Mixing characteristics of cracked gaseous hydrocarbon fuels in scramjets

Magesh R. Ravindran, Mathew G. Bricalli, Adrian S. Pudsey, Hideaki Ogawa

Research output: Chapter in Book/Report/Conference proceedingConference contribution

1 Citation (Scopus)

Abstract

High-performance hydrocarbon-fuelled scramjet engines require efficient fuel-air mixing due to the relatively short flow residence time through the combustor. At high temperatures, hydrocarbon fuels react endothermically and absorb thermal energy from the surroundings. The process known as cracking becomes essential at high Mach numbers to increase the total heat-sink capacity of the fuel. This study presents the results of numerical simulations that investigate the mixing characteristics of cracked gaseous heavy hydrocarbon fuels injected through a circular, flush-wall porthole injector inclined at 45-deg to the freestream. The mixing characteristics of six fuel compositions representing various cracking efficiencies ranging from 0-100% are investigated. The mixing rates and flow structures are found to change with fuel compositions. As the cracking increases, the mixing and streamwise circulation increase for an injectant. However, the jet penetration and stagnation pressure losses decrease. The density gradients determine the strength of vorticity in the vicinity of the injector. The streamwise circulation is found to have a strong influence on the mixing and the strength of bow shock on the jet penetration. Overall, it is shown that there are mixing benefits to be gained by injecting cracked hydrocarbon fuels compared to heavy uncracked fuels in scramjets.

Original languageEnglish
Title of host publication22nd AIAA International Space Planes and Hypersonics Systems and Technologies Conference
PublisherAmerican Institute of Aeronautics and Astronautics Inc, AIAA
ISBN (Print)9781624105777
DOIs
Publication statusPublished - Jan 1 2018
Externally publishedYes
Event22nd AIAA International Space Planes and Hypersonics Systems and Technologies Conference, 2018 - Orlando, United States
Duration: Sep 17 2018Sep 19 2018

Publication series

Name22nd AIAA International Space Planes and Hypersonics Systems and Technologies Conference

Conference

Conference22nd AIAA International Space Planes and Hypersonics Systems and Technologies Conference, 2018
CountryUnited States
CityOrlando
Period9/17/189/19/18

Fingerprint

gaseous fuels
hydrocarbon fuels
supersonic combustion ramjet engines
Hydrocarbons
hydrocarbon
injectors
penetration
stagnation pressure
Residual fuels
heat sinks
flow structure
Heat sinks
bows
Flow structure
combustion chambers
Thermal energy
Combustors
Vorticity
Chemical analysis
thermal energy

All Science Journal Classification (ASJC) codes

  • Control and Systems Engineering
  • Space and Planetary Science
  • Aerospace Engineering

Cite this

Ravindran, M. R., Bricalli, M. G., Pudsey, A. S., & Ogawa, H. (2018). Mixing characteristics of cracked gaseous hydrocarbon fuels in scramjets. In 22nd AIAA International Space Planes and Hypersonics Systems and Technologies Conference [AIAA 2018-5260] (22nd AIAA International Space Planes and Hypersonics Systems and Technologies Conference). American Institute of Aeronautics and Astronautics Inc, AIAA. https://doi.org/10.2514/6.2018-5260

Mixing characteristics of cracked gaseous hydrocarbon fuels in scramjets. / Ravindran, Magesh R.; Bricalli, Mathew G.; Pudsey, Adrian S.; Ogawa, Hideaki.

22nd AIAA International Space Planes and Hypersonics Systems and Technologies Conference. American Institute of Aeronautics and Astronautics Inc, AIAA, 2018. AIAA 2018-5260 (22nd AIAA International Space Planes and Hypersonics Systems and Technologies Conference).

Research output: Chapter in Book/Report/Conference proceedingConference contribution

