Results 211 to 220 of about 12,692 (263)
Some of the next articles are maybe not open access.
Effects of mainstream attack angles on film-cooling effectiveness of double-jet film-cooling
International Journal of Thermal Sciences, 2020Abstract Effects of mainstream attack angles on double-jet film-cooling (DJFC) effectiveness under different blowing ratios (M = 0.5, 1.0, 1.5, 2.0) are investigated experimentally on a flat plate, and the flow field is obtained by simulation. The attack angles (i) are −30°, −20°, −10°, 0°, 10°, 20°, 30° respectively.
Gongnan Xie, Jiaxu Yao
exaly +2 more sources
Directional Effects of Effusion Cooling on the Cooling Film Effectiveness
AIAA Journal, 2021Effusion cooling in gas turbine combustors is complicated by swirling flows for anchoring flame, whereas miniature effusion cooling jets are highly directional.
Leo C. Paitich +5 more
openaire +1 more source
Aircraft Engineering and Aerospace Technology, 2021
Purpose This paper aims to investigate the film cooling effectiveness (FCE) and mixing flow characteristics of the flat surface ramp model integrated with a compound angled film cooling jet. Design/methodology/approach Three-dimensional numerical simulation is performed on a flat surface ramp model with Reynolds Averaged Navier-Stokes approach using
Krishna Anand Vasu Devan Nair Girija Kumari +1 more
openaire +1 more source
Purpose This paper aims to investigate the film cooling effectiveness (FCE) and mixing flow characteristics of the flat surface ramp model integrated with a compound angled film cooling jet. Design/methodology/approach Three-dimensional numerical simulation is performed on a flat surface ramp model with Reynolds Averaged Navier-Stokes approach using
Krishna Anand Vasu Devan Nair Girija Kumari +1 more
openaire +1 more source
Effects of Curvature on the Film Cooling Effectiveness of Double-Jet Film Cooling
Volume 5B: Heat Transfer, 2014The effect of curvature on the film cooling characteristics of Double-Jet Film Cooling (DJFC) was numerically investigated using three-dimensional Reynolds-Averaged Navier-Stokes (RANS). The low-Reynolds number shear stress transport (SST) model was employed as the turbulence closure model.
Gaoliang Liao +3 more
openaire +1 more source
Transactions of the Canadian Society for Mechanical Engineering, 1991
Measurements of the flow field and film cooling effectiveness downstream of a two-dimensional inclined slot were made. A two-dimensional numerical model solving the transport equations in curvilinear orthogonal coordinate system was developed to simulate film cooling process. Comparisons were made between numerical and experimental results.
I. Gartshore, M. Salcudean, P. Matys
openaire +1 more source
Measurements of the flow field and film cooling effectiveness downstream of a two-dimensional inclined slot were made. A two-dimensional numerical model solving the transport equations in curvilinear orthogonal coordinate system was developed to simulate film cooling process. Comparisons were made between numerical and experimental results.
I. Gartshore, M. Salcudean, P. Matys
openaire +1 more source
Predictions of Adiabatic Film Cooling Effectiveness for Effusion Film Cooling
Volume 4: Turbo Expo 2007, Parts A and B, 2007This paper presents computational predictions of adiabatic film cooling effectiveness for effusion cooling systems with 90° and 30° holes. Predictions are performed for a range of coolant injection mass flow rates per unit surface area, G, of 0.1kg/sm2 - 1.6 kg/sm2 for 90° holes with constant pitch-to-diameter ratio of X/D = 11 and 10 rows of holes and
Nadiahnor Md. Yusop +5 more
openaire +1 more source
Exploitation of Acoustic Effects in Film Cooling
Journal of Engineering for Gas Turbines and Power, 2014There have been numerous studies of the behavior of shaped film cooling holes for turbine applications. It is known that the introduction of coolant is an unsteady process, and a handful of studies have described and characterized the unsteadiness. To the best of our knowledge, there are no studies in which unsteady acoustic effects have been actively ...
Collins, M, Povey, T
openaire +2 more sources
Cooling Effectiveness on Film Cooled Turbine Blades
Heat Transfer: Volume 5 — Computational, Aerospace and Environmental Heat Transfer, 2001Abstract This paper presents experiments on the cooling effectiveness obtained for two different injection locations on the suction side of a turbine blade at transonic flow conditions. Previous results of a computational analysis and flow visualization indicated that a separation bubble is present on the suction side at a location x/L =
M. Derrar, J. Nagler, W. W. Koschel
openaire +1 more source
The effect of unsteadiness on film cooling effectiveness
33rd Aerospace Sciences Meeting and Exhibit, 1995Abstract : A unique feature of turbine rotor blade film cooling is the main flow unsteadiness caused by the upstream stator vanes. The combined effect of the vane inviscid flow field and the trailing edge wake results in a rapidly changing external pressure at the film cooled blade surface.
Jeffrey Bons +4 more
openaire +1 more source