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In_service deterioration can lead to undesired shape variations on high-pressure turbine rotor blades. This can have a significant impact on efficiency, power generation and component life. Loss of power production from the high_pressure turbine rotor causes engine over_throttling to compensate for the lower performance. This will in turn worsen the operating conditions and ultimately reduce the life of the component. The aim of this study is to provide a high_fidelity flow simulation of in_serviced shrouded High_Pressure Turbine (HPT) blades of a modern Jet Engine. Shape variations effects on the aerodynamic performance of several shrouded HPT blades with different number of in_service hours have been investigated. In order to establish a digital model of the shape variation, a novel reverse engineering procedure is carried out, to come up with a parametrized definition of each blade's variations from nominal including any observable damage. The investigation is conducted by means of an in_house, full 3D steady_state RANS simulation of the flow around a series of damaged rotor blade geometries, which are obtained through high_resolution GOM scans. The analysis shows that the aerodynamic performance of the HPT rotor blades under investigation is primarily sensitive to shroud damage, which is found to account for efficiency losses often greater than 3%, and for more than 80% of the total performance loss. A secondary role on efficiency is found to be played by the blade shape deviation. A highly linear correlation is found between HPT stage efficiency and a combination of shroud damage parameters.

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