Deposition of particulate pollutants on turbine vanes after being ingested into aircraft engines can lead to degradation of their thermomechanical performance under high temperature and high-velocity gas flow conditions. The high-pressure turbine guide vanes adjacent to the exit of the combustion chamber, experience the highest temperatures among all turbine components, making them more susceptible to severe deposition issues. The deposition problems on the vane surfaces become even more complex due to the influence of hot streaks originating from the combustion chamber. In this study, numerical simulations combined with user-defined functions were employed to investigate the migration and deposition characteristics of particles on the first-stage stator vane of a high-pressure turbine under actual operating conditions. A Gaussian temperature distribution was applied at the turbine inlet to simulate hot streaks, and variations in the hot streaks temperature ratio and their relative circumferential positions to the vane were considered. Results revealed significant temperature variations between adjacent vanes due to the presence of hot streaks. When the hot streaks were positioned directly in front of the vane leading edge, a large number of high-temperature particles impinged and deposited on the leading edge surfaces. As the hot streaks was aligned with the vane mid-passage, more high-temperature particles deposited on the mid-chord and trailing edge regions of the vane, as well as the leading edge of adjacent vanes. Increasing the hot streaks temperature ratio caused the high-temperature center of the hot streaks trail to concentrate towards the midspan position, reducing overall deposition levels on the vane surface. In contrast to a uniform inlet temperature case, the hot spot increased the deposition levels on two adjacent vanes and widened the gap of deposition efficiency between the vanes by up to 11.6%, thus intensifying the flow field non-uniformities towards downstream rotors.

The deposition of particulate pollutants on turbine vanes after being ingested into aircraft engines can lead to degradation of their thermomechanical performance under high temperature and high-speed gas flow conditions. The high-pressure turbine guide vanes adjacent to the exit of the combustion chamber, experience the highest temperatures among all turbine components, making them more susceptible to severe deposition issues. The deposition problem on the vane surfaces becomes even more complex due to the influence of hot streaks originating from the combustion chamber. In this study, numerical simulations combined with user-defined functions were employed to investigate the migration and deposition characteristics of particles on the first stage stator vane of the high-pressure turbine under real operating conditions. A Gaussian temperature distribution was applied at the turbine inlet to simulate hot streaks, and variations in the hot streaks temperature ratio and their relative circumferential positions to the vane were considered. The results revealed significant temperature variations between adjacent vanes due to the presence of hot streaks. When the hot streaks was positioned directly in front of the vane leading edge, a large number of high-temperature particles impinged and deposited on the leading edge. As the hot streaks was positioned at the center of the flow passage, more high-temperature particles deposited on the mid-chord and trailing edge regions of the vane, as well as the leading edge of adjacent vanes. Increasing the hot streaks temperature ratio caused the high-temperature center of the hot streaks trail to concentrate towards the midspan position, reduced overall deposition level on the vane surface, but it was still higher than that of the uniform inlet temperature of the guide vane.

TK14

国家自然科学基金（52276035）；航空发动机及燃气轮机基础科学中心项目（P2022-B-II-028-001）