Using Sweep and Dihedral to Control Three-Dimensional Flow in Transonic Stators of Axial Compressors

Gümmer, Volker; Wenger, U.; Kau, Hans-Peter

doi:10.1115/1.1330268

Cited by 73 publications

(20 citation statements)

References 14 publications

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“…As the core component in gas turbines, multi-stage compressors are continuously developed to achieve higher stage loading, making it critical to capture the aerodynamic performances during the design and optimization processes. 20,21 However, there seems to be very little discussion in the literature about the detailed aerodynamic analysis on highly loaded compressor in semi-closed cycles. In the previous studies, the investigations are mainly on the overall characteristic of the components, and few data are available regarding the particular aerodynamic parameters.…”

Section: Introductionmentioning

confidence: 99%

Aerodynamic analysis of a highly loaded compressor in semi‐closed cycles using a throughflow method

Song

2015

Greenhouse Gases

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This paper outlines the aerodynamic performance of a highly loaded 5‐stage compressor in a conceptual semi‐closed cycle. An in‐house throughflow computation procedure that has been proven to be a powerful tool in aerodynamic analysis for modern compressors is applied to simulate the compressor. The influences of changes in physical properties of the working medium with varying ratios of exhaust CO2 recirculation are considered in the computation. A series of numerical simulations is conducted with two settings depending on whether the rotational speed is set to obey the criterion of similarity. For the identical non‐dimensional speed parameter, the compressor can operate stably with pure CO2 as the working fluid. The distributions of aerodynamic parameters undergo no big differences under various CO2 contents; however, a somewhat little higher loss is observed for the 5th stage. When the absolute rotational speed is set according to the originally designed value, the compressor can bear a 25% CO2 content at the cost of a substantially narrowed working range, and a recirculation ratio of approximately 10% is a safe threshold value. The aerodynamic configuration also undergoes a notable redistribution given these circumstances; the load of the front stages is reduced, but the rear stages become the risk factors at near stall condition. This research reveals that from the compressor design point of view, a semi‐closed cycle is feasible using existing technology and that compressor modifications are needed according to situational requirements. © 2015 Society of Chemical Industry and John Wiley & Sons, Ltd

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Section: Introductionmentioning

confidence: 99%

Aerodynamic analysis of a highly loaded compressor in semi‐closed cycles using a throughflow method

Song

2015

Greenhouse Gases

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“…The effects of blade sweep include the influence of secondary flow and radial redistribution despite shockwave control. Gu¨mmer et al 11 investigated the sweep and dihedral effects in stators of axial compressors both numerically and experimentally and demonstrated that positive sweep and positive dihedral could reduce endwall losses and increase operating ranges.…”

Section: Introductionmentioning

confidence: 99%

Effect of blade sweep on inlet flow in axial compressor cascades

Chang

Zhu

Jin

et al. 2015

Chinese Journal of Aeronautics

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This paper presents comparative numerical studies to investigate the effects of blade sweep on inlet flow in axial compressor cascades. A series of swept and straight cascades was modeled in order to obtain a general understanding of the inlet flow field that is induced by sweep. A computational fluid dynamics (CFD) package was used to simulate the cascades and obtain the required three-dimensional (3D) flow parameters. A circumferentially averaged method was introduced which provided the circumferential fluctuation (CF) terms in the momentum equation. A program for data reduction was conducted to obtain a circumferentially averaged flow field. The influences of the inlet flow fields of the cascades were studied and spanwise distributions of each term in the momentum equation were analyzed. The results indicate that blade sweep does affect inlet radial equilibrium. The characteristic of radial fluid transfer is changed and thus influencing the axial velocity distributions. The inlet flow field varies mainly due to the combined effect of the radial pressure gradient and the CF component. The axial velocity varies consistently with the incidence variation induced by the sweep, as observed in the previous literature. In addition, factors that might influence the radial equilibrium such as blade camber angles, solidity and the effect of the distance from the leading edge are also taken into consideration and comparatively analyzed. ª 2015 Production and hosting by Elsevier Ltd. on behalf of CSAA & BUAA.

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“…Tubbs H et al [8] demonstrated a 1 percent rise of efficiency and 6 percent rise of surge margin for the high pressure compressor of IAE V2500 engine by adopting end-bent CDA blades. V. Gümmer et al [9] applied an advanced 3-D blading concept to an engine section stator of the BR710 engine, finding that positive sweep and positive dihedral could reduce endwall losses and largely alleviate the hub corner stall.…”

Section: Introductionmentioning

confidence: 98%

Corner flow control in high through-flow axial commercial fan/booster using blade 3-D optimization

2012

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This study is aimed at using blade 3-D optimization to control corner flows in the high through-flow fan/booster of a high bypass ratio commercial turbofan engine. Two kinds of blade 3-D optimization, end-bending and bow, are focused on. On account of the respective operation mode and environment, the approach to 3-D aerodynamic modeling of rotor blades is different from stator vanes. Based on the understanding of the mechanism of the corner flow and the consideration of intensity problem for rotors, this paper uses a variety of blade 3-D optimization approaches, such as loading distribution optimization, perturbation of departure angles and stacking-axis manipulation, which are suitable for rotors and stators respectively. The obtained 3-D blades and vanes can improve the corner flow features by end-bending and bow effects. The results of this study show that flows in corners of the fan/booster, such as the fan hub region, the tip and hub of the vanes of the booster, are very complex and dominated by 3-D effects. The secondary flows there are found to have a strong detrimental effect on the compressor performance. The effects of both end-bending and bow can improve the flow separation in corners, but the specific ways they work and application scope are somewhat different. Redesigning the blades via blade 3-D optimization to control the corner flow has effectively reduced the loss generation and improved the stall margin by a large amount.

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Using Sweep and Dihedral to Control Three-Dimensional Flow in Transonic Stators of Axial Compressors

Cited by 73 publications

References 14 publications

Aerodynamic analysis of a highly loaded compressor in semi‐closed cycles using a throughflow method

Aerodynamic analysis of a highly loaded compressor in semi‐closed cycles using a throughflow method

Effect of blade sweep on inlet flow in axial compressor cascades

Corner flow control in high through-flow axial commercial fan/booster using blade 3-D optimization

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