On the Aerodynamics of Swept and Leaned Transonic Compressor Rotors

Benini, Ernesto; Biollo, Roberto

doi:10.1115/gt2006-90547

Cited by 22 publications

(16 citation statements)

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“…Interestingly they claimed that the highest efficiency gain was obtained with backward sweep and an optimized S-shaped camber line without losing a stall margin. That could support a finding of Benini and Biollo [5] where a backward-swept rotor had a higher efficiency and a larger choke flow than both the datum and a forward-swept design, posing against the general agreement on blade sweep. It can be assumed that when more blade design parameters are involved in transonic rotor design the current knowledge on blade lean and sweep only might need to change.…”

Section: Numerical Efforts Of Aerodynamic Re-design In a Single-stagementioning

confidence: 58%

“…However, their modified blades did not represent the best that could be produced for the applied lean (and/or sweep) because of no changes at each blade section. Benini and Biollo [5] numerically investigated the impact of axially-swept and tangentially-leaned shapes on the NASA Rotor 37 datum, and confirmed that a positively-leaned rotor had a substantial increment of efficiency and a reduction of shock strength. As mentioned in their paper, no attempts were made to change other blade design parameters like camber, supposing findings cannot be generalized.…”

Section: Numerical Efforts Of Aerodynamic Re-design In a Single-stagementioning

confidence: 82%

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Numerical Efforts of Aerodynamic Re-Design in a Single-Stage Transonic Axial Compressor: Part 1 — Stator Design

2017

Volume 2A: Turbomachinery

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In many aerodynamic design parameters for the axial-flow compressor, three variables of tailored blading, blade lean and sweep were considered in the re-design efforts of a transonic single stage which had been designed in 1960’s NASA public domains. As Part 1, the re-design was limited to the stator vane only. For the original MCA (Multiple Circular Arc) blading, which had been applied at all radii, the CDA (Controlled Diffusion Airfoil) blading was introduced at midspan as the first variant, and the endwalls of hub and casing (or tip) were replaced with the DCA (Double Circular Arc) blading for the second variant. Aerodynamic performance was predicted through a series of CFD analysis at design speed, and the best aerodynamic improvement, in terms of pressure ratio/efficiency and operability, was found in the first variant of tailored blading. It was selected as a baseline for the next design efforts with blade lean, sweep and both combined. Among 12 variants, a case of positively and mildly leaned blades was found the most attractive one, relative to the original design, providing benefits of an 1.0% increase of pressure ratio at design flow, an 1.7% increase of efficiency at design flow, a 10.5% increase of the surge margin and a 32.3% increase of the choke margin.

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Section: Numerical Efforts Of Aerodynamic Re-design In a Single-stagementioning

confidence: 58%

Section: Numerical Efforts Of Aerodynamic Re-design In a Single-stagementioning

confidence: 82%

Numerical Efforts of Aerodynamic Re-Design in a Single-Stage Transonic Axial Compressor: Part 1 — Stator Design

2017

Volume 2A: Turbomachinery

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“…As mentioned in [16,17], it is weakening the passage's shock and it is reducing loss core near the tip of the suction surface. A recent numerical work gave a point of view on the impact of blade curvature in transonic compressor rotors, showing how the movement of blade sections in the tangential direction can influence the internal flow field [18,19]. Another research group investigated the aerodynamic effects induced by several tangential blade curvatures on the same rotor.…”

Section: Mixing Between Blade-to-blade Plane Group and Hub-to-shroud mentioning

confidence: 99%

Design Optimization of a Transonic-Fan Rotor Using Numerical Computations of the Full Compressible Navier-Stokes Equations and Simplex Algorithm

Aziz¹,

Owis

Abdelrahman

2014

International Journal of Rotating Machinery

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The design of a transonic-fan rotor is optimized using numerical computations of the full three-dimensional Navier-Stokes equations. The CFDRC-ACE multiphysics module, which is a pressure-based solver, is used for the numerical simulation. The code is coupled with simplex optimization algorithm. The optimization process is started from a suitable design point obtained using low fidelity analytical methods that is based on experimental correlations for the pressure losses and blade deviation angle. The fan blade shape is defined by its stacking line and airfoil shape which are considered the optimization parameters. The stacking line is defined by lean, sweep, and skews, while blade airfoil shape is modified considering the thickness and camber distributions. The optimization has been performed to maximize the rotor total pressure ratio while keeping the rotor efficiency and surge margin above certain required values. The results obtained are verified with the experimental data of Rotor 67. In addition, the results of the optimized fan indicate that the optimum design is found to be leaned in the direction of rotation and has a forward sweep from the hub to mean section and backward sweep to the tip. The pressure ratio increases from 1.427 to 1.627 at the design speed and mass flow rate.

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“…Generally, active flow control methods mainly include aspiration/suction techniques, tip injection (Taghavi-Zenouz et al, 2018), plasma actuator (Akcayoz et al, 2016) and acoustic excitation (Yarusevych et al, 2005). The latter is mainly composed of sweep and dihedral (Copenhaver et al, 1996;Benini et al, 2007), casing treatment (Mao et al, 2018a;2018c), blade tip winglet (Zhong et al, 2013;Jung et al, 2018), vortex generators (Hergt et al, 2012) and non-axisymmetric endwall (Liu et al, 2017).…”

Section: Introductionmentioning

confidence: 99%

Impact of Boundary Layer Suction on Clearance Leakage Flow in a Cantilever Stator of Transonic Compressor

Zhang

Liu

et al. 2020

JAFM

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To control secondary flow effects and enhance the aerodynamic performance of the compressor, the flow control effects of the flow suction at the endwall with different circumferential positions and at the blade tip were numerically investigated in the cantilever stator of an axial single-stage transonic compressor. The main purpose was to gain a better understanding of the application of boundary layer suction and the associated control mechanisms in the cantilever stator. The studies show that the optimal position of the endwall suction slot should be located up the stator blade, in terms of the leakage flow structures and the blade tip unloading effect. In addition, the flow control effects of the suction at the blade tip on leakage flow upstream is better than that of the endwall flow suction with the same structure. Further, the studies of compressor aerodynamic performance curves illustrate that the efficiency and pressure ratio is increased by 0.34% and 1.09% at the peak efficiency point, and are increased by 0.39% and 0.14% at the near stall point, respectively.

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On the Aerodynamics of Swept and Leaned Transonic Compressor Rotors

Abstract: ASME PAPER GT-2006-9054

Cited by 22 publications

References 0 publications

Numerical Efforts of Aerodynamic Re-Design in a Single-Stage Transonic Axial Compressor: Part 1 — Stator Design

Numerical Efforts of Aerodynamic Re-Design in a Single-Stage Transonic Axial Compressor: Part 1 — Stator Design

Design Optimization of a Transonic-Fan Rotor Using Numerical Computations of the Full Compressible Navier-Stokes Equations and Simplex Algorithm

Impact of Boundary Layer Suction on Clearance Leakage Flow in a Cantilever Stator of Transonic Compressor

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