Effect of Axial Velocity Density Ratio on the Performance of a Controlled Diffusion Airfoil Compressor Cascade

Kumaran, Rangarajulu Senthil; Kamble, Sachin S.; Swamy, Kmm; Nagpurwala, Quamber H.; Bhat, Ananthesha

doi:10.1515/tjj-2014-0036

Cited by 4 publications

(1 citation statement)

References 8 publications

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“…When the maximum flow area ratio of the blade is less than 1.053, the angle of the suction surface of the turbine is reduced to three-dimensional separation, the AVDR near hub increases, and the intermediate span AVDR is decreased. Due to the upward contraction of the flow path at the trailing edge of the design C, the AVDR near hub is improved comparing to design D. According to the results published by Kumaran in 2015 [12] , a large separation area would occur in the suction side of a CDA airfoil when the AVDR below certain value, which revealed a linkage between the minimum AVDR and the blockage. A low AVDR area can be seen near the hub of OGV, reflecting a blockage zone at corner zone, which is likely to induce corner separation.…”

Section: Isa 22000rpmmentioning

confidence: 93%

Influence of Meridian Flow Path and Loading Distribution on the Performance of Turbine Rear Frame

Li¹,

Jin²,

Gui³

et al. 2019

Proceedings of Global Power &Amp; Propulsion Society

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The prototype gas turbine has low efficiency and severely deviated outlet flow, thus, the Turbine Rear Frame (TRF) meridian flow path and Outlet Guide Vane (OGV) are redesigned, and the influence of meridian flow path and the different loading distribution on the internal flow field structure is analyzed by CFD calculations. The results show that when the maximum flow area ratio of the blade area is too high, separation will occur. The flow path design with a character that expand first and then contract can suppress the corner separation. The load distribution of OGV will affect the deflection distribution. Moving the maximum deflection position backwards can make the blade suction side turn smoothly, which is beneficial to reduce the axial adverse pressure gradient and relieve the suction surface corner separation. The transition-loaded airfoil can form an endwall bend on the suction side of the blade, reduce the cross flow in the channel, and alleviate the corner separation. After the retrofit design, the turbine efficiency can be increased by 6% or more, and the pressure recovery coefficient of OGV has a rise of more than 0.08, the outlet flow deviation after OGV is less than 3.5º (15.864º for prototype).

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Section: Isa 22000rpmmentioning

confidence: 93%

Influence of Meridian Flow Path and Loading Distribution on the Performance of Turbine Rear Frame

Li¹,

Jin²,

Gui³

et al. 2019

Proceedings of Global Power &Amp; Propulsion Society

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Flow quality improvement of the wind tunnel testing for a highly-loaded compressor cascade at high incidence

Cai

Gao

et al. 2022

International Journal of Turbo &Amp; Jet-Engines

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To obtain reliable and accurate experimental data in cascade testing, the influencing factors and the improving method of the flow quality of a highly-loaded compressor cascade under high incidence were investigated through a series of numerical simulations and experiments. The numerical method was validated by experimental data and agreed well at both incidence angles of 0° and 6°. Under the original upper end wall, both experimental and numerical results indicated an unsatisfactory flow quality of the cascade with an obvious nonuniformity of inlet Mach number, and the incidence of the central blade is 3.6° larger than the theoretical value. Using a small curved upper wall can reduce the severe flow separation on the upper wall and achieve a maximum improvement in flow quality under the critical installation angle, where the incidence deviation of the central blade was reduced to 2.1°. Using the combination of adjustable tailboards and a small curved upper end wall can further improve the cascade flow quality. Under the optimal angle of the tailboards, both the inflow uniformity and the outflow periodicity of the three middle blade passages the test requirements, and the incidence deviation of the central blade is reduced to 0.2°.

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A Novel Quasi-3D Method for Cascade Flow Considering Axial Velocity Density Ratio

Chen

Zhou

et al. 2018

International Journal of Turbo &Amp; Jet-Engines

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A novel quasi-3D Computational Fluid Dynamics (CFD) method of mid-span flow simulation for compressor cascades is proposed. Two dimension (2D) Reynolds-Averaged Navier-Stokes (RANS) method is shown facing challenge in predicting mid-span flow with a unity Axial Velocity Density Ratio (AVDR). Three dimension (3D) RANS solution also shows distinct discrepancies if the AVDR is not predicted correctly. In this paper, 2D and 3D CFD results discrepancies are analyzed and a novel quasi-3D CFD method is proposed. The new quasi-3D model is derived by reducing 3D RANS Finite Volume Method (FVM) discretization over a one-spanwise-layer structured mesh cell. The sidewall effect is considered by two parts. The first part is explicit interface fluxes of mass, momentum and energy as well as turbulence. The second part is a cell boundary scaling factor representing sidewall boundary layer contraction. The performance of the novel quasi-3D method is validated on mid-span pressure distribution, pressure loss and shock prediction of two typical cascades. The results show good agreement with the experiment data on cascade SJ301-20 and cascade AC6-10 at all test condition. The proposed quasi-3D method shows superior accuracy over traditional 2D RANS method and 3D RANS method in performance prediction of compressor cascade.

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Effect of Axial Velocity Density Ratio on the Performance of a Controlled Diffusion Airfoil Compressor Cascade

Cited by 4 publications

References 8 publications

Influence of Meridian Flow Path and Loading Distribution on the Performance of Turbine Rear Frame

Influence of Meridian Flow Path and Loading Distribution on the Performance of Turbine Rear Frame

Flow quality improvement of the wind tunnel testing for a highly-loaded compressor cascade at high incidence

A Novel Quasi-3D Method for Cascade Flow Considering Axial Velocity Density Ratio

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