9% improvements in the static pressure rise compared to case 1, respectively. The static and total pressure curves also indicated that a smaller tip clearance at the trailing edge was more effective than a smaller tip clearance at the leading edge. Large total pressure losses generally result from leakage flow through the tip gap [5]. As the tip clearance height at the leading or trailing edge is reduced in size, reductions in the tip leakage flow decrease losses and improve pressure rises. In the original case, at of 0.8, the tip leakage flow rate was 5% lower than that at of 1.0, while the mass flow rate was 20% lower than that at of 1.0. Because the mass flow rate through the impeller was reduced much more than the mass flow rate through the tip, the influence of the tip clearance flow was not reduced at of 0.8. Therefore, the decreased tip clearance was still effective even at the lower mass flow rate.

The performance of a centrifugal compressor is significantly affected by tip clearance in two ways. First, tip leakage flow causes large pressure losses due to mixing with the main passage flow, as mentioned above. Second, the impeller cannot transfer its momentum to the fluid across the tip clearance, which decreases the total work input. Consequently, small changes in the tip clearance could have large influences on the compressor performance. The work input coefficient at the impeller exit is shown in Figure 6. Higher work input coefficients were associated with all impellers with tip clearances smaller than that of the original case. Additionally, decreasing the tip clearance at the trailing edge rather than at the leading edge effectively increased the work input.

The shapes of the total efficiency curves for all cases resembled the original case, with a maximum peak at of 1.0, as shown in Figure 6. The impellers with reduced tip clearances yielded better efficiencies because the mixing loss caused by the tip clearance flow was reduced. In particular, cases 3 and 6 showed 1.2% and 2.2% improvements in efficiency compared to case 1 at the design point, respectively. At low mass flow rates, the total efficiency difference between cases 1 and 3 decreased compared to the peak-efficiency point, probably because the mixing loss due to the tip clearance was less prominent.

The diffuser performance was investigated by measuring the static and total pressure ratios at the vaneless diffuser exit, as shown in Figure 7. The overall characteristics of the diffuser exit pressures were similar to those of the impeller exit pressures. It was evident that case 6 had higher static and total pressure ratios than any other cases. In addition, cases 2 and 3, which featured reduced tip clearances at the trailing edge, were clearly superior to cases 4 and 5, which featured reduced tip clearances at the leading edge, with regards to the static and total pressures at the diffuser exit.

##### 6.2. Flow Field Analysis

The flow field was analyzed to investigate the performance variations caused by the reduced tip clearance at the leading or trailing edges. The flow field comparison was confined to the operating condition at of 1.0, under which a higher efficiency was observed for cases 1, 3, 5.

###### 6.2.1. Tip Leakage Flow

Variations in the normalized flow velocity through the tip clearance from the leading edge to the trailing edge are shown in Figure 8. Relative to case 1, the flow velocity along the blade chord clearly decreased for cases 3 and 5. In case 1, the tip leakage flow velocity distribution had local maxima at 20% and 80% chord lengths. In case 3, the flow velocity increased from the leading edge to a maximum at 20% chord length, then it retained a nearly constant value until 80% chord length. This result indicated that case 3 experienced a significant reduction in the tip leakage flow in the rear region due to the smaller tip clearance at the trailing edge. On the other hand, case 5 displayed a slow increase in the tip leakage flow from the leading edge to 80% chord length, where the tip leakage flow velocity reached a local maximum value. In contrast with case 5, case 3 displayed a larger flow velocity across the gap in the front region but a smaller flow velocity in the rear region. The total flow rate integrated along the chord length in case 3 was lower than that in case 5. The flow rate across the tip in cases 3 and 5 were reduced to 69% and 73%, respectively, of the value in case 1. These flow velocity variations significantly affected the flow field and were closely related to the lower total pressure loss.

###### 6.2.2. Blade Tip Loading

The effects of the tip clearance distribution on the blade tip loading were investigated by comparing the blade pressure distributions near the shroud in the three cases. Figure 9 shows a plot of the blade tip loading values at 90% span from the hub. All three cases showed similar pressure distributions along the blade chord. However, at 30% chord length from the leading edge, case 5 showed the highest blade loading, suggesting that the generation of a tip leakage vortex was delayed because the mass flow rate across the tip clearance decreased significantly in the front part of the blade due to the small tip clearance at the leading edge. On the other hand, after 75% chord length, the static pressure increase on the pressure surface for case 3 was much larger than it was for the other cases, and it generated higher blade tip loading in the rear region. This result arose from the fact that case 3 had a small tip clearance at the trailing edge, which produced a weak tip leakage flow and decreased the mixing loss.

