The Use of Sweep and Dihedral in Multistage Axial Flow Compressor Blading—Part I: University Research and Methods Development

Gallimore, S. J.; Bolger, John J.; Cumpsty, N. A.; Taylor, Max R.; Wright, Peter I.; Place, James M. M.

doi:10.1115/1.1507333

Cited by 136 publications

(62 citation statements)

References 27 publications

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“…The use of sweep, lean (dihedral), and skew (stacking line in rotational direction) in axial flow compressor rotor has become a matter of interest in the design of turbomachinery blades [23][24][25][26][27][28][29]. The blade shape parameters which are used to construct a threedimensional stacking line is generally introduced to reduce shock losses, corner separation in the blade hub, and tip clearance losses in transonic compressor rotor.…”

Section: Objective Functions and Design Variablesmentioning

confidence: 99%

“…The blade shape parameters which are used to construct a threedimensional stacking line is generally introduced to reduce shock losses, corner separation in the blade hub, and tip clearance losses in transonic compressor rotor. For example, Gallimore et al [23] introduced three-dimensional blade designs using a sweep and a lean in an axial flow compressor rotor for engine. They showed that the positive lean reduced a hub corner and tip clearance losses excepting near the mid-span region.…”

Section: Objective Functions and Design Variablesmentioning

confidence: 99%

See 1 more Smart Citation

Surrogate Based Optimization Techniques for Aerodynamic Design of Turbomachinery

Samad¹,

Kim²

2009

International Journal of Fluid Machinery and Systems

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Recent development of high speed computers and use of optimization techniques have given a big momentum of turbomachinery design replacing expensive experimental cost as well as trial and error approaches. The surrogate based optimization techniques being used for aerodynamic turbomachinery designs coupled with Reynolds-averaged NavierStokes equations analysis involve single-and multi-objective optimization methods. The objectives commonly tried to improve were adiabatic efficiency, pressure ratio, weight etc. Presently coupling the fluid flow and structural analysis is being tried to find better design in terms of weight, flutter and vibration, and turbine life. The present article reviews the surrogate based optimization techniques used recently in turbomachinery shape optimizations.

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Section: Objective Functions and Design Variablesmentioning

confidence: 99%

Section: Objective Functions and Design Variablesmentioning

confidence: 99%

Surrogate Based Optimization Techniques for Aerodynamic Design of Turbomachinery

Samad¹,

Kim²

2009

International Journal of Fluid Machinery and Systems

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“…(Mohammed and Raj, 1977; Yamaguchi, Tominaga and Masutani, 1993; Wadia, Szucs and Crall, 1998). Gallimore et al (2002) found that the application of forward Engineering Applications of Computational Fluid Mechanics Vol. 3, No.…”

Section: Introductionmentioning

confidence: 99%

Aerodynamic Performance of Low Speed Axial Flow Compressor Rotors with Sweep and Tip Clearance

Ramakrishna

Govardhan

2009

Engineering Applications of Computational Fluid Mechanics

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Blade tip gap, though finite, has great influence on the performance of a turbomachine. Tilting the blade sections to the flow direction (blade sweep) would increase the operating range of an axial compressor by modifying the pressure and velocity fields on the suction surface. The present paper investigates the combined effect of these two factors on various flow characteristics in a low speed axial flow compressor. For the present study, six computational domains were modeled: two rotor sweep configurations (0° and 20°) and three different clearance levels for each rotor. Commercial CFD package ANSYS ® CFX 11.0 is used for the simulations. Results indicated that the effect of tip clearance is more predominant in swept rotor than unswept rotor in terms of change in total pressure rise and efficiency. Traced streamlines indicated that blade sweep guides the suction surface boundary layer fluid towards the trailing edge, preventing it from getting accumulated near the tip. Studies near the tip region showed the pattern of velocity streamlines through the tip gap. Tip clearance vortices are found and their trajectory and effect on the flow are studied. Total pressure rise contours at the rotor exit showed that radial migration of low energy boundary layer fluid towards the tip sections is well prevented with sweep.

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“…Results by Li et al [2], Vad [4], and McNulty et al [5] show that sweep blade can improve the aerodynamics performance of fans and compressors, including increasing total-pressure peak value, enhancing efficiency, and widening no-stall range. By both CFD simulations and experiments, Gallimore et al [1,3] investigated sweep blade in hi-speed axial compressors. In their investigations, sweep blade could perform well or badly by stacking airfoil profiles along different dihedral directions.…”

Section: Introductionmentioning

confidence: 99%

“…The sweep blade which is designed by stacking airfoil profiles along a dihedral line has been proved successful in improving the flow stability in recent studies. Compared with the conventional radial-straight-line stacking blade, dihedral-line stacking (sweep) blade can reduce hydraulic losses near tip clearance by controlling secondary flows [1].…”

Section: Introductionmentioning

confidence: 99%

Investigation of the Hydrodynamics of Sweep Blade in Hi-Speed Axial Fuel Pump Impeller

Tao

Yang

Wang

et al. 2013

Advances in Mechanical Engineering

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Fuel pump is a crucial component in aircraft engine ignition system. For the hi-speed axial fuel pumps, rotating stall triggers vortex and affects the operation stability and security. Sweep blade is widely used to solve the stability problems in aerodynamics field. Investigation on the hydrodynamics was conducted in this study. Based on the typical straight blade pump, positive and negative sweep blade pumps were modeled. With the large eddy simulation method, CFD simulations were conducted to calculate and analyze the flow characteristics in the pump models. To verify the simulation, experiments were also launched on the hydraulic test rig. Results show that the vortex occurs at the suction surface of blade and gathers near the blade tip region. Positive sweep blade is effective to reduce the hydraulic losses by driving the stalled fluid into the mid-part of blade. By applying the positive sweep blade on the axial fuel pump, the instability operating region will be diminished. Adopting sweep blade provides an effective means for stability and security of axial fuel pumps.

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The Use of Sweep and Dihedral in Multistage Axial Flow Compressor Blading—Part I: University Research and Methods Development

Cited by 136 publications

References 27 publications

Surrogate Based Optimization Techniques for Aerodynamic Design of Turbomachinery

Surrogate Based Optimization Techniques for Aerodynamic Design of Turbomachinery

Aerodynamic Performance of Low Speed Axial Flow Compressor Rotors with Sweep and Tip Clearance

Investigation of the Hydrodynamics of Sweep Blade in Hi-Speed Axial Fuel Pump Impeller

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