Burners for Supersonic Ram-Jets

Mullen, James W.; Fenn, J.ohn; Garmon, Roland

doi:10.1021/ie50493a052

Cited by 17 publications

(8 citation statements)

References 11 publications

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“…As was pointed out by Mullen et al (4), probably because of incomplete vaporization the combustion level, and, therefore, theburner pressure, do not decrease in the rich region with this fuel but remain relatively constant beyond the stoichiometric point. It is, therefore, consistent with the picture developed above that regenerative pressure fluctuations culminating in blowoff should not occur with kerosene.…”

Section: Duct Tonesupporting

confidence: 50%

“…For example, a burner comprising a simple 0.75-inch oxyhydrogen pilot cone is much more prone to instability than one comprising the same cone with the addition of four radial gutters. Correspondingly, with a 14-inch tail pipe and comparable inlet conditions the former attains an impulse efficiency of 68% as contrasted with 90% in the latter case (4). Although by increasing the tail pipe length the impulse efficiency obtainable with poor igniters could be greatly increased, the tendency toward rough burning was not decreased.…”

Section: Causes Of Rough Burningmentioning

confidence: 87%

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Burners for Supersonic Ram-Jets

Fenn¹,

Forney²,

Garmon³

1951

Ind. Eng. Chem.

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Section: Duct Tonesupporting

confidence: 50%

Section: Causes Of Rough Burningmentioning

confidence: 87%

Burners for Supersonic Ram-Jets

Fenn¹,

Forney²,

Garmon³

1951

Ind. Eng. Chem.

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“…per (hour) (cubic foot) (atm.1•8). Such a rate is an order of magnitude greater than the highest published experimental value (11) for an appreciable volume known to the authors. Lack of other data makes direct comparison of these results impossible.…”

Section: Observed Space Heat Release Rates Are Very Highmentioning

confidence: 54%

High Temperature Reaction Rates in Hydrocarbon Combustion

Longwell¹,

Weiss²

1955

Ind. Eng. Chem.

264

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“…The S values have not been corrected for these losses which, by direct measurement, amou .ted to 23 per cent and 12 per cent respectively in runs 236 and 225. Under similar conditions with hydrocarbon burners where the heat loss is about 5 per cent, an efficiency of 85 per cent is obtained with a 14-inch tailpipe [27].The next eight runs indicate the generally more efficient operation observed in the split-flow annular type of system. The heat losses through the wall appear to be small, and the downstream mixing processes are enhanced by this technique.…”

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confidence: 78%

Section: Confidentialmentioning

confidence: 91%

Ramjet Technology. Chapter 16. Solid Fuel Ramjets

Wolf¹,

Mullen²

1951

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The ramjet powerplant for aircraft propulsion, conceived nearly 40 years ago [22,23], has been available in useful form for less than a decade. Its deve_opers focused their efforts largely on liquid fuels, particularly hydrocarbons of the gasoline or kerosene type. Nevertheless, during the period of resurgent interest occasioned by World War II, there was early recognition that solid fuels might offer certain design and performance advantages.Although the Germans were chiefly interested in coal and even wood, Sanger and Bredt [36] did suggest the use of metal dispersions to obtain higher flame temperatures and, Hence, thrust coefficients. Lippisch [20] and Schwabl [37] were first attracted to solids because of the inherent simplicity of the fuel system in short-duration missiles and artillery or mortar shells. They carried out numerous burner tests with briquetted carbon and natural coal charges, later extending the scope of their work to designs suitable for piloted aircraft.At Great Britain's National Gas Turbine Establishment, Roberson [33] prepared a theoretical performance survey covering a very large number of solid fuels. Actual experimental work appears to have been confined to aluminum and was conducted Some attention was also given to aluminum hydrocarbon slurries by Mazurkiewicz [25].In this country, at the Applied Physics Laboratory of The Johns Hopkins University, Berl [8] developed techniques for improving the output of a lean propylene oxide burner through the addition of aluminum and magnesium powders. At the Jet Propulsion Laboratory of the California Institute of Technology, Bartel and Kannie [7] used carbon tubes in flow combustion tests and Alperin [1] considered the problem from a theoretical viewpoint. Damon and his associates at the Bureau of Mines [11] initially investigated coal for ramjet use, but later began to incorporate the light metals in their formulations. Smith [39] extended to ramjet flow conditions the earlier fundamental investigations of Hottel and his Massachusetts Institute of Technology co-workers [44,12,29] into the mechanism of burning carbon spheres. The experimental phases of the program were continued under the direction of Hottel and Williams [3,4]. Collins and Squiers of the Continental Aviation and Engineering Corporation intensively examined the application of magnesium to booster [24,40] and gun-launched [42] ramjets. To a lesser extent they also employed aluminum, boron, and napthaiene in their experimental program. Wolf and others from Experiment Incorporated [46] assisted in the early magnes-.um fuel and burner development.Two types of propellant charges resulted from this joint program. Either of these ^ives satisfactory performance under the internal flow conditions obtained in supersonic ramjets and meet to a large extent all other requirements for operational feasibility. Later, the effect of a solid or liquid dispersed phase, such as magnesium oxide, on the aerothermodynamic relations employed in ramjet design calculations was examined [47]. [50,53]...

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Burners for Supersonic Ram-Jets

Cited by 17 publications

References 11 publications

Burners for Supersonic Ram-Jets

Burners for Supersonic Ram-Jets

High Temperature Reaction Rates in Hydrocarbon Combustion

Ramjet Technology. Chapter 16. Solid Fuel Ramjets

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