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Article

Effects of Leading-Edge Modification in Damaged Rotor Blades on Aerodynamic Characteristics of High-Pressure Gas Turbine

by 1 and 1,2,*
1
Department of Mechanical Engineering, Chung-Ang University, Seoul 06911, Korea
2
Department of Intelligent Energy and Industry, Chung-Ang University, Seoul 06911, Korea
*
Author to whom correspondence should be addressed.
Mathematics 2020, 8(12), 2191; https://doi.org/10.3390/math8122191
Received: 9 November 2020 / Revised: 3 December 2020 / Accepted: 5 December 2020 / Published: 9 December 2020
(This article belongs to the Special Issue Computational Fluid Dynamics 2020)
The flow and heat-transfer attributes of gas turbines significantly affect the output power and overall efficiency of combined-cycle power plants. However, the high-temperature and high-pressure environment can damage the turbine blade surface, potentially resulting in failure of the power plant. Because of the elevated cost of replacing turbine blades, damaged blades are usually repaired through modification of their profile around the damage location. This study compared the effects of modifying various damage locations along the leading edge of a rotor blade on the performance of the gas turbine. We simulated five rotor blades—an undamaged blade (reference) and blades damaged on the pressure and suction sides at the top and middle. The Reynolds-averaged Navier–Stokes equation was used to investigate the compressible flow in a GE-E3 gas turbine. The results showed that the temperatures of the blade and vane surfaces with damages at the middle increased by about 0.8% and 1.2%, respectively. This causes a sudden increase in the heat transfer and thermal stress on the blade and vane surfaces, especially around the damage location. Compared with the reference case, modifications to the top-damaged blades produced a slight increase in efficiency about 2.6%, while those to the middle-damaged blades reduced the efficiency by approximately 2.2%. View Full-Text
Keywords: gas turbine; damaged rotor blade; leading-edge modification; aerodynamic characteristics gas turbine; damaged rotor blade; leading-edge modification; aerodynamic characteristics
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MDPI and ACS Style

Mai, T.D.; Ryu, J. Effects of Leading-Edge Modification in Damaged Rotor Blades on Aerodynamic Characteristics of High-Pressure Gas Turbine. Mathematics 2020, 8, 2191. https://doi.org/10.3390/math8122191

AMA Style

Mai TD, Ryu J. Effects of Leading-Edge Modification in Damaged Rotor Blades on Aerodynamic Characteristics of High-Pressure Gas Turbine. Mathematics. 2020; 8(12):2191. https://doi.org/10.3390/math8122191

Chicago/Turabian Style

Mai, Thanh Dam, and Jaiyoung Ryu. 2020. "Effects of Leading-Edge Modification in Damaged Rotor Blades on Aerodynamic Characteristics of High-Pressure Gas Turbine" Mathematics 8, no. 12: 2191. https://doi.org/10.3390/math8122191

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