Effects of damaged rotor blades on the aerodynamic behavior and heat-transfer characteristics of high-pressure gas turbines
- Authors
- Mai, T.D.; Ryu, J.
- Issue Date
- Mar-2021
- Publisher
- MDPI AG
- Keywords
- Aerodynamic characteristic; Compressible flow; Damaged rotor blade; Gas turbine; Heat-transfer coefficient
- Citation
- Mathematics, v.9, no.6
- Journal Title
- Mathematics
- Volume
- 9
- Number
- 6
- URI
- https://scholarworks.bwise.kr/cau/handle/2019.sw.cau/51779
- DOI
- 10.3390/math9060627
- ISSN
- 2227-7390
2227-7390
- Abstract
- Gas turbines are critical components of combined-cycle power plants because they influence the power output and overall efficiency. However, gas-turbine blades are susceptible to damage when operated under high-pressure, high-temperature conditions. This reduces gas-turbine performance and increases the probability of power-plant failure. This study compares the effects of rotor-blade damage at different locations on their aerodynamic behavior and heat-transfer properties. To this end, we considered five cases: a reference case involving a normal rotor blade and one case each of damage occurring on the pressure and suction sides of the blades’ near-tip and midspan sections. We used the Reynolds-averaged Navier-Stokes equation coupled with the k − ω SST γ turbulence model to solve the problem of high-speed, high-pressure compressible flow through the GE-E3 gas-turbine model. The results reveal that the rotor-blade damage increases the heat-transfer coefficients of the blade and vane surfaces by approximately 1% and 0.5%, respectively. This, in turn, increases their thermal stresses, especially near the rotor-blade tip and around damaged locations. The four damaged-blade cases reveal an increase in the aerodynamic force acting on the blade/vane surfaces. This increases the mechanical stress on and reduces the fatigue life of the blade/vane components. © 2021 by the authors. Licensee MDPI, Basel, Switzerland.
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