Application of Non-Axisymmetric Endwall Contouring to Conventional and High-Lift Turbine Airfoils

Praisner, T. J.; Allen-Bradley, E.; Grover, E. A.; Knezevici, D. C.; Sjolander, S. A.

doi:10.1115/gt2007-27579

Cited by 45 publications

(36 citation statements)

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“…Praisner et al [3] also presented a CFD investigation into non-axisymmetric endwall contouring in a family of three turbine airfoils. The results predicted benefit in row loss reduction.…”

Section: Nomenclaturementioning

confidence: 97%

Numerical investigation of a high-subsonic axial-flow compressor rotor with non-axisymmetric hub endwall

Lu²,

Zhang³

et al. 2010

J. Therm. Sci.

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The major source of loss in modern compressors is the secondary loss. Non-axisymmetric endwall profile contouring is now a well established design methodology in axial flow turbines. However, flow development in axial compressors is differ from turbines, the effects of non-axisymmetric endwall to axial compressors requires flow analysis in detail. This paper presents both experimental and numerical data to deal with the application of a non-axisymmetric hub endwall in a high-subsonic axial-flow compressor. The aims of the experiment here were to make sure the numerically obtained flow fields is the physical mechanism responsible for the improvement in efficiency, due to the non-axisymmetric hub endwall. The computational results were first compared with available measured data of axisymmetric hub endwall. The results agreed well with the experimental data for estimation of the global performance. The coupled flow of the compressor rotor with non-axisymmetric hub endwall was simulated by a state-of-the-art multi-block flow solver. The non-axisymmetric hub endwall was designed for a subsonic compressor rotor with the help of sine and cosine functions. This type of non-axisymmetric hub endwall was found to have a significant improvement in efficiency of 0.45% approximately and a slightly increase for the total pressure ratio. The fundamental mechanisms of non-axisymmetric hub endwall and their effects on the subsonic axial-flow compressor endwall flow field were analyzed in detail. It is concluded that the non-axisymmetric endwall profiling, though not optimum, can mitigate the secondary flow in the vicinity of the hub endwall, resulting in the improvement of aerodynamic performance of the compressor rotor.

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“…Praisner et al [3] also presented a CFD investigation into non-axisymmetric endwall contouring in a family of three turbine airfoils. The results predicted benefit in row loss reduction.…”

Section: Nomenclaturementioning

confidence: 97%

Numerical investigation of a high-subsonic axial-flow compressor rotor with non-axisymmetric hub endwall

Lu²,

Zhang³

et al. 2010

J. Therm. Sci.

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“…Pralsner et al [20] Endwall profiling Total pressure loss coefficient, SKE and TKE (turbulent kinetic energy) Ingram et al [9] Endwall profiling Exit flow angle deviation Germain et al [21] Endwall profiling Combination of total pressure loss coefficient and CSKE Schüpbach et al [22] Endwall profiling CSKE Moon and Koh [2] Streamwise endwall fence Stream wise vorticity no slip condition and are adiabatic. At inlet experimentally measured total pressure profile for 0…”

Section: Numerical Methodologymentioning

confidence: 99%

Secondary Flow Loss Reduction in a Turbine Cascade with a Linearly Varied Height Streamwise Endwall Fence

Kumar

Govardhan

2011

International Journal of Rotating Machinery

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The present study attempts to reduce secondary flow losses by application of streamwise endwall fence. After comprehensive analysis on selection of objective function for secondary flow loss reduction, coefficient of secondary kinetic energy (CSKE) is selected as the objective function in this study. A fence whose height varies linearly from the leading edge to the trailing edge and located in the middle of the flow passage produces least CSKE and is the optimum fence. The reduction in CSKE by the optimum fence is 27% compared to the baseline case. The geometry of the fence is new and is reported for the first time. Idea of this fence comes from the fact that the size of the passage vortex (which is the prime component of secondary flow) increases as it travels downstream, hence the height of fence should vary as the objective of fence is to block the passage vortex from crossing the passage and impinging on suction surface of the blade. Optimum fence reduced overturning and underturning of flow by more than 50% compared to the baseline case. Magnitude and spanwise penetration of the passage vortex were reduced considerably compared to the baseline case.

