| 摘要 |
FIELD: mechanical engineering; turbopump units of liquid propellant rocket engine. SUBSTANCE: rotor has shaft 1, turbine working wheel 2, working wheels 3,4 of oxidizer and fuel pumps, respectively, and automatic relief device. Oxidizer pump support consists of unit of twin single-row ball bearings 7,8, with resilient device 9 and support ring 16 installed between outer races of bearings. resilient device is made in form of ring resilient member connected with base resting on outer race of one of ball bearing. Resilient member resting on outer race of second ball bearing is installed with axial clearance relative to support ring. Value of clearance is equal to axial clearance of ball bearing. Minimum value of clearance in automatic relief device exceeds value of clearance between end faces of base of resilient member and support ring. Ring groove 20 is made in rotor housing, and channels 19 are made in support ring to let in cooling liquid. EFFECT: enhanced operation of rotor under any operation conditions of engine, including starting, improved reliability, increased service life of supports. 4 cl, 3 dwg- |
