The aero-propulsion sector is continually seeking to reduce fuel consumption, costs and environmental pollution. Gas turbine engines form a significant part of this sector and their development is a key approach to meet fuel reduction targets. One approach to enhance these engines is to increase the temperature at the inlet of the High Pressure Turbine (HPT), however, this exposes the HPT blades to significant thermal load and damages. The blade tip is exposed to much higher heat load, therefore it is recognised as a critical area for design improvement within the HPT.
The longer the blade is in service the more eroded its edges become, this is known as the in-service burnout effect. This effect changes the flow characteristics over the blade tip and increases losses due to the tip flows, which contributes to the 30% of the total loss in the turbine stage. Therefore, it is significantly important to study the tip flows using realistic models i.e. tips exposed to in-service burnout, there is a very large knowledge gap about this in the literature. This investigation aims to perform an optimisation aerothermal study of the in-service burnout effect on a typical high pressure turbine blade of gas turbine engine.
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