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Effect of V-shaped Ribs on Internal Cooling of Gas Turbine Blades
- Source :
- Journal of Engineering and Technological Sciences, Vol 49, Iss 4 (2017)
- Publication Year :
- 2017
- Publisher :
- ITB Journal Publisher, 2017.
-
Abstract
- Thermal efficiency and power output of gas turbines increase with increasing turbine rotor inlet temperature. The rotor inlet temperatures in most gas turbines are far higher than the melting point of the blade material. Hence the turbine blades need to be cooled. In this work, simulations were carried out with the leading edge of gas turbine blade being internally cooled by coolant passages with V-shaped ribs at angles of 30°, 45° or 60° and at three aspect ratios (1:1, 1:2 and 2:3). The trailing edge of the blade was cooled by cylindrical and triangular pin-fin perforations in staggered and inline arrangements. Numerical analyses were carried out for each configuration of the cooling passages. The best cooling passages for leading edge and trailing edge were deduced by comparing the results of these analyses. It was found that using V-shaped ribs and fins induces a swirling flow, which in turn increases the velocity gradient and hence produces an improvement in heat transfer. The results show that under real time flow conditions, the application of V-shaped ribs and pin-fin perforations is a very promising technique for improving blade life.
- Subjects :
- Thermal efficiency
Leading edge
Materials science
internal cooling
Turbine blade
trailing edge
02 engineering and technology
law.invention
030507 speech-language pathology & audiology
03 medical and health sciences
0203 mechanical engineering
law
ribs
Trailing edge
Velocity gradient
Rotor (electric)
General Engineering
turbine blade cooling
Mechanics
Engineering (General). Civil engineering (General)
Coolant
020303 mechanical engineering & transports
Heat transfer
TA1-2040
0305 other medical science
Subjects
Details
- Language :
- English
- ISSN :
- 23385502 and 23375779
- Volume :
- 49
- Issue :
- 4
- Database :
- OpenAIRE
- Journal :
- Journal of Engineering and Technological Sciences
- Accession number :
- edsair.doi.dedup.....54f3536a5b5ab9eaa7d0e125a7c1999d