RT Journal Article
ID 78b328270e0a518c
A1 Wright, Lesley M.
A1 Han, Je-Chin
T1 HEAT TRANSFER ENHANCEMENT FOR TURBINE BLADE INTERNAL COOLING
JF Journal of Enhanced Heat Transfer
JO JEH(T)
YR 2014
FD 2015-09-30
VO 21
IS 2-3
SP 111
OP 140
K1 single-phase convection
K1 rough surfaces
K1 swirl-flow devices
K1 jet impingement
K1 compound enhancement techniques
AB Gas turbines are used extensively for aircraft propulsion, land-based power generation, and industrial
applications. The turbine inlet temperatures are far above the permissible metal temperatures. Therefore,
there is a need to cool the blades for safe operation. Modern developments in turbine cooling
technology play a critical role in increasing the thermal efficiency and power output of advanced gas
turbine designs. Turbine blades and vanes are cooled internally and externally. This paper focuses on
heat transfer augmentation of turbine blade internal cooling. Internal cooling is typically achieved
by passing the cooling air through rib-enhanced serpentine passages inside the blades. Impinging
jets, pin-fins, and dimples are also used for enhancing internal cooling heat transfer. In the past 10
years, there has been considerable progress in turbine blade internal cooling research and this paper
is focused on reviewing selected publications to reflect recent developments in this area. In particular,
this paper focuses on the newly developed design concepts as well as the combination of existing
cooling techniques for turbine airfoil internal heat transfer augmentation. Rotation effects on the turbine
blade leading-edge, triangular-shaped channel, mid-chord multi-pass channel, and trailing-edge,
wedge-shaped channel with coolant ejection are also considered.
PB Begell House
LK https://www.dl.begellhouse.com/journals/4c8f5faa331b09ea,11584a19582df1ec,78b328270e0a518c.html