Sealing structure of rocket engine turbine pump

• Main Authors: LI LINMIN, LIN YANPI, LI XIAOJUN, ZHU ZUCHAO
• Format: Patent
• Language: Chinese; English
• Published: 10.12.2021
• Subjects: BLASTING; HEATING; LIGHTING; MECHANICAL ENGINEERING; NON-POSITIVE DISPLACEMENT PUMPS; POSITIVE DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS; WEAPONS

The invention discloses a sealing structure of a rocket engine turbine pump. The sealing structure comprises a centrifugal impeller (4), wherein the centrifugal impeller comprises a rear disc (41), a front disc and a plurality of blades; and a sealing pair is formed between a first sealing ring and a second sealing ring. The sealing structure is characterized in that a plurality of auxiliary blades (43 and 44) are arranged on the outer side of the rear disc (41) and located at the radial inner end of the first sealing ring (42); the plurality of auxiliary blades are evenly distributed in the circumferential direction; a backflow space is formed between the plurality of auxiliary blades and the first sealing ring in the radial direction; a plurality of backflow holes (45) are formed in the rear disc (41) and located at the radial inner end of the first sealing ring (42); and the backflow space is communicated with the backflow holes. According to the sealing structure, part of leakage flow leaked from the seal