Results 21 to 30 of about 402 (231)
Cutback squealer tip trailing edge cooling performance
International Journal of Heat and Mass Transfer, 2020 Abstract The trailing edge tip region has always been the most vulnerable part of high-pressure turbine blade. The requirements for both aerodynamic efficiency and cooling effectiveness make it a challenging task in turbine blade cooling design. A closely combined experimental and CFD effort, specifically focusing on trailing edge region, is reported
S. Lu, H. Ma, Q. Zhang, J. Teng
openaire +2 more sources
Impact of Cooling Injection on the Transonic Over-Tip Leakage Flow and Squealer Aerothermal Design Optimization [PDF]
, 2015 In the present work, the effect of coolant injection on the over-tip-leakage (OTL) flow and squealer designs has been investigated in a transonic flow regime.
He, L., Zhang, Q., Liu, Y., Wang, Z.
core +1 more source
Desensitization of Tip Clearance Effects in Axial Flow Turbines
Journal of Fluid Science and Technology, 2010 The present study aims to control the leakage flow and total pressure loss in high pressure turbines. A new tip shape is proposed. It is based on the triple squealer shape by adopting a new middle squealer, along the camber line, whose first and last ...
Mohamed EL-GHANDOUR +2 more
doaj +1 more source
MachinesBlade tip leakage flow in gas turbines is associated with aerodynamic loss and local heat transfer variation in the tip region. In this study, the flow structure, total pressure loss coefficient, heat transfer coefficient (HTC), and film cooling ...
Dae Hyun Kim, Jin Taek Chung
doaj +1 more source
AerospaceThis study deals with the effectiveness of casing-injection for a few squealer tip designs in a turbine stage to mitigate tip leakage penalties. Seventy-two Unsteady Reynolds-Averaged Navier–Stokes (URANS) simulations were conducted.
Nasser Can Kasımbeyoğlu +2 more
doaj +1 more source
International Journal of Turbomachinery, Propulsion and Power, 2019 The present research focused on the analysis of the leakage flows developing from advanced blade tip geometries. The aerodynamic field of a contoured blade tip and of a high-performance rimmed blade were investigated against a baseline squealer rotor ...
Bogdan C. Cernat, Sergio Lavagnoli
doaj +1 more source
Dominant flow structure in the squealer tip gap and its impact on turbine aerodynamic performance
, 2017 Tip leakage loss reduction is important for improving the turbine aerodynamic performance. In this paper, the flow field of a transonic high pressure turbine stage with a squealer tip is numerically investigated. The physical mechanism of flow structures
Shao, Fei, +14 more
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Calpain small subunit homodimerization is robust and calcium‐independent
FEBS Letters, EarlyView.Calpains dimerize via penta‐EF‐hand (PEF) domains. Using single‐molecule force spectroscopy, we measured the strength and kinetics of PEF–PEF homodimer binding. The interaction is robust, shows a transient conformational step before dissociation, and remains largely insensitive to Ca2+.
Nesha May O. Andoy +4 more
wiley +1 more source
High-Pressure Turbine Aerodynamic Enhancement Using Rotor Tip Desensitization Technique
EnergiesTurbines experience pressure losses from various sources, one of which is the tip leakage flow in the rotor blades. This is one of the main factors responsible for the decrease in turbine efficiency. This leakage is caused by pressure differences between
Luciano Porto Bontempo +5 more
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Turbine Blade Tip External Cooling Technologies
Aerospace, 2018 This article provides an overview of gas turbine blade tip external cooling technologies. It is not the intention to comprehensively review all the publications from past to present.
Song Xue, Wing F. Ng
doaj +1 more source