advances in turbine airfoil cooling designs enabled by
TRANSCRIPT
Advances in Turbine Airfoil Cooling Designs Enabled by Improvements in
Core Manufacture & Casting Capability
TURBINE BLADE COOLING METHODSTURBINE BLADE COOLING METHODS
4
HOTGAS
Cooling Air(a) Convection Cooling (b) Impingement Cooling
(c) Film Cooling (d) Full-coverage Film Cooling
(e) Transpiration Cooling
ADVANCES IN TURBINE BLADE COOLING
4000
3500
3000
2500
2000
15001960 1970 1980 1990 2000 2010
Single Piece, Single Cast,Single Crystal Transpiration Cooling
Advanced FilmCooling
Film Cooling
Impingement Cooling
Radial HoleCoolingSolid
Uncooled
YEAR OF APPLICATION
TUR
BIN
E IN
LET
TEM
PER
ATU
RE
(ÞF)
After Frasier US Patent 5295530
After Philip.Haley-RR-2000-Gas Turbine of the Future
Airfoil Cooling Technology Trends
After Philip.Haley-RR-2000-Gas Turbine of the Future
GE Aero Serpentine Design Circa 1971US patent 3,628,885
Note impingement cooling sheet metal insert at Leading Edge
IGT Vane Impingement Cooling DesignUS Patent 04297077
Note trailing edgepin fin design Note sheet metal
Inserts for impingementCooling in circuits 1 & 2
ADVANCES IN TURBINE BLADE COOLINGRolls Royce Cast Cool Quasi-Transpiration Cooling
RR-Patent 5924483
IGT Bucket Radial Cooling DesignGE 6B 1st Bucket STEM Drilled Holes
GE GER-4217A
Cooling circuitsproduced by STEMdrilling radial holesin solid airfoil
IGT Blade Cooling Radial STEM Drilled v Cored Cast Serpentine Designs
US Patent 6966756
Cooling circuitsproduced by STEMdrilling radial holes
Cooling circuitsproduced by complexceramic core duringcasting process
GE-Aero Multiwall-Cooling Circuit DesignUS Patent 7296973
Note details of crossover holesbetween some circuits increasing the
complexity of the ceramic core
ADVANCES IN TURBINE BLADE COOLINGIGT Turbines – Siemens Adv. Multiwall
US Patent Appl. Pub # 2006-0222495