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
Dusting Hole Film Cooling Heat Transfer on a Transonic Turbine Blade Tip
International Journal of Rotating Machinery, 2022 Investigated is a transonic turbine blade tip with a squealer rim and a squealer recess, with a single dusting film cooling hole contained within the leading edge region of the squealer recess.
Ward Manneschmidt +6 more
doaj +1 more source
Blade Tip Leakage Flow and Heat Transfer with Pressure-Side Winglet
International Journal of Rotating Machinery, 2006 A numerical study has been conducted to explore the effect of a pressure-side winglet on the flow and heat transfer over a blade tip. Calculations are performed for both a flat tip and a squealer tip.
A. K. Saha +3 more
doaj +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., Liu, Y., Wang, Z., Zhang, Q.
core +1 more source
Computational Investigation of Novel Tip Leakage Mitigation Methods for High Pressure Turbine Blades [PDF]
, 2014 This paper presents preliminary findings on a possible approach to reducing tip leakage losses. In this paper a computational study was conducted on the EEE (Energy Efficient Engine) HPT (High Pressure Turbine) rotor tip geometry using the commercial ...
Canelli C. +11 more
core +5 more sources
Influence of grooved rib tip structure on tip loss and heat transfer in a gas turbine blade
Frontiers in Energy Research, 2022 This study focuses on the effects of three groove tip structures (full rib groove tip, partial rib tip on the suction side, and partial rib tip on the pressure side) on tip leakage flow, aerodynamic characteristics of a cascade, and heat transfer in a ...
Zhiqi Kong, Tianyi Zhang, Wei Du
doaj +1 more source
Effect of film-hole configuration on film-cooling effectiveness of squealer tips
Journal of Thermal Science and Technology, 2017 Three-dimensional numerical simulations are carried out to investigate the effects of film-hole arrangement and blowing ratio on the squealer tip leakage flow field and tip film-cooling performance.
Fengna CHENG +3 more
doaj +1 more source
An experimental and computational study of tip clearance effects on a transonic turbine stage [PDF]
, 2009 This paper describes an experimental and computational investigation into the influence of tip clearance on the blade tip heat load of a high-pressure (HP) turbine stage.
Ainsworth, Roger W +2 more
core +3 more sources
Aerothermal Performance of Shroudless Turbine Blade Tips with Relative Casing Movement Effects [PDF]
, 2015 Qualitatively different heat transfer characteristics between a transonic blade tip and a subsonic one have recently been discovered. High-resolution experimental data can be acquired for blade-tip heat transfer research using a high-speed linear cascade.
A. S. Virdi +10 more
core +1 more source
Performance of Partial and Cavity Type Squealer Tip of a HP Turbine Blade in a Linear Cascade
International Journal of Aerospace Engineering, 2018 Three-dimensional highly complex flow structure in tip gap between blade tip and casing leads to inefficient turbine performance due to aerothermal loss.
Levent Kavurmacioglu +3 more
doaj +1 more source