ライブラリ登録: Guest
ICHMT DL ホーム 今年 アーカイブ 執行委員会 熱・物質移動国際センター

EFFECT OF THE GEOMETRY OF FILM COOLING HOLES ON HEAT TRANSFER COEFFICIENT IN CONDITION OF VARIOUS MAINSTREAM PRESSURE GRADIENTS

DOI: 10.1615/ICHMT.2009.HeatTransfGasTurbSyst.350
16 pages

Cun-liang Liu
School of Engine and Energy, Northwestern Polytechnical University, Xi’an 710072, China

Xiao-wei Zhang
School of Engine and Energy, North Western Polytechnical University, Xi’an 710072, P. R. China

Hui-ren Zhu
School of Engine and Energy, Northwestern Polytechnical University, Xi’an 710072, China

Guang-Chao Li
School of Engine and Energy, Northwestern Polytechnical University, Xi’an 710072, China

Du-chun Xu
School of Engine and Energy, Northwestern Polytechnical University, Xi’an 710072, China

要約

According to the pressure distribution on the blade surface, three various test sections of the flat plate have been made produced the zero, favorable or adverse mainstream pressure gradients, respectively. A new type film cooling hole has been presented that both the entrance and the exit are expanded, called the bidirectional expanded holes. The effect of the geometry of film cooling holes on the nominal heat transfer coefficient, h/h0, has been investigated experimentally under three various mainstream pressure gradients utilizing a conventional temperature measurement technique named metal film & thermocouple. Result showed that plane angles, α, and radial angles, β, are the dominant influencing factors of noticeable effects on h/h0, however the pitch between the adjacent holes, p, is secondary factor. A trend is seen mostly that h/h0 for various mainstream pressure gradients are decreased with the distant from the exit of the film hole, x/d, increasing; in the vicinity of the hole the drastically altered flow-field has a strong impact and can result in a substantial augmentation of the heat transfer.

ICHMT Digital Library

Bow shocks on a jet-like solid body shape. Thermal Sciences 2004, 2004. Pulsed, supersonic fuel jets - their characteristics and potential for improved diesel engine injection. PULSED, SUPERSONIC FUEL JETS - THEIR CHARACTERISTICS AND POTENTIAL FOR IMPROVED DIESEL ENGINE INJECTION
View of engine compartment components (left). Plots of temperature distributions in centreplane, forward of engine (right). CHT-04 - Advances in Computational Heat Transfer III, 2004. Devel... DEVELOPMENT AND CURRENT STATUS OF INDUSTRIAL THERMOFLUIDS CFD ANALYSIS
Pratt & Whitney's F-135 Joint Strike Fighter Engine under test in Florida is a 3600F class jet engine. TURBINE-09, 2009. Turbine airfoil leading edge stagnation aerodynamics and heat transfe... TURBINE AIRFOIL LEADING EDGE STAGNATION AERODYNAMICS AND HEAT TRANSFER - A REVIEW
Refractive index reconstructed field. (a) Second iteration. (b) Fourth iteration. Radiative Transfer - VI, 2010. Theoretical development for refractive index reconstruction from a radiative ... THEORETICAL DEVELOPMENT FOR REFRACTIVE INDEX RECONSTRUCTION FROM A RADIATIVE TRANSFER EQUATION-BASED ALGORITHM
Two inclusion test, four collimated sources. Radiative Transfer - VI, 2010. New developments in frequency domain optical tomography. Part II. Application with a L-BFGS associated to an inexa... NEW DEVELOPMENTS IN FREQUENCY DOMAIN OPTICAL TOMOGRAPHY. PART II. APPLICATION WITH A L-BFGS ASSOCIATED TO AN INEXACT LINE SEARCH