###### 6.2.3. Loss Generation Process

The loss distribution in the impeller was investigated by calculating the entropy function using (1), as suggested by Whitfield and Baines [18]. The entropy function distributions from the leading edge to the trailing edge are shown in Figure 10,

The slope of the entropy function was nearly constant for the impeller with a uniform tip clearance (case 1), whereas the entropy function for impellers with nonuniform tip clearances (cases 3 and 5) was non-linear. Variations in the entropy slope were related to the tip clearance loss changes caused by the nonuniform tip clearance. Stronger interactions between the tip leakage flow and the main passage flow occurs at the point at which the tip leakage flow is stronger. At such points, the flow interaction is strong, which increases the mixing loss and deteriorates the compressor performance. The entropy function of case 3 had a steep slope in the front region but a shallow slope in the rear region rather than that for case 5. As a consequence, the entropy function of case 3 was lower at the trailing edge than it was in case 5. Because the entropy function at the impeller exit represents the accumulated total loss through the flow passage, the low entropy in case 3 produced a higher impeller efficiency, as shown in Figure 6. This result indicated that the positive effects of loss reduction in the rear region of case 3 were more dominant than the loss gains in the front region. The tip clearance losses were quantitatively compared by calculating the total pressure loss coefficient induced by the tip clearance using the following equation [19]:

The overall total pressure loss in case 3 was 3.4% lower than that of case 5 and 29% lower than that of case 1. Consequently, the tip clearance loss can be decreased more effectively by reducing the tip clearance at the trailing edge.

###### 6.2.4. Impeller Outlet Flow

The total efficiency distributions at the impeller outlet planes are shown in Figure 11. The efficiency distributions of all three cases showed similar high efficiency flow patterns near the pressure side and low efficiency flow patterns near the suction side of the shroud, which are typical properties of centrifugal compressors [20]. The magnitude and extent of the low efficiency regions differed to some degree. The low efficiency region near the shroud suction side in case 1 was most extended both in the circumferential and in the axial directions compared with the other two cases because the tip leakage flow was the strongest in case 1. The magnitude and extent of the low efficiency region in case 5 were significantly lower than in case 1, and further reductions in the low efficiency region were achieved in case 3. Variations in the high loss region contributed significantly to the reduced performance at the impeller exit. It should be noted that the tip clearance height at the trailing edge was a main factor in determining the high loss region near the shroud at the impeller exit.

A comparison of the circumferentially averaged radial velocity distributions from the hub to the shroud at the impeller exit is plotted in Figure 12. At the impeller exit, the flow near the shroud experiences secondary flows that block the flow passage. In addition, the tip clearance flow influences the secondary flow structure and further blocks the flow passage, thereby generating a large total pressure loss near the shroud. The blockage resulted in a rapid decrease in the radial velocity near the shroud in all three cases. The low radial velocity near the shroud indicated a separated zone in which a high loss fluid accumulated. A blocked zone with a negative radial velocity was present above 98% span from the hub in cases 1 and 5, suggesting that a strong reverse flow was present near the shroud because low momentum flow could not overcome the pressure gradient in the radial direction. However, in case 3, no reverse flow was observed near the shroud, suggesting that the blockage was smaller in case 3 than in the other two cases. For this reason, case 3 included the smallest high-loss region near the shroud, as shown in Figure 11. The increased radial velocities near the shroud in case 3 were explained by the reduced tip leakage flow in the rear region, as confirmed in Figure 8. The radial velocity distributions in cases 1 and 5 were almost identical, even though these systems included different tip clearances at the leading edge. This result suggested that the radial velocity distribution in the spanwise direction at the impeller exit depended strongly on the tip clearance at the trailing edge.

###### 6.2.5. Wake Flow

The wake formation at the impeller exit was investigated by comparing the relative velocity distributions in the three cases, as shown in Figure 13. All three cases showed a strongly nonuniform flow both in the circumferential and in the axial directions, and the flow structure was highly three-dimensional at the impeller exit. In addition to the axial flow variations due to the skewed shear layer, the flow was affected in the circumferential direction by the blade loading. The relative velocity distributions in cases 1 and 5 showed similar qualitative characteristics. Case 3 presented a different flow structure in the wake region, which included an area of low relative velocity.

The circumferential nonuniformity at the impeller exit was investigated by comparing the relative deviations from the mass-averaged relative velocity at 90% span for the three cases, as shown in Figure 14. The absolute magnitude of the deviations in case 3 was smaller than that in the other cases in the region from the pressure side to the mid-pitch, which led to an enhanced uniformity in the flow field in the circumferential direction. Another important feature is the location of the wake region, where the relative velocity deviation has the minimum value. The wake region appeared near the pressure side in cases 1 and 5, but it was closer to the center of the blade pitch in case 3.

