Fuel Density Effects and Supersonic Combustion Characteristics of Hydrogen/hydrocarbon Mixed Fuels PDF Download

Author: Randy Alan Bell
Publisher:
ISBN:
Category :
Languages : en
Pages : 110

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Author: Ahmed A. Taha
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 378

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Author: W. W. HORSTMAN
Publisher:
ISBN:
Category :
Languages : en
Pages : 1

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Book Description
The combustion performance of potential hydrocarbon fuels for supersonic aircraft jet engines was evaluated in a J-79 engine combustor. The combustor test conditions simulated full-scale engine operation at high altit des and supersonic speeds. As the inlet air pressure decreased, the combustion efficienc decreased. Differences in combustion efficiency were noted between 8 fuels at the various operating c n iti ns. A comparison of the fuel flow requirement for a constant urner temperature rise (thrust) at two test conditions indicated lowest fuel flow on a weight basis for a paraffinic fuel and a production type JP-6 fuel; lowest fuel flow on a volume basis was indicated for a naphthenic fuel and isopropylbicyclohexyl. At a more severe operating condition the isopropylbicyclohexyl indicated a low fuel flow requirement on both a weight and volume basis. The effect of fuel preheat on combustion efficiency was negligible. Combustor liner temperat re ere not affected appreciably by fuel differences. The carbon deposits were very light for all fuels. The fuels with the higher ASTM initial and 10% boiling points had higher ignition requirements at simulated altitude relight test conditions. (Author).

Author: S. N. Tiwari
Publisher:
ISBN:
Category :
Languages : en
Pages :

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Author: Stuart Hersh
Publisher:
ISBN:
Category : Boron as fuel
Languages : en
Pages : 46

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The program is directed towards answering the following question. Given a boron combustible particle of known initial size and composition moving at a high relative velocity in a gaseous medium, how are the combustion behavior and particle dynamics influenced by the particle (gas relative velocity, gas composition, temperature, and pressure anticipated in operational combustors. The role of the shock tube in answering this question is discussed. An 'ideal' experiment is postulated and several possible practical experimental techniques are assessed relative to this standard. To aid in the assessment of the practicality of an experimental technique, a computer program was developed to compute particle trajectories for shock tube flows. Some preliminary experiments aimed at establishing the applicability of a reflected shock technique to the measurement of burning particle drag coefficients were carried out. The results of these experiments yielded very high values of the drag coefficient. At the present time, it is not known if this result was due to the roughness of the particles, static charge effects, the effect of combustion or the preliminary nature of the experiments. In all probability a combination of the above factors is involved. (Author).

Author: W. Chinitz
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 101

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Book Description
A theoretical and experimental investigation has been undertaken to define the supersonic combustion characteristics of endothermic hydrocarbon fuels which are of interest as a result of research carried out at Shell Development Company. In the program discussed herein, principal attention was focussed upon the propane and methylcyclohexane dehydrogenation fuel systems. The ultimate objective is to define the parameters that affect the combustion process and to establish the feasibility of burning these fuels in supersonic flows.

Author: Mingbo Sun
Publisher: Springer Nature
ISBN: 9811535957
Category : Technology & Engineering
Languages : en
Pages : 380

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Book Description
This book describes the unsteady phenomena needed to understand supersonic combustion. Following an initial chapter that introduces readers to the basic concepts in and classical studies on unsteady supersonic combustion, the book highlights recent studies on unsteady phenomena, which offer insights on e.g. interactions between acoustic waves and flames, flow dominating instability, ignition instability, flame flashback, and near-blowout-limit combustion. In turn, the book discusses in detail the fundamental mechanisms of these phenomena, and puts forward practical suggestions for future scramjet design.

Author: G. Yu
Publisher:
ISBN:
Category :
Languages : en
Pages :

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Author: W. Chinitz
Publisher:
ISBN:
Category :
Languages : en
Pages : 101

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Book Description
A theoretical and experimental investigation has been undertaken to define the supersonic combustion characteristics of endothermic hydrocarbon fuels which are of interest as a result of research carried out at Shell Development Company. In the program discussed herein, principal attention was focussed upon the propane and methylcyclohexane dehydrogenation fuel systems. The ultimate objective is to define the parameters that affect the combustion process and to establish the feasibility of burning these fuels in supersonic flows. (Author).

Author: Edward G. Stricker
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 28

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Book Description
The combustion efficiency and the altitude operational limits of three liquid hydrocarbon fuels having high volumetric energy content (decalin, tetralin, and monomethylnaphthalene) were compared with an AN-F-58 fuel in a single tubular combustor from a J33 turbojet engine. The investigation covered a range of simulated engine conditions for altitudes from 20,000 to 60,000 feet; 42- to 107-percent normal rated engine speed; and a flight Mach number of 0.6. The independent effects of combustor-inlet-air temperature, pressure, and mass air flow on the combustion efficiency of the fuels were determined around a standard combustion-inlet condition.