Recent advances in transonic axial compressor aerodynamics

Biollo, Roberto; Benini, Ernesto

doi:10.1016/j.paerosci.2012.05.002

Cited by 63 publications

(26 citation statements)

References 90 publications

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“…The development of modern aircraft compressors aims to increase pressure ratios and to reduce weights at once [1,2]. The advantages resulting from this design approach, which lead to a reduced number of stages and compactness, are a lower fuel consumption and an increased overall performance.…”

Section: Introductionmentioning

confidence: 99%

Accurate 2-D Modelling of Transonic Compressor Cascade Aerodynamics

2019

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Modern aeronautic fans are characterised by a transonic flow regime near the blade tip. Transonic cascades enable higher pressure ratios by a complex system of shockwaves arising across the blade passage, which has to be correctly reproduced in order to predict the performance and the operative range. In this paper, we present an accurate two-dimensional numerical modelling of the ARL-SL19 transonic compressor cascade. A large series of data from experimental tests in supersonic wind tunnel facilities has been used to validate a computational fluid dynamic model, in which the choice of turbulence closure resulted critical for an accurate reproduction of shockwave-boundary layer interaction. The model has been subsequently employed to carry out a parametric study in order to assess the influence of main flow variables (inlet Mach number, static pressure ratio) and geometric parameters (solidity) on the shockwave pattern and exit status. The main objectives of the present work are to perform a parametric study for investigating the effects of the abovementioned variables on the cascade performance, in terms of total-pressure loss coefficient, and on the shockwave pattern and to provide a quite large series of data useful for a preliminary design of a transonic compressor rotor section. After deriving the relation between inlet and exit quantities, peculiar to transonic compressors, exit Mach number, mean exit flow angle and total-pressure loss coefficient have been examined for a variety of boundary conditions and parametrically linked to inlet variables. Flow visualisation has been used to describe the shock-wave pattern as a function of the static pressure ratio. Finally, the influence of cascade solidity has been examined, showing a potential reduction of total-pressure loss coefficient by employing a higher solidity, due to a significant modification of shockwave system across the cascade.

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Section: Introductionmentioning

confidence: 99%

Accurate 2-D Modelling of Transonic Compressor Cascade Aerodynamics

2019

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“…Pierret et al [4] proposed using mean camber line distribution as a design variable. However, as discussed by various authors [10][11][12], flow properties also depend strongly on blade curvature; thus a direct control on the variation of the blade angles along the blade chord is also important to control diffusion.…”

Section: Blade Parameterizationmentioning

confidence: 99%

A 3D Parameterization for Transonic Fan Blade Multidisciplinary Design

Trépanier¹

2017

AAOAJ

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This paper presents a new tridimensional approach for transonic fan blade design. The proposed parameterization uses parameters closely linked to aerodynamic performance of blades, such as beta angles and thickness distributions and allows the control of these parameters in both axial and spans wise directions independently. In addition, a multi-level modification approach is presented, which allows modifying the blade geometry locally or globally. This multi-level approach enables to use a reduced number of parameters for preliminary design optimizations and to switch, in a seamless way, to higher precision for final design optimizations. The parameterization is validated by the replication and modification of the NASA Rotor 67 and examples are given of the application of the parameterization to multidisciplinary fan blade design.

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“…The supersonic compressor cascades are mainly subjected to two sources (Bölcs et al, 1986) of aerodynamic losses: the entropy rise across the shock wave and the losses originated in the shock wave boundary layer interaction (SWBLI) process. Weakening the shock wave intensity by means of reducing the Mach number ahead of the shock wave or moving the normal shock wave to an oblique shock wave can moderate the entropy rise and has been widely studied in former studies (Liu et al, 2017;Biollo et al, 2013;Calvert et al, 1994). Thus the current study focuses on the reduction of losses originated in the SWBLI.…”

Section: Introductionmentioning

confidence: 99%

Large Eddy Simulation of Pulsed Blowing in a Supersonic Compressor Cascade

Meng

Chen

Ding

et al. 2020

JAFM

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Large Eddy Simulation (LES) of a two dimensional supersonic compressor cascade is performed in the current study. It is found that the Shock Wave Boundary Layer Interaction causes a large scale of total pressure losses and presents strong fluctuation features. Thus the pulsed and steady excitation jets are applied to suppress the flow separations and to reduce the total pressure losses. Several impacting parameters, such as jet axial location, jet hole width, jet angle to the local blade surface and jet mass flowrate are chosen based on the primary analysis by the calculations by the Reynolds Averaged Navier-Stokes equations. In addition, based on the results of frequency spectrum and POD analysis, the excitation jet frequency is chosen for the pulsed excitation jet scheme. It is concluded that the pulsed excitation jet scheme achieves a 9.8% reduction of total pressure loss in comparison to the steady excitation jet scheme under the same time-averaged excitation jet mass flow rate. The excitation jets affect both the flow field near the jet hole on the suction surface and the flow field on the pressure surface via the management of the reflection shock wave. In addition, the excitation frequency dominates not only the time-averaged flow field, but also the second and third modes which stand for the unsteady structures in the flow field under the POD analysis. The first mode contains most energy in the flow field and the energy percentage decreases dramatically with the increase of the mode number. In comparison to the steady excitation jet scheme, the pulsed excitation jet scheme gathers more energy to the low orders of the modes, especially the first four modes. With the mixing effect and high dissipation rate of the high-frequency signals, the high-frequency signals shrink in the wake and the flow field builds up more uniformity.

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Recent advances in transonic axial compressor aerodynamics

Cited by 63 publications

References 90 publications

Accurate 2-D Modelling of Transonic Compressor Cascade Aerodynamics

Accurate 2-D Modelling of Transonic Compressor Cascade Aerodynamics

A 3D Parameterization for Transonic Fan Blade Multidisciplinary Design

Large Eddy Simulation of Pulsed Blowing in a Supersonic Compressor Cascade

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