To determine the source of movement of the wake region, the secondary vorticity distribution at the impeller exit was calculated using the following equation, and the results are shown in Figure 15:

The sign of the secondary vorticity indicated the rotational direction of the secondary flow, where positive values corresponded to vortices rotating in the counter-clockwise direction and negative values corresponded to vortices rotating in the clockwise rotation. Two distinct vortices were observed in all three cases. The vortex with a positive secondary vorticity generated by the Coriolis force, called the passage vortex, moved low momentum fluid above the mid-span from the pressure to the suction side. On the other hand, the tip leakage vortex with a negative secondary vorticity moved low momentum fluid near the shroud from the suction to the pressure side. Interactions between these two vortices rotating in opposite directions affected the location of the wake region near the shroud. In cases 1 and 5, the tip leakage vortex was stronger than the passage vortex, so that the transport of low-energy fluid to the suction side was limited. This explained why the wake region was located near the pressure side in cases 1 and 5, as shown in Figure 14. In case 3, however, the intensity of the tip leakage vortex decreased due to the reduced tip clearance at the trailing edge. Therefore, the passage vortex became large and was not hampered by the tip leakage vortex, which further transported the low-energy fluid toward the suction side. In other words, the larger passage vortex played a key role in moving the wake region further toward the suction side for a system with a small tip clearance at the trailing edge.

The relative deviations from the mass-averaged relative velocity from the hub to the shroud at the impeller exit are further compared in Figure 16. All cases showed similar nonuniform flow patterns in the hub-to-shroud direction. That is, high relative velocities were present near the hub, whereas low relative velocities were found near the shroud. A 7% reduction in the flow deviation at 95% span was achieved in case 3 compared to the other two cases. This observation indicated that case 3 had a more uniform flow pattern in the axial direction due to the smaller wake region. In addition, reductions in the relative velocity gradient from the hub to the shroud produced a smaller secondary flow, which increased the impeller efficiency for case 3.

Because the impeller outlet flow field significantly influences the diffuser inlet flow conditions, the flow inside the vaneless diffuser experiences severe distortions in the axial direction. The flow angle distribution from the hub to the shroud at the impeller exit for a compressor with a vaned diffuser must be considered in the design of advanced three-dimensional diffusers [21].

Figure 17 shows variations in the flow angles from the hub to the shroud at a 110% impeller exit radius. Because the flow angle is measured from the circumferential direction, flows with small flow angles tend to be more circumferential. All three cases presented distorted flow patterns because the upstream impeller flow was strongly nonuniform in the axial direction. Differences in the flow angle between the hub and the shroud were at least 10°. Near the shroud, the wake flow, which had a small flow angle, remained in the diffuser inlet downstream of the impeller because the wake mixing process was incomplete. The diffuser flow pattern in case 3 was more homogeneous than in the other two cases in terms of the flow angle distribution in the axial direction due to the improved uniformity of the flow field at the impeller exit, as confirmed in Figure 16. Therefore, a smaller tip clearance at the trailing edge provided a better potential for diffusion processes inside a vaneless diffuser than did a smaller tip clearance at the leading edge.

#### 7. Conclusions

The effects of a nonuniform tip clearance on the flow fields and performance of a centrifugal compressor were analyzed. Six impellers with different tip clearance distributions were modeled numerically, and the flow fields were investigated in detail to identify the factors that contributed to variations in the performance and efficiency.(1)Although impellers with reduced tip clearances at the leading or trailing edges performed better than the impeller with a original uniform tip clearance, a smaller tip clearance at the trailing edge reduced the overall tip leakage mass flow rate more effectively than a smaller tip clearance at the leading edge. Accordingly, a smaller tip clearance at the trailing edge lowered the mixing loss caused by interactions between the tip leakage flow and the main passage flow.(2)A nonuniform tip clearance influenced the location of the wake region by modulating the interaction between the passage and tip leakage vortices, which rotated in the opposite directions and transported low-momentum fluid near the shroud. A small tip clearance at the trailing edge reduced the tip leakage vortex and increased the passage vortex, which consequently increased the transport of the wake region toward the suction side.(3)A reduced tip clearance at the trailing edge produced a more uniform flow at the impeller exit both in the circumferential and in the axial directions due to a reduced wake region. Because the diffuser inlet flow was significantly affected by the upstream impeller outlet flow, decreasing the tip clearance at the trailing edge significantly improved diffusion processes inside the vaneless diffuser.

#### Nomenclature

: | Absolute velocity |

: | Diameter |

LE: | Leading edge |

: | Mass flow rate |

: | Static pressure |

PS: | Pressure side |

: | Volume flow rate |

: | Gas constant |

: | Entropy |

SS: | Suction side |

SV: | Normalized secondary vorticity |

: | Static temperature |

TE: | Trailing edge |

: | Blade speed |

: | Relative velocity |

: | Flow coefficient = |

: | Design flow coefficient |

: | Ratio of specific heat |

: | Isentropic total-to-total efficiency |

: | Work input coefficient |

: | Density |

: | Entropy function |

: | Impeller rotational speed |

: | Vorticity |

: | Total pressure loss coefficient. |

*Subscripts*

0: | Total condition |

1: | Impeller inlet |

2: | Impeller outlet |

CL: | Tip clearance |

: | Circumferential component. |

#### Acknowledgments

The authors would like to thank the Institute of Jet Propulsion and Turbomachinery at RWTH Aachen for providing them with experimental data. This work was supported by the Defense Acquisition Program Administration, Agency for Defense Development [UD040006AD], and BK21.

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