Results 181 to 190 of about 402 (231)

Heat Transfer Coefficient on the Squealer Tip and Near Squealer Tip Regions of a Gas Turbine Blade

Heat Transfer, Volume 4, 2002
Detailed heat transfer coefficient distributions on a squealer tip of a gas turbine blade were measured using a hue detection based transient liquid crystals technique. The heat transfer coefficients on the shroud and near tip region of the pressure and suction sides of a blade were also measured.
Jae Su Kwak, Je-Chin Han
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Heat Transfer Coefficients on the Squealer Tip and Near-Tip Regions of a Gas Turbine Blade With Single or Double Squealer

Journal of Turbomachinery, 2003
Detailed heat transfer coefficient distributions on a gas turbine squealer tip blade were measured using a hue detection based transient liquid-crystals technique. The heat transfer coefficients on the shroud and near tip regions of the pressure and suction sides of a blade were also measured.
Jae Su Kwak, Jaeyong Ahn, Je-Chin Han, C. Pang Lee, Robert Boyle, Raymond Gaugler, Ronald S. Bunker   +6 more
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Influences of Squealer Tip Geometrical Characteristics on Tip-leakage Flow in Turbine Rotor

Proceedings of Global Power & Propulsion Society, 2022
Tip-leakage loss caused by tip-leakage flow is an important source of aerodynamic loss in turbine rotor. Squealer tips are often used to control the tip-leakge flow and loss. In this paper, a transonic single-stage high-pressure turbine is simulated numerically to investigate the effects of cavity width and height on tip-leakage flow and loss. Based on
Yufan Wang, Weihao Zhang*, Zhengping Zou, Shoumin Jiang, Zhenzhe Na, Yun Chen   +5 more
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Aerodynamic losses for squealer tip with different winglets

Journal of Mechanical Science and Technology, 2019
Aerodynamic loss measurements and flow visualizations have been conducted for a squealer tip with different winglets. The present results for seven winglets indicate that winglet coverage along the pressure side has a negative effect in the loss reduction, whereas winglet coverage along the suction side has a positive effect.
Yong Cheol Seo, Sang Woo Lee
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Flow Investigations in the Tip Gap of Rotor Blade Tips With Squealer Cavity

Volume 6A: Turbomachinery, 2013
The tip leakage flow in turbines is considered to be responsible/or significant machine losses. An efficient reduction of these losses by e. g. squealer cavities at rotor blade tips requires a detailed physical and quantitative understanding of the tip leakage flow.
Andreas Fischer, Jörg König, Jürgen Czarske, Clemens Rakenius, Gregor Schmid, Heinz-Peter Schiffer   +5 more
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Tip leakage aerodynamics over stepped squealer tips in a turbine cascade

Experimental Thermal and Fluid Science, 2011
Abstract Tip gap flow physics and aerodynamic loss generations for two stepped squealer tips of a “Higher Pressure-side rim and Lower Suction-side rim” (HPLS) tip and a “Lower Pressure-side rim and Higher Suction-side rim” (LPHS) tip have been investigated in a turbine cascade.
Seong Eun Lee, Sang Woo Lee, Ho Sang Kwak   +2 more
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Influence of tip clearance and cavity depth on heat transfer in a cutback squealer tip

Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering, 2020
Numerical simulations are conducted to present the aerothermal performance of a turbine blade tip with cutback squealer rim. Two different tip clearance heights (0.5%, 1.0% of the blade span) and three different cavity depths (2.0%, 3.0%, and 6.0% of the blade span) are investigated. The results show that a high heat transfer coefficient (HTC) strip on
Weijie Wang, Shaopeng Lu, Hongmei Jiang, Qiusheng Deng, Jinfang Teng, Wensheng Yu   +5 more
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Aerothermal Performance of Axially Varying Winglet-Squealer Blade Tips

Volume 10B: Turbomachinery — Axial Flow Turbine Aerodynamics; Deposition, Erosion, Fouling, and Icing; Radial Turbomachinery Aerodynamics, 2022
Abstract High-pressure turbine blades are usually susceptible to secondary flow losses due to fluid flow between the casing and the blade tip. In this study, we have evaluated the performance of several blade tip designs for different combinations of winglets and squealer geometries towards mitigating tip leakage losses.
Anmol Garg, Nagabhushana Rao Vadlamani, Balaji Srinivasan   +2 more
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Effects of Impeller Squealer Tip on Centrifugal Compressor Performance

Journal of Engineering for Gas Turbines and Power, 2016
This paper summarizes the main results sorted out from a design of experiment (DoE) based on a validated computational fluid dynamics (CFD). Several tip recessed geometries applied to an unshrouded impeller were considered in conjunction with two tip clearance levels.
Riccardo Da Soghe, Cosimo Bianchini, Lorenzo Toni, Dante Tommaso Rubino   +3 more
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Effects of Tip Gap Film Injection From Plain and Squealer Blade Tips

Volume 3: Turbo Expo 2004, 2004
The present study investigates the effect of orthogonal tip gap film injection from a plain and squealer tip of a HPT first stage rotor blade. The pressure ratio (inlet total pressure to exit static pressure) for the cascade used was 1.2, and the experiments were run in a blow-down test rig with a four-blade stationary linear cascade.
Hasan Nasir, Srinath V. Ekkad, Ronald S. Bunker, Chander Prakash   +3 more
openaire   +1 more source