Skip to main navigation
Skip to search
Skip to main content
Penn State Home
Help & FAQ
Home
Researchers
Research output
Research units
Equipment
Grants & Projects
Prizes
Activities
Search by expertise, name or affiliation
Experimental heat transfer investigation around the film-cooled leading edge of a high-pressure gas turbine rotor blade
Cengiz Camci, T. Arts
Aerospace Engineering
Research output
:
Contribution to journal
›
Article
›
peer-review
53
Scopus citations
Overview
Fingerprint
Fingerprint
Dive into the research topics of 'Experimental heat transfer investigation around the film-cooled leading edge of a high-pressure gas turbine rotor blade'. Together they form a unique fingerprint.
Sort by
Weight
Alphabetically
Keyphrases
Free Stream
100%
High-pressure Gas
100%
Gas Turbine Rotor Blade
100%
Temperature Ratio
100%
Experimental Heat Transfer
100%
High Pressure
50%
Incidence Angle
50%
Coolant
50%
Heat Transfer
50%
Reynolds number
50%
Mach number
50%
Film Cooling
50%
Calculation Method
50%
Heat Transfer Enhancement
50%
Platinum Thin Film
50%
Weight Ratio
50%
Aero-engine
50%
Wall Temperature
50%
Thin Film Gauge
50%
Angle Variation
50%
Isentropic Compression
50%
Cooled Gas Turbine
50%
Pressure Film
50%
Stationary Frame
50%
Compression Tube
50%
Engineering
Leading Edge
100%
Gas Turbine
100%
Rotor Blade
100%
Pressure Gas
100%
Thin Films
50%
Mach Number
50%
Incidence Angle
50%
Heat Transfer Data
50%
Aeroengine
50%
Cooled Gas
50%
Mass Weight
50%
Isentropic Compression
50%