抄録
At present, National Space Development Agency of Japan (NASDA) is moving ahead of the development tests of the cryogenic engine LE-5, and setting further about the development of the second-generation, high-performance rocket engine LE-7.
Combination of liquid oxygen (LOX) and liquid hydrogen (LH2) was chosen as propellants through the technological experiences of LE-5, to minimize the total vehicle weight for certain launching capacity into geostationary orbit.
The most critical point to realize this high-performance engine is in the high pressure level, especially the turbopump discharge pressure must be increased remarkably.
This paper concentrates on LE-7 LH2 turbopump and introduce followings.
1) Required performance and Restraints for LH2 turbopump
2) Description of design
3) Technical problems
