Thrust augmentation optimization through supersonic after-burning in scramjet engine nozzles via surrogate-assisted evolutionary algorithms

Michael J. Candon, Hideaki Ogawa, Graham E. Dorrington

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

Abstract

Scramjets are a class of hypersonic airbreathing engine that are associated with realizing the technology required for economical, reliable and high-speed access-to-space and atmospheric transport. The expanding flow in the scramjet nozzle comprises of unburned hydrogen which under ideal conditions, can be utilized to introduce an after-burning scheme. After-burning augments the thrust produced by the scramjet nozzle and creates a more robust nozzle design. This paper presents a single-objective design optimization considering three design variables with the objective of producing maximum thrust augmentation. It is found that significant levels of thrust augmentation are produced based upon contributions from increased pressure, mass flow and energy in the nozzle. Further understanding of the phenomenon by which thrust augmentation is being produced is provided in the form of variance-based global sensitivity analysis, force contribution breakdowns, analysis of the nozzle flowfields, analysis of the surface pressure and shear stress distributions acting on the nozzle wall and analysis of the combustion efficiency.

Original languageEnglish
Title of host publication53rd AIAA Aerospace Sciences Meeting
PublisherAmerican Institute of Aeronautics and Astronautics Inc, AIAA
ISBN (Print)9781624103438
DOIs
Publication statusPublished - Jan 1 2015
Externally publishedYes
Event53rd AIAA Aerospace Sciences Meeting, 2015 - Kissimmee, United States
Duration: Jan 5 2015Jan 9 2015

Publication series

Name53rd AIAA Aerospace Sciences Meeting

Other

Other53rd AIAA Aerospace Sciences Meeting, 2015
CountryUnited States
CityKissimmee
Period1/5/151/9/15

Fingerprint

Evolutionary algorithms
Nozzles
Engines
Nozzle design
Hypersonic aerodynamics
Sensitivity analysis
Stress concentration
Shear stress
Hydrogen

All Science Journal Classification (ASJC) codes

  • Aerospace Engineering

Cite this

Candon, M. J., Ogawa, H., & Dorrington, G. E. (2015). Thrust augmentation optimization through supersonic after-burning in scramjet engine nozzles via surrogate-assisted evolutionary algorithms. In 53rd AIAA Aerospace Sciences Meeting [AIAA 2015-1106] (53rd AIAA Aerospace Sciences Meeting). American Institute of Aeronautics and Astronautics Inc, AIAA. https://doi.org/10.2514/6.2015-1106

Thrust augmentation optimization through supersonic after-burning in scramjet engine nozzles via surrogate-assisted evolutionary algorithms. / Candon, Michael J.; Ogawa, Hideaki; Dorrington, Graham E.

53rd AIAA Aerospace Sciences Meeting. American Institute of Aeronautics and Astronautics Inc, AIAA, 2015. AIAA 2015-1106 (53rd AIAA Aerospace Sciences Meeting).

