Numerical investigation and loss estimation of high-pressure turbine cascade flow with contoured endwall and incoming wakes

Hu, Chenxing; Líu, Hao; Geng, Kaihe; Rong, Rui

doi:10.1016/j.ast.2020.106335

Cited by 11 publications

(4 citation statements)

References 26 publications

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“…In order to analyze the effect of unsteady disturbance upstream of the ITD on the loss generation and flow behaviors, dynamic mode decomposition (DMD) 39-41 can be used to obtain the wake mode from the rotor. The discrete-time series of the snaps V1N=[v1 v2…vN] obtained from CFD results are employed to analyze the information of the structure, frequency, and growth rate of the original flow field.…”

Section: Dmd Methodsmentioning

confidence: 99%

Loss evaluation and aerodynamics investigation of an aggressive intermediate turbine duct under off-design conditions

Geng

et al. 2022

Proceedings of the Institution of Mechanical Engineers, Part G:

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To maximize the performance of the intermediate turbine duct (ITD) under off-design conditions, the loss generation in a one-half stage turbine was quantified using entropy generation and the global entropy generation rate. The numerical results solved by the unsteady Reynolds-averaged Navier–Strokes equations were first verified. Then, the aerodynamic losses within the high-pressure turbine stage were evaluated by efficiency loss under nine operating conditions composed of three rotor speeds and three rotor tip gaps. Finally, the disturbance modes caused by the upstream wake were captured by the dynamic mode decomposition method. Different from the influence of tip gaps, losses of the high-pressure turbine and the ITD are due to the swirl angle display an opposite trend. Under the influence of the interaction between the tip leakage flow and the shroud flow of the ITD, the viscous dissipation and turbulent dissipation increase with a larger tip gap owing to the dominant counter-rotating vortices and secondary flow occurring near the upstream of the ITD shroud. In addition, a large gap seems to enlarge the swirl component of the inflow angle, especially over 80% passage height, leading to greater dissipation losses in these areas. At the ITD inlet, two pairs of counter-rotating vortices at the shroud and the hub are, respectively, captured by the axial velocity mode. Large tip gaps enhance endwall vortices near the shroud and make the up vortex pairs merge into one pair.

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Section: Dmd Methodsmentioning

confidence: 99%

Loss evaluation and aerodynamics investigation of an aggressive intermediate turbine duct under off-design conditions

Geng

et al. 2022

Proceedings of the Institution of Mechanical Engineers, Part G:

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“…In addition, research on controlling PV has been conducted extensively. In related previous studies, leading-edge fillets/bulbs [16,17], non-axisymmetric endwall contour-ing [18][19][20][21], boundary layer endwall fences [22], and undulated blades [23] were used as passive control devices, whereas steady jet blowing [24], pulsed jet blowing [25], air suction [26], and PAs [27] were used as active flow-control devices.…”

Section: Introductionmentioning

confidence: 99%

Active Flow Control for Passage Vortex Reduction in a Linear Turbine Cascade with Various Tip Clearance Sizes Using a Dielectric Barrier Discharge Plasma Actuator

Matsunuma

Segawa

2023

Aerospace

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In an axial-flow turbine of a jet engine used for aircraft propulsion, the passage vortex (PV) and tip leakage vortex (TLV) generated inside the blade passage deteriorate the aerodynamic performance. In this study, a dielectric barrier discharge plasma actuator (PA) was installed in the upstream endwall of the turbine cascade to suppress the PV. The effects of the presence or absence of tip clearance and the change in the size of the tip clearance on the vortex structure at the exit of the turbine cascade were observed by recording the flow velocity distributions using particle image velocimetry. In the absence of tip clearance, only the PV existed and was completely suppressed by the PA. By contrast, in the presence of tip clearance, a TLV occurred in addition to the PV. When the input voltage to the PA was varied with various tip clearance sizes, the change in the flow fields where the PV and TLV interfered was clarified. With tip clearance, the PV was suppressed as the input voltage increased; however, the TLV increased considerably. At each tip clearance size, changes in the center positions of the PV and TLV were observed at varying input voltages of the PA. With increasing input voltages of the PA, the center position of the PV moved to the pressure surface side of the tip of the adjacent blade, and the center position of the TLV moved toward the middle of the flow passage. With a larger tip clearance, the amount of movement at the center positions of both the PV and TLV increased.

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“…Li 21 and Ba 22 applied the casing treatments to improve the aerodynamic performance. Hu 23 studied numerically the influence of the contoured endwall on the aerodynamic performance. Maesschalck [24][25][26] apllied the carved and squealer-like tip to promote the aerodynamic thermal performance and proposed the optimization strategy.…”

Section: Introductionmentioning

confidence: 99%

Experimental and numerical study of novel tip configurations in a turbine cascade

Jin

Song

et al. 2022

Proceedings of the Institution of Mechanical Engineers, Part A:

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Two novel tip modeling methods are proposed in this paper. One novel tip is established by the mathematical method and the other is generated by the B-spline surface. And the genetic algorithm, the orthogonal design and the Kriging model are applied to optimize two kinds of novel tips numerically. The optimal mathematical tip and the optimal B-spline tip are acquired respectively. The aerodynamic tests were investigated at the wind tunnel test section, including the flat tip, the squealer tip, the optimal mathematical tip and the optimal B-spline tip. The static pressure distributions on the casing and the blade surface were measured by the pressure taps. Meanwhile, the secondary flow and the loss were obtained by the five-hole probe at the exit section. A comparison of the simulation analysis results with the experimental results shows good agreement. Compared with the flat tip, the measured loss on the squealer tip, the optimal mathematical tip and the optimal B-spline tip is decreased by 7.2%, 10.5% and 12.6% respectively.

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Numerical investigation and loss estimation of high-pressure turbine cascade flow with contoured endwall and incoming wakes

Cited by 11 publications

References 26 publications

Loss evaluation and aerodynamics investigation of an aggressive intermediate turbine duct under off-design conditions

Loss evaluation and aerodynamics investigation of an aggressive intermediate turbine duct under off-design conditions

Active Flow Control for Passage Vortex Reduction in a Linear Turbine Cascade with Various Tip Clearance Sizes Using a Dielectric Barrier Discharge Plasma Actuator

Experimental and numerical study of novel tip configurations in a turbine cascade

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