Modeling the 3-D Flow Effects on Deviation Angle for Axial Compressor Middle Stages

Roberts, W. B.; Serovy, G. K.; Sandercock, D. M.

doi:10.1115/1.3239859

Cited by 32 publications

(18 citation statements)

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“…The effect of tip clearance flow on deviation is accounted for by the deviation model of Lakshminarayana (1970). 3D deviation and losses are distributed over the blade span by functions adopted from Roberts et al (1986). The overall level of losses of the tip clearance and of the secondary flow model is adjusted manually to receive a design point efficiency that is close to the RANS results of the baseline.…”

Section: Throughflow Setupmentioning

confidence: 99%

Design optimization of a multi-stage axial compressor using throughflow and a database of optimal airfoils

Schnoes

Voß

Nicke

2018

J. Glob. Power Propuls Soc.

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The basic tool set to design multi-stage axial compressors consists of fast codes for throughflow and blade-to-blade analysis. Detailed blade row design is conducted with 3D CFD, mainly to control the end wall flow. This work focuses on the interaction between throughflow and blade-to-blade design and the transition to 3D CFD. A design strategy is presented that is based on a versatile airfoil family. The new class of airfoils is generated by optimizing a large number of airfoil shapes for varying design requirements. Each airfoil geometry satisfies the need for a wide working range as well as low losses. Based on this data, machine learning is applied to estimate optimal airfoil shape and performance. The performance prediction is incorporated into the throughflow code. Based on a throughflow design, the airfoils can be stacked automatically to generate 3D blades. On this basis, a 3D CFD setup can be derived. This strategy is applied to study upgrade options for a 15-stage stationary gas turbine compressor test rig. At first, the behavior of the new airfoils is studied in detail. Afterwards, the design is optimized for mass flow rate as well as efficiency. Selected configurations from the Pareto-front are evaluated with 3D CFD.

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Section: Throughflow Setupmentioning

confidence: 99%

Design optimization of a multi-stage axial compressor using throughflow and a database of optimal airfoils

Schnoes

Voß

Nicke

2018

J. Glob. Power Propuls Soc.

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“…According to Roberts et al [18] parametric spanwise curves have been averaged along the blade height to obtain mean contributions, which depend on operational parameters like end-wall boundary layer displacement thicknesses, blade camber and solidity, channel aspect ratio, or wheel tip clearance.…”

Section: Velocity Trianglesmentioning

confidence: 99%

A quasi-one-dimensional CFD model for multistage turbomachines

Léonard

Adam

2008

J. Therm. Sci.

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The objective of this paper is to present a fast and reliable CFD model that is able to simulate stationary and transient operations of multistage compressors and turbines. This analysis tool is based on an adapted version of the Euler equations solved by a time-marching, finite-volume method. The Euler equations have been extended by including source terms expressing the blade-flow interactions. These source terms are determined using the velocity triangles and a row-by-row representation of the blading at mid-span. The losses and deviations undergone by the fluid across each blade row are supplied by correlations. The resulting flow solver is a performance prediction tool based only on the machine geometry, offering the possibility of exploring the entire characteristic map of a multistage compressor or turbine. Its efficiency in terms of CPU time makes it possible to couple it to an optimization algorithm or to a gas turbine performance tool. Different test-cases are presented for which the calculated characteristic maps are compared to experimental ones.

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“…The empirical correlations used here for the classical throughflow computations mispredict the mean level of the deviation angle at the outlet of the compressor stage by 2-3 degrees. The 3-D loss correlations of Roberts [16] used in the classical throughflow, while providing the correct level of underturning, The figure 17, giving the total temperature, highlights the radial mixing phenomenon, which is relatively weak in this machine, but nevertheless present. The Navier-Stokes throughflow computation without radial mixing model over-predicts the temperature at the walls.…”

Section: Classical Versus High-order Throughflowmentioning

confidence: 99%

On the Role of the Deterministic and Circumferential Stresses in Throughflow Calculations

Simon

Thomas

Léonard

2009

Journal of Turbomachinery

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This paper presents a throughflow analysis tool developed in the context of the average-passage flow model elaborated by Adamczyk. The Adamczyk's flow model describes the 3-D timeaveraged flow field within a blade row passage. The set of equations that governs this flow field is obtained by performing a Reynolds averaging, a time averaging and a passage-to-passage averaging on the Navier-Stokes equations. The throughflow level of approximation is obtained by performing an additional circumferential averaging on the 3-D average-passage flow.The resulting set of equations is similar to the 2-D axisymmetric Navier-Stokes equations but additional terms resulting from the averages show up : blade forces, blade blockage factor, Reynolds stresses, deterministic stresses, passage-to-passage stresses and circumferential stresses. This set of equations represents the ultimate throughflow model provided that all stresses and blade forces can be modeled. The relative importance of these additional terms is studied in the present contribution.The stresses and the blade forces are determined from 3-D steady and unsteady databases (a low speed compressor stage and a transonic turbine stage) and incorporated in a throughflow model based on the axisymmetric Navier-Stokes equations. A good agreement between the throughflow solution and the averaged 3-D results is obtained. These results are also compared to those obtained with a more "classical" throughflow approach based on a Navier-Stokes formulation for the endwall losses, correlations for profile losses and a simple radial mixing model assuming turbulent diffusion. INTRODUCTIONThe throughflow level of approximation still remains an important tool for designing turbomachines [10] even though 3-D calculations are used more and more early in the design process. Throughflow codes are mainly used at the preliminary design stage for specifying the target aerodynamic performances to be achieved by the blading. They can be used either in the design mode, where the angular momentum and/or the total conditions are prescribed and the flow angles are sought, either in the analysis mode, where a known machine geometry is analyzed for its performance. The throughflow models are also used to exploit experimental results or to couple single blade row calculations in order to compute the flow field inside a multistage machine [4].Unfortunately, these models heavily rely on empirical inputs, such as profile losses correlations or end-wall loss models. They can accurately predict the flow field inside a turbomachine provided that the design parameters are not too far from those of the reference machines that were used to calibrate the throughflow model. This approach has shown to be efficient but lacks of generality.The most widespread throughflow method is certainly the streamline curvature method (SLC). In 1980, Spuur has proposed another approach based on the Euler equations. This approach has only started to retain attention in the 1990. Recent works using this approach can be foun...

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Modeling the 3-D Flow Effects on Deviation Angle for Axial Compressor Middle Stages

Cited by 32 publications

References 0 publications

Design optimization of a multi-stage axial compressor using throughflow and a database of optimal airfoils

Design optimization of a multi-stage axial compressor using throughflow and a database of optimal airfoils

A quasi-one-dimensional CFD model for multistage turbomachines

On the Role of the Deterministic and Circumferential Stresses in Throughflow Calculations

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