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Start Transinet Analysis of Turbopump-Fed LOX/LH2 Rocket Engine (LE-5).

N8619371

Publication Date	1985
Personal Author	Kanmuri, A.; Wakamatsu, Y.; Shimura, T.; Toki, K.; Torii, Y.
Page Count	35
Abstract	The first Japanese LOX/LH2 rocket engine (LE-5) employs a turbopump-fed gas generator cycle system. The LE-5 engine starts up in such an unique method that the power of the turbopump system is at first built up by a coolant bleed cycle followed by a gas generator cycle. A computer program for the start transient simulation has been developed and it has been utilized for analysing start-up characteristics of the LE-5 engine. The outline of the computer program and the analytical results are discussed here. The results of the analysis have been effectively used for the setting of the firing test condition and for the termination of the engine start sequence in each phases of the development. The results of the simulation are also compared with the experimental results.
Keywords	Cryogenic rocket propellants Liquid hydrogen Liquid oxygen Liquid propellant rocket engines Turbine pumps Computer programs Computerized simulation Gas generators Test firing Foreign technology
Source Agency	NASA Foreign Exchange Program
NTIS Subject Category	81G - Rocket Engines & Motors
Corporate Authors	National Aerospace Lab., Tokyo (Japan).; National Aeronautics and Space Administration, Washington, DC.
Supplemental Notes	In Japanese; English Summary.
Document Type	Technical Report
NTIS Issue Number	198613

Start Transinet Analysis of Turbopump-Fed LOX/LH2 Rocket Engine (LE-5).

Start Transinet Analysis of Turbopump-Fed LOX/LH2 Rocket Engine (LE-5).
N8619371

Publication Date	1985
Personal Author	Kanmuri, A.; Wakamatsu, Y.; Shimura, T.; Toki, K.; Torii, Y.
Page Count	35
Abstract	The first Japanese LOX/LH2 rocket engine (LE-5) employs a turbopump-fed gas generator cycle system. The LE-5 engine starts up in such an unique method that the power of the turbopump system is at first built up by a coolant bleed cycle followed by a gas generator cycle. A computer program for the start transient simulation has been developed and it has been utilized for analysing start-up characteristics of the LE-5 engine. The outline of the computer program and the analytical results are discussed here. The results of the analysis have been effectively used for the setting of the firing test condition and for the termination of the engine start sequence in each phases of the development. The results of the simulation are also compared with the experimental results.
Keywords	Cryogenic rocket propellants Liquid hydrogen Liquid oxygen Liquid propellant rocket engines Turbine pumps Computer programs Computerized simulation Gas generators Test firing Foreign technology
Source Agency	NASA Foreign Exchange Program
NTIS Subject Category	81G - Rocket Engines & Motors
Corporate Authors	National Aerospace Lab., Tokyo (Japan).; National Aeronautics and Space Administration, Washington, DC.
Supplemental Notes	In Japanese; English Summary.
Document Type	Technical Report
NTIS Issue Number	198613