Effect of Various Tip Clearance Squealer Design on Turbine Stage Efficiency

Lomakin, Nikolay; Granovskiy, Andrey; Shchaulov, Vladimir; Szwedowicz, J.

doi:10.1115/gt2015-42726

Cited by 5 publications

(4 citation statements)

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“…Silva et al [10] used numerical methods to analyze the influence of the depth of the cavity in the high-pressure turbine on the turbine efficiency and heat transfer conditions. Lomakin et al [11] studied the effect of different groove types on the efficiency of the turbine stage, and pointed out that the sealing effect of the groove tip on the clearance leakage is related to the thickness of the blade. Jung et al [12] used numerical methods to explore the aerodynamic loss mechanism of high-pressure turbines.…”

Section: Introductionmentioning

confidence: 99%

Effects of Groove Structure on Aerodynamic Performance of a Turbine Blade

Fan¹,

Wu²,

Zhou³

et al. 2022

Proceedings of Global Power &Amp; Propulsion Society

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In the tip gap between a blade and the casing, there are many highly three-dimensional and complex flow structures, which leads to significantly reduce the aerodynamic performance of a turbine. And the interaction between the tip leakage flow and the main passage flow is a substantial source of aerodynamic loss. In order to minimize the flow loss caused by the tip clearance leakage flow to the high-pressure turbine blades, the first-stage rotor of the GE-E3 high-pressure turbine introduced a groove structure and optimized the design parameters. Firstly, the control effect of the groove structure is proved.Then the influence of the design parameter of groove depth on the control effect is studied. Finally, based on the uniform design method, the flow control effect of the groove structure with different design parameter combinations is numerically simulated to obtain the optimal design plan for controlling the tip clearance leakage flow. The results show that there is an optimal groove depth value; the total pressure loss coefficient at the 110% axial chord length is reduced by 9.84%, and the rotor blade efficiency is increased by 0.323%. The obstructive effect of the groove structure causes the airflow to separate after passing through the pressure surface to form a return zone, which hinders the leakage flow and reduces the leakage loss.

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Section: Introductionmentioning

confidence: 99%

Effects of Groove Structure on Aerodynamic Performance of a Turbine Blade

Fan¹,

Wu²,

Zhou³

et al. 2022

Proceedings of Global Power &Amp; Propulsion Society

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show abstract

“…[7][8][9] In the early stage, researchers studied the effect of single side squealer tip on TLF through experiments and numerical methods and found that the suction side squealer tip has a better blocking effect on the TLF. 10,11 Then, more and more researchers focused on the geometric optimization of the squealer tip, such as the number and layout of rims, [12][13][14] cutback configurations, 15,16 and the width and depth of rims. 17,18 The researchers from the von Karman Institute for Fluid Dynamics (VKI) [19][20][21] tried to optimize the squealer-like tip geometry by using the differential evolution algorithm and finally obtained the double-cavity tip configuration with great aerodynamic and thermal performance.…”

Section: Introductionmentioning

confidence: 99%

Effects of inclined squealer rims on tip leakage vortex and loss in a transonic axial turbine

Wang

Zhang

et al. 2022

Proceedings of the Institution of Mechanical Engineers, Part A:

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In this paper, to investigate the effects of inclined squealer rims on tip leakage flow and loss, numerical simulations have been performed on a transonic high-pressure turbine. Based on the geometry of prototype with conventional cavity tip, six modifications with different inclined rims are constructed. The effects of inclined suction side squealer rim (SSSR) on tip leakage flow (TLF) is analyzed emphatically. The results show that it is advantageous to control the TLF and loss if the internal and external surface of SSSR are inclined in a proper direction. When the internal surface of SSSR is inclined toward the cavity, the scraping vortex and its pneumatic labyrinth sealing effect are enhanced, which is beneficial to blocking the TLF and reducing the mixing loss. As the external surface of SSSR is inclined toward the passage, the pressure gradient near the tip changes and the intensity of adverse pressure gradient decreases, which is conducive to suppressing the breakdown of tip leakage vortex (TLV). In addition, the inclined external surface could make the TLV away from the blade and reduce the viscous dissipation. Regarding the aerodynamic performance of the turbine, the inclined pressure side squealer rim (PSSR) could improve the stage efficiency of the turbine by 0.08% relative to the prototype, while the proper inclined SSSR could further improve that by 0.18%.

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“…It was found that the squealer tip performs well in terms of both aerodynamic and heat transfer characteristics. Lomakin et al 17) studied nine variants of squealer tips based on CFD simulation. The effects of partial squealer extension and rim inclination were the main focus.…”

Section: Introductionmentioning

confidence: 99%