CECE: Expanding the Envelope of Deep Throttling in Liquid Oxygen/Liquid Hydrogen Rocket Engines For NASA Exploration Missions

Giuliano, V.; Leonard, Timothy G.; Lyda, R.; Kim, Tony S.

doi:10.2514/6.2010-6724

Cited by 8 publications

(2 citation statements)

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“…CECE has a throttling ability of 10 : 1 and the high delta pressure injector for LOX. 4) In the examination of the LH 2 supply system, the pump discharge pressure is set to 20 MPa for the 1,000 kN-level engine and 5 MPa for the 100 kN-level engine referring to the LE-5B and LE-X engines. 18,19) In the examination of the LOX supply system, the ratio of the pressure drop in plumbing to the chamber pressure, C pl , is set to be 0.15.…”

Section: Resultsmentioning

confidence: 99%

“…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%

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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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Section: Resultsmentioning

confidence: 99%