Benchmark testing of an enhanced operability LO2/LH2 RD-0120 engine

Rachuk, V. S.; Shostak, Arthur B.; Dmitrenko, A.; Goncharov, G. M.; Hernández, Ricardo Marco; Starle, R.; Hulka, James R.

doi:10.2514/6.1996-2609

Cited by 5 publications

(2 citation statements)

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“…The reusability and operability of the RD-O120 engine were examined in a recent test program. 32 A schematic for the RD-O120 engine is shown in Fig. 29, and all of the operating parameters are listed.…”

Section: B Rd-o120mentioning

confidence: 99%

Cycles for Earth-to-Orbit Propulsion

Manski¹,

Goertz²,

Sa-oslash³

et al. 1998

Journal of Propulsion and Power

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The reduction of Earth-to-orbit launch costs in conjunction with an increase in launcher reliability and operational ef ciency are the key demands on future space transportation systems. Results of various system analyses indicate that these demands can be met with future single-stage-to-orbit (SSTO) vehicles using advanced technologies for both structure and propulsion systems. This paper will provide a classi cation and description of all turbopump feed liquid rocket engine cycles, followed by a combined vehicle/propulsion analysis of the design parameters for the propulsion systems and their associated thermodynamic cycles for the launch of future SSTO vehicles. Existing and projected rocket engine cycles capable of SSTO missions will be presented.

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Section: B Rd-o120mentioning

confidence: 99%

Cycles for Earth-to-Orbit Propulsion

Manski¹,

Goertz²,

Sa-oslash³

et al. 1998

Journal of Propulsion and Power

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“…Throttling has been investigated and several engines were tested in deep and shallow throttled conditions. [1][2][3][4][5][6][7][8][9][10][11][12][13][14] Throttling is also necessary for the rocket-based-combined-cycle engine (RBCC) to change its operation to the ramjet mode. 15) In the rocket engine, thrust is proportional to the combustion chamber pressure.…”

Section: Introductionmentioning

confidence: 99%

Conceptual Study of Throttled Operation of Rocket Engine Turbopump

Kanda

2013

Trans. Japan Soc. Aero. S Sci.

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Throttled operation of turbopumps of liquid rocket engines is studied analytically. Two types of pressure drops in the propellant injector are examined, that is, the drop of gas injection and that of liquid injection. Circulation is examined in relation to throttling to operate the pump in the vicinity of the design condition. An enthalpy increase at the pump entrance is derived analytically in the circulation system. With the derived analytical relationships, throttled operating conditions are examined for imaginary LH 2 and LOX turbopumps with a LH 2 /LOX property calculation code. The circulation causes gasification at the entrance of the high-pressure LH 2 pump. This does not occur in the mid-pressure LH 2 pump or the LOX pump. In the liquid propellant injection system, the unstable region becomes narrower than in the gas propellant injection. The ratio of the turbine flow rate to the pump flow rate decreases in line with throttling. Throttling does not degrade the engine specific impulse from the viewpoint of the turbine bleed ratio.

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