Ravindran, MR, Bricalli, MG, Pudsey, AS & Ogawa, H 2018, Mixing characteristics of cracked gaseous hydrocarbon fuels in scramjets. in 22nd AIAA International Space Planes and Hypersonics Systems and Technologies Conference., AIAA 2018-5260, 22nd AIAA International Space Planes and Hypersonics Systems and Technologies Conference, American Institute of Aeronautics and Astronautics Inc, AIAA, 22nd AIAA International Space Planes and Hypersonics Systems and Technologies Conference, 2018, Orlando, United States, 9/17/18. https://doi.org/10.2514/6.2018-5260
Ravindran MR, Bricalli MG, Pudsey AS, Ogawa H. Mixing characteristics of cracked gaseous hydrocarbon fuels in scramjets. In 22nd AIAA International Space Planes and Hypersonics Systems and Technologies Conference. American Institute of Aeronautics and Astronautics Inc, AIAA. 2018. AIAA 2018-5260. (22nd AIAA International Space Planes and Hypersonics Systems and Technologies Conference). https://doi.org/10.2514/6.2018-5260
Ravindran, Magesh R. ; Bricalli, Mathew G. ; Pudsey, Adrian S. ; Ogawa, Hideaki. / Mixing characteristics of cracked gaseous hydrocarbon fuels in scramjets. 22nd AIAA International Space Planes and Hypersonics Systems and Technologies Conference. American Institute of Aeronautics and Astronautics Inc, AIAA, 2018. (22nd AIAA International Space Planes and Hypersonics Systems and Technologies Conference).
@inproceedings{18b8a4813b604b6d8a5f35287058e3b2,
title = "Mixing characteristics of cracked gaseous hydrocarbon fuels in scramjets",
abstract = "High-performance hydrocarbon-fuelled scramjet engines require efficient fuel-air mixing due to the relatively short flow residence time through the combustor. At high temperatures, hydrocarbon fuels react endothermically and absorb thermal energy from the surroundings. The process known as cracking becomes essential at high Mach numbers to increase the total heat-sink capacity of the fuel. This study presents the results of numerical simulations that investigate the mixing characteristics of cracked gaseous heavy hydrocarbon fuels injected through a circular, flush-wall porthole injector inclined at 45-deg to the freestream. The mixing characteristics of six fuel compositions representing various cracking efficiencies ranging from 0-100{\%} are investigated. The mixing rates and flow structures are found to change with fuel compositions. As the cracking increases, the mixing and streamwise circulation increase for an injectant. However, the jet penetration and stagnation pressure losses decrease. The density gradients determine the strength of vorticity in the vicinity of the injector. The streamwise circulation is found to have a strong influence on the mixing and the strength of bow shock on the jet penetration. Overall, it is shown that there are mixing benefits to be gained by injecting cracked hydrocarbon fuels compared to heavy uncracked fuels in scramjets.",
author = "Ravindran, {Magesh R.} and Bricalli, {Mathew G.} and Pudsey, {Adrian S.} and Hideaki Ogawa",
year = "2018",
month = "1",
day = "1",
doi = "10.2514/6.2018-5260",
language = "English",
isbn = "9781624105777",
series = "22nd AIAA International Space Planes and Hypersonics Systems and Technologies Conference",
publisher = "American Institute of Aeronautics and Astronautics Inc, AIAA",
booktitle = "22nd AIAA International Space Planes and Hypersonics Systems and Technologies Conference",

}

TY - GEN

T1 - Mixing characteristics of cracked gaseous hydrocarbon fuels in scramjets

AU - Ravindran, Magesh R.

AU - Bricalli, Mathew G.

AU - Pudsey, Adrian S.

AU - Ogawa, Hideaki

PY - 2018/1/1

Y1 - 2018/1/1

N2 - High-performance hydrocarbon-fuelled scramjet engines require efficient fuel-air mixing due to the relatively short flow residence time through the combustor. At high temperatures, hydrocarbon fuels react endothermically and absorb thermal energy from the surroundings. The process known as cracking becomes essential at high Mach numbers to increase the total heat-sink capacity of the fuel. This study presents the results of numerical simulations that investigate the mixing characteristics of cracked gaseous heavy hydrocarbon fuels injected through a circular, flush-wall porthole injector inclined at 45-deg to the freestream. The mixing characteristics of six fuel compositions representing various cracking efficiencies ranging from 0-100% are investigated. The mixing rates and flow structures are found to change with fuel compositions. As the cracking increases, the mixing and streamwise circulation increase for an injectant. However, the jet penetration and stagnation pressure losses decrease. The density gradients determine the strength of vorticity in the vicinity of the injector. The streamwise circulation is found to have a strong influence on the mixing and the strength of bow shock on the jet penetration. Overall, it is shown that there are mixing benefits to be gained by injecting cracked hydrocarbon fuels compared to heavy uncracked fuels in scramjets.

AB - High-performance hydrocarbon-fuelled scramjet engines require efficient fuel-air mixing due to the relatively short flow residence time through the combustor. At high temperatures, hydrocarbon fuels react endothermically and absorb thermal energy from the surroundings. The process known as cracking becomes essential at high Mach numbers to increase the total heat-sink capacity of the fuel. This study presents the results of numerical simulations that investigate the mixing characteristics of cracked gaseous heavy hydrocarbon fuels injected through a circular, flush-wall porthole injector inclined at 45-deg to the freestream. The mixing characteristics of six fuel compositions representing various cracking efficiencies ranging from 0-100% are investigated. The mixing rates and flow structures are found to change with fuel compositions. As the cracking increases, the mixing and streamwise circulation increase for an injectant. However, the jet penetration and stagnation pressure losses decrease. The density gradients determine the strength of vorticity in the vicinity of the injector. The streamwise circulation is found to have a strong influence on the mixing and the strength of bow shock on the jet penetration. Overall, it is shown that there are mixing benefits to be gained by injecting cracked hydrocarbon fuels compared to heavy uncracked fuels in scramjets.

UR - http://www.scopus.com/inward/record.url?scp=85056191688&partnerID=8YFLogxK

UR - http://www.scopus.com/inward/citedby.url?scp=85056191688&partnerID=8YFLogxK

U2 - 10.2514/6.2018-5260

DO - 10.2514/6.2018-5260

M3 - Conference contribution

AN - SCOPUS:85056191688

SN - 9781624105777

T3 - 22nd AIAA International Space Planes and Hypersonics Systems and Technologies Conference

BT - 22nd AIAA International Space Planes and Hypersonics Systems and Technologies Conference

PB - American Institute of Aeronautics and Astronautics Inc, AIAA

ER -