Turbine blade internal impingement cooling structure based on ultrasonic enhanced heat transfer

• Main Authors: WANG JIEFENG, LI JIANWU, LIU YUSONG, FU YANGCHUN, YAN BIAO, LI LIANG
• Format: Patent
• Language: Chinese; English
• Published: 23.07.2021
• Subjects: BLASTING; ENGINE PLANTS IN GENERAL; HEATING; LIGHTING; MACHINES OR ENGINES IN GENERAL; MECHANICAL ENGINEERING; NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES; STEAM ENGINES; WEAPONS

The invention discloses a turbine blade internal impingement cooling structure based on ultrasonic enhanced heat transfer. According to the turbine blade internal impingement cooling structure based on ultrasonic enhanced heat transfer, under the operation working condition of a gas turbine, cooling gas enters a cold air cavity from a blade root under certain pressure, the axis of the cold air cavity is perpendicular to the axis of a nozzle but not intersects with the axis of the nozzle in space, and the cooling gas is tangentially introduced into the nozzle to rotate rapidly and generate vortex. When the cooling gas is sprayed out from the minimum diameter position of a nozzle outlet, high-speed jet flow can be generated, and sound can be produced; when the vibration frequency of the jet flow is consistent with the frequency of a resonant cavity, strong ultrasonic waves are generated; and the boundary layer effect, the acoustic streaming effect and the cavitation effect during ultrasonic propagation can enha