Ignition characterization of the GOX/ethanol propellant combination

Lawver, B. R.; Rousar, D. C.; Boyd, William C.

doi:10.2514/6.1984-1467

Cited by 5 publications

(4 citation statements)

References 0 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…The RCE design leverages torch igniter concepts that have been in development since the 1980's over several technology projects 4,10 . The injector concept uses core fuel orifices near the spark plug tip for a high mixture ratio (i.e.…”

Section: A Enginementioning

confidence: 99%

Development and Flight Operation of a 5 lbf to 20 lbf O2/CH4 Roll Control Engine for Project Morpheus

McManamen¹,

Hurlbert²,

Kroeger³

2014

50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference

View full text Add to dashboard Cite

The development and flight operation of a 22 N to 89 N (5 lbf to 20 lbf) O2/CH4 rocket engine is discussed herein. The Roll Control Engine (RCE) was designed by NASA JSC for the Project Morpheus flying vertical test bed and is fully integrated with the Morpheus main engine. Morpheus is a NASA Advanced Exploration System (AES) Project lead out of JSC. Several iterations of the RCE design have resolved some technical problems which are described in the present work. Over 20 flight tests have demonstrated that the Roll Control System (RCS) engines are reliable, capable of operation over a wide range of pressures (2400 kPa to 1000 kPa or 350 psig to 150 psig) and propellant temperatures (gas to liquid), and meet the control requirements for the vehicle. Information regarding ground turnaround and flight operational experience in the earth atmospheric environment is presented. The purpose of this work is to disseminate the knowledge that Project Morpheus has gained through research and development of this engine.Nomenclature Soff = FDIR fail off strike Ft = thrust force Isp = specific impulse Pc = chamber pressure Pin = engine inlet pressure Ptank = propellant tank pressure Q = volumetric flow rate Tin = engine inlet fluid temperature Tnoz = nozzle outer skin temperature Tsat = saturation temperature Ttank = propellant tank fluid temperature Vb = RCS bleed valve open command Vm = RCE main valve open command Acronyms CFM = cryogenic fluid management CG = center of gravity CNTRL = Morpheus control software EMI = electromagnetic interference FDIR = fault detection, isolation, and reconfiguration FFC = fuel film cooling ISRU = in-situ resource utilization MIB = minimum impulse bit MR = mass mixture ratio PCAD = propulsion and cryogenics advanced development PROP = Morpheus propulsion software RCE = roll control engine RCS = roll control system 1 Morpheus RCS Lead, Propulsion Branch, EP4, and AIAA Member.

show abstract

Section: A Enginementioning

confidence: 99%

Development and Flight Operation of a 5 lbf to 20 lbf O2/CH4 Roll Control Engine for Project Morpheus

McManamen¹,

Hurlbert²,

Kroeger³

2014

50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference

View full text Add to dashboard Cite

show abstract

“…The effects of propellant inlet temperature were studied by Lawver et al 49 for GOX/ethanol, and ignition was sensitive only to the fuel temperature. As a worst case, an abnormal ignition delay of approximately 1 s was observed for cold fuel inlet temperature of 17IK, a low chamber pressure of 0.55 MPa (80 psia), and a low mixture ratio of 0.8.…”

Section: F Spark Ignition Devicesmentioning

confidence: 99%

“…An earlier criticism of published data was provided by Ballal and Lefebvre, 55 wherein they identified the importance of spark gap, spark duration, spark phase, and degree of turbulence. Lawver et al 49 demonstrated ignition with 10 mJ for GO 2 /ethanol in a torch-type igniter for a 620-lbf engine. Spark levels down to 10 mJ have been demonstrated when igniting a LOX/RP-1, 2000-psia, 20,000-lbf thrust chamber.…”

Section: F Spark Ignition Devicesmentioning

confidence: 99%

Propellant Ignition and Flame Propagation

2004

Liquid Rocket Thrust Chambers

View full text Add to dashboard Cite

Nomenclature AB = Arrhenius preexponentials C = concentration c p = heat capacity d q = quenching distance E -activation energy Emin = minimum ignition energy F = fuel h = heat k = conductivity / = liquid m -reaction order with respect to fuel TV = total order of reaction n = reaction order with respect to oxidizer O = oxidizer o = initial condition or totalThe ratio of this ignition pressure to the nominal pressure is then given byThis expression should not be taken as exact. It provides only an estimate of the ignition overpressure and indicates that a longer delay r t will induce a higher pressure peak. To reduce the amplitude of this pressure, one has to decrease the delay and inject the propellants progressively into the chamber. Purchased from American Institute of Aeronautics and Astronautics Downloaded by PENNSYLVANIA STATE UNIVERSITY on March 15, 2015 | http://arc.aiaa.org |

show abstract

“…While early work focused on LO 2 /LH 2 , the majority of these projects over the past 35þ years have focused on extending the technologies for oxygen/hydrocarbon propellant combinations [5]. Aerojet has been involved with the development of a variety of combustion devices and propulsion systems that utilize oxygen and a range of potential hydrocarbon fuels, including RP-1, RP-2, JP-10, propane, ethanol, and methane [6][7][8][9][10][11][12]. This background has proven beneficial with respect to NASA's interest in advancing technologies for oxygen/hydrocarbon propellant systems.…”

Section: Introductionmentioning

confidence: 99%