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“…Secondary losses in turbine and compressor blade rows have been the topic of many investigations over the past decades. Means of secondary losses reduction via the application of endwall contouring have been the subject of several investigations, such as the ones from Hoeger et al (2002), Harvey (2008), Reising and Schiffer (2009a), Lepot et al (2011) and Hergt et al (2011) on compressor rows, and the ones from Praisner et al (2007), Knezevici (2011) and Taremi and Sjolander (2011) on turbine rows.…”

Section: Research Objectivesmentioning

confidence: 99%

“…Non-axisymmetric endwall contouring is used as another approach to control the endwall flow. This approach was originally developed on axial flow turbines and its effect on endwall flow and on the blade row losses has been the subject of several investigations, such as the ones from Rose (1994), Harvey et al (2000), Hartland et al (2000) and more recently, Praisner et al (2007) and Knezevici et al (2008). The application of non-axisymmetric endwall contouring as a means of endwall flow control on compressor blade rows has only been the subject of recent studies, with the work of Harvey (2008), Schiffer (2009a, 2009b), Lu et al (2009) and Lepot et al (2011).…”

Section: Non-axisymmetric Endwall Contouringmentioning

confidence: 99%

“…For a turbine cascade, the main objective of endwall contouring is to reduce the secondary losses. This can be done by reducing the strength of the cross-passage flow and retarding the development of the passage vortex (Taremi and Sjolander, 2011;Knezevici et al, 2010;Praisner et al, 2007). For a compressor cascade, in addition to reducing secondary losses, it is also desired to reduce or remove the corner stall, as this is a major source of loss.…”

Section: Endwall Contouringmentioning

confidence: 99%

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Controlling Secondary Flows in Highly-Loaded Compressor Cascades

Prevost¹

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This thesis documents the experimental results of a research program investigating the effect of non-axisymmetric endwall contouring on the secondary flows and loss generation in a highly-loaded compressor cascade. The results are compared with the losses for the baseline flat endwall in order to evaluate the potential benefits.The compressor blade was designed by Pratt & Whitney Aircraft and is representative of an exit guide vane row in an aircraft engine. The experimental study was conducted in Carleton University's low speed linear cascade wind tunnel. The measurements were made at a constant Reynolds number of 150,000 (based on the axial chord and the inlet velocity) for two values of incidence, 0° (design incidence) and +7°.Quantitative results were obtained from static pressure measurements on the suction and pressure surfaces of the blade to evaluate the blade loadings and from measurements made by a seven-hole pressure probe downstream of the cascade to assess the blade row losses. Qualitative results were obtained from oil surface flow visualisation on the endwall and on the blade surfaces and were used to assist in the interpretation of the flow physics.The current research showed that the application of non-axisymmetric endwall contouring at design incidence modified the secondary flows near the endwall, mitigating the formation of the corner stall. The benefits from contouring were observed in terms of reductions in the secondary losses and in the underturning of the secondary flows compared to the flat endwall test case.However, these benefits were not observed at the off-design incidence studied. The application of endwall contouring generated higher secondary kinetic energy near the endwall, which penetrated deeper along the span and occupied a larger area, resulting in higher secondary and total losses as it dissipated moving downstream of the cascade.iii

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Application of Non-Axisymmetric Endwall Contouring to Conventional and High-Lift Turbine Airfoils

Cited by 45 publications

References 0 publications

Numerical investigation of a high-subsonic axial-flow compressor rotor with non-axisymmetric hub endwall

Numerical investigation of a high-subsonic axial-flow compressor rotor with non-axisymmetric hub endwall

Secondary Flow Loss Reduction in a Turbine Cascade with a Linearly Varied Height Streamwise Endwall Fence

Controlling Secondary Flows in Highly-Loaded Compressor Cascades

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