System sensitivity studies of a LOX/methane expander cycle rocket engine

Crocker, Andrew; Peery, S.

doi:10.2514/6.1998-3674

Cited by 10 publications

(7 citation statements)

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“…7,8) In addition, conceptual studies for methane-fueled engines have been conducted to examine their operating characteristics. [9][10][11][12][13] Pempie and Boccaletto studied the expander cycle of 150 kN thrust upper-stage engines and discussed the operating features. 9) They compared the operating conditions of the engine with those of a hydrogen-fueled engine.…”

Section: Introductionmentioning

confidence: 99%

Expander and Coolant-Bleed Cycles of Methane-Fueled Rocket Engines

Kanda

Sato

Kimura

et al. 2018

Trans. Japan Soc. Aero. S Sci.

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This paper describes the characteristics of methane-fueled rocket engines and compares these characteristics with those of hydrogen-fueled engines in terms of both expander and coolant-bleed cycles. Methane vaporizes in a cooling jacket under low-pressure operating conditions, whereas it liquefies in the turbine in the coolant-bleed cycle. The thermodynamic property of methane limits the operating range of methane-fueled engines. When the coolant-bleed cycle is used, the specific impulse degradation of methane-fueled engines becomes larger compared to that of hydrogen-fueled engines. This is due to methane having a lower specific heat and temperature after regenerative cooling. Even though the heat absorbing ability of methane is much lower than that of hydrogen, methane-fueled engines can operate with higher chamber pressures using the expander cycle. This is due to the larger density and the higher temperature after the regenerative cooling of liquid methane. Throttling of the methane-fueled engines does not have a great impact on the pump exit pressure in the expander cycle, whereas it increases the bleed ratio and degrades the specific impulse in the coolant bleed cycle of methane-fueled engines.

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Section: Introductionmentioning

confidence: 99%

Expander and Coolant-Bleed Cycles of Methane-Fueled Rocket Engines

Kanda

Sato

Kimura

et al. 2018

Trans. Japan Soc. Aero. S Sci.

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“…The straightforward. Any increase in the surface area or heat end result is that chamber pressure tends to decrease transfer coefficient will result in a proportional increase in with larger thrust levels 5 . There are ways, however, the heat flux.…”

Section: Number(s)mentioning

confidence: 99%

Another Look at the Practical and Theoretical Limits of an Expander Cycle, LOX/H2 Engine

Krach¹,

Sutton²

1999

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Public reporting burden for this collection of information is estimated to average 1 hour per response, including the time for reviewing instructions, searching existing data sources, gathering and maintaining the data needed, and completing and reviewing this collection of information. Send comments regarding this burden estimate or any other aspect of this collection ot information, including suggestions for reducing this burden to Department of Defense, Washington Headquarters Services, Directorate for Information Operations and Reports (0704-0188), 1215 Jefferson Davis Highway, Suite 1204, Arlington, VA 22202-4302. Respondents should be aware that notwithstanding any other provision of law, no person shall be subject to any penalty for failing to comply with a collection of information if it does not display a currently valid OMB control number. PLEASE DO NOT RETURN YOUR FORM TO THE ABOVE ADDRESS. REPORT DATE (DD-MM-YYYY)2 ABSTRACTAdvances in materials and increases in turbopump efficiencies necessitate another look at the theoretical and practical limits for growth in chamber pressure and thrust in a liquid rocket expander cycle engine. The basic equations for turbopump power and heat flux rate out of the cooling jacket are examined to determine the theoretical limits for chamber pressure using an expander cycle. Turbopump efficiencies and operating speed limits for a LOX/H 2 expander engine are explored to determine practical limits as applied to the chamber pressure.

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“…Its engineering is well known in industry (Pumps, valves, etc…). Liquid rocket engines burning methane with oxygen have never flown, but many studies and some tests in Russia [2], Japan [3], USA [4], Korea [5] and Europe [6], [7] have been performed.…”

Section: Iintroductionmentioning

confidence: 99%

LOX/CH4 and LOX/LH2 Heavy Launch Vehicle Comparison

Vernin¹,

Pempie²

2009

45th AIAA/ASME/SAE/ASEE Joint Propulsion Conference &Amp;amp; Exhibit

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LOX/CH4 is often regarded as a new promising propellant. As a light hydrocarbon the advantage of methane compared to RP-1 is its worldwide availability, higher ISP. From a propulsion point of view methane leads to low soot combustion and a good capability to cool the combustion chamber without the risk of cracking and deposit. Compared to liquid Hydrogen fuel despite its lower IPS, methane presents a higher density and a high vapor pressure.The topic of this paper is to present a trade-off design of two kinds of heavy launch vehicle able to bring to GTO a 6t class payload. Each of three stages of the launcher burn either LOX/LH2 or LOX/CH4. The key factors for comparison are the GLOW, the propellant mass and engines thrust for each stage. NomenclatureFs = Delivered thrust at ground level (kN) Fv = Delivered thrust at sea level (kN) ISPs = Specific impulse at ground level (s) ISPv = Specific impulse at sea level (s) Me = Propellant mass (T) Pc = Chamber pressure (bar)

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System sensitivity studies of a LOX/methane expander cycle rocket engine

Cited by 10 publications

References 0 publications

Expander and Coolant-Bleed Cycles of Methane-Fueled Rocket Engines

Expander and Coolant-Bleed Cycles of Methane-Fueled Rocket Engines

Another Look at the Practical and Theoretical Limits of an Expander Cycle, LOX/H2 Engine

LOX/CH4 and LOX/LH2 Heavy Launch Vehicle Comparison

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