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

Candon, MJ, Ogawa, H & Dorrington, GE 2015, Thrust augmentation optimization through supersonic after-burning in scramjet engine nozzles via surrogate-assisted evolutionary algorithms. in 53rd AIAA Aerospace Sciences Meeting., AIAA 2015-1106, 53rd AIAA Aerospace Sciences Meeting, American Institute of Aeronautics and Astronautics Inc, AIAA, 53rd AIAA Aerospace Sciences Meeting, 2015, Kissimmee, United States, 1/5/15. https://doi.org/10.2514/6.2015-1106
Candon MJ, Ogawa H, Dorrington GE. Thrust augmentation optimization through supersonic after-burning in scramjet engine nozzles via surrogate-assisted evolutionary algorithms. In 53rd AIAA Aerospace Sciences Meeting. American Institute of Aeronautics and Astronautics Inc, AIAA. 2015. AIAA 2015-1106. (53rd AIAA Aerospace Sciences Meeting). https://doi.org/10.2514/6.2015-1106
Candon, Michael J. ; Ogawa, Hideaki ; Dorrington, Graham E. / Thrust augmentation optimization through supersonic after-burning in scramjet engine nozzles via surrogate-assisted evolutionary algorithms. 53rd AIAA Aerospace Sciences Meeting. American Institute of Aeronautics and Astronautics Inc, AIAA, 2015. (53rd AIAA Aerospace Sciences Meeting).
@inproceedings{ad0493ec68d143dfa44ee350f93cf314,
title = "Thrust augmentation optimization through supersonic after-burning in scramjet engine nozzles via surrogate-assisted evolutionary algorithms",
abstract = "Scramjets are a class of hypersonic airbreathing engine that are associated with realizing the technology required for economical, reliable and high-speed access-to-space and atmospheric transport. The expanding flow in the scramjet nozzle comprises of unburned hydrogen which under ideal conditions, can be utilized to introduce an after-burning scheme. After-burning augments the thrust produced by the scramjet nozzle and creates a more robust nozzle design. This paper presents a single-objective design optimization considering three design variables with the objective of producing maximum thrust augmentation. It is found that significant levels of thrust augmentation are produced based upon contributions from increased pressure, mass flow and energy in the nozzle. Further understanding of the phenomenon by which thrust augmentation is being produced is provided in the form of variance-based global sensitivity analysis, force contribution breakdowns, analysis of the nozzle flowfields, analysis of the surface pressure and shear stress distributions acting on the nozzle wall and analysis of the combustion efficiency.",
author = "Candon, {Michael J.} and Hideaki Ogawa and Dorrington, {Graham E.}",
year = "2015",
month = "1",
day = "1",
doi = "10.2514/6.2015-1106",
language = "English",
isbn = "9781624103438",
series = "53rd AIAA Aerospace Sciences Meeting",
publisher = "American Institute of Aeronautics and Astronautics Inc, AIAA",
booktitle = "53rd AIAA Aerospace Sciences Meeting",

}

TY - GEN

T1 - Thrust augmentation optimization through supersonic after-burning in scramjet engine nozzles via surrogate-assisted evolutionary algorithms

AU - Candon, Michael J.

AU - Ogawa, Hideaki

AU - Dorrington, Graham E.

PY - 2015/1/1

Y1 - 2015/1/1

N2 - Scramjets are a class of hypersonic airbreathing engine that are associated with realizing the technology required for economical, reliable and high-speed access-to-space and atmospheric transport. The expanding flow in the scramjet nozzle comprises of unburned hydrogen which under ideal conditions, can be utilized to introduce an after-burning scheme. After-burning augments the thrust produced by the scramjet nozzle and creates a more robust nozzle design. This paper presents a single-objective design optimization considering three design variables with the objective of producing maximum thrust augmentation. It is found that significant levels of thrust augmentation are produced based upon contributions from increased pressure, mass flow and energy in the nozzle. Further understanding of the phenomenon by which thrust augmentation is being produced is provided in the form of variance-based global sensitivity analysis, force contribution breakdowns, analysis of the nozzle flowfields, analysis of the surface pressure and shear stress distributions acting on the nozzle wall and analysis of the combustion efficiency.

AB - Scramjets are a class of hypersonic airbreathing engine that are associated with realizing the technology required for economical, reliable and high-speed access-to-space and atmospheric transport. The expanding flow in the scramjet nozzle comprises of unburned hydrogen which under ideal conditions, can be utilized to introduce an after-burning scheme. After-burning augments the thrust produced by the scramjet nozzle and creates a more robust nozzle design. This paper presents a single-objective design optimization considering three design variables with the objective of producing maximum thrust augmentation. It is found that significant levels of thrust augmentation are produced based upon contributions from increased pressure, mass flow and energy in the nozzle. Further understanding of the phenomenon by which thrust augmentation is being produced is provided in the form of variance-based global sensitivity analysis, force contribution breakdowns, analysis of the nozzle flowfields, analysis of the surface pressure and shear stress distributions acting on the nozzle wall and analysis of the combustion efficiency.

UR - http://www.scopus.com/inward/record.url?scp=84980390580&partnerID=8YFLogxK

UR - http://www.scopus.com/inward/citedby.url?scp=84980390580&partnerID=8YFLogxK

U2 - 10.2514/6.2015-1106

DO - 10.2514/6.2015-1106

M3 - Conference contribution

AN - SCOPUS:84980390580

SN - 9781624103438

T3 - 53rd AIAA Aerospace Sciences Meeting

BT - 53rd AIAA Aerospace Sciences Meeting

PB - American Institute of Aeronautics and Astronautics Inc, AIAA

ER -