A comparison of numerical predictions of supersonic combustion of hydrogen using different chemistry models in a model combustor

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

1 Citation (Scopus)

Abstract

The effect of reduced chemistry model on the numerical predictions of supersonic combustion of hydrogen in a model combustor is investigated. To this end, 3D, compressible, turbulent, reacting flow calculation with a reduced chemistry model (with 7 reactions and 7 species) has been carried out. The results are compared with earlier results obtained using the single step chemistry and detailed chemistry model. Staged injection is considered to evaluate the capability of the reduced chemistry model. Predictions of mass fractions of major species, minor species, dimensionless stagnation temperature and combustion efficiency along the combustor length are presented and discussed. Further, dimensionless wall static pressure is compared with experimental data reported in the literature. Results show that the reduced chemistry predicts the overall combustion parameters reasonably well. The heat release is predicted to be lower than that of detailed chemistry model. Also, the flow separation due to heat release is predicted to be shorter with the reduced mechanism. In this work, the difference in predictions of supersonic combustion of hydrogen with different chemistry models are discussed.

Original languageEnglish
Title of host publication47th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition
Publication statusPublished - 2009
Externally publishedYes
Event47th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition - Orlando, FL, United States
Duration: 5 Jan 20098 Jan 2009

Other

Other47th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition
CountryUnited States
CityOrlando, FL
Period5/1/098/1/09

Fingerprint

supersonic combustion
combustion chambers
Combustors
combustion
hydrogen
chemistry
Hydrogen
prediction
predictions
stagnation temperature
combustion efficiency
reacting flow
wall pressure
heat
flow separation
static pressure
comparison
Flow separation
turbulent flow
Turbulent flow

ASJC Scopus subject areas

  • Space and Planetary Science
  • Aerospace Engineering

Cite this

Kannaiyan, K., & Babu, V. (2009). A comparison of numerical predictions of supersonic combustion of hydrogen using different chemistry models in a model combustor. In 47th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition [2009-0716]

A comparison of numerical predictions of supersonic combustion of hydrogen using different chemistry models in a model combustor. / Kannaiyan, Kumaran; Babu, V.

47th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition. 2009. 2009-0716.

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

Kannaiyan, K & Babu, V 2009, A comparison of numerical predictions of supersonic combustion of hydrogen using different chemistry models in a model combustor. in 47th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition., 2009-0716, 47th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition, Orlando, FL, United States, 5/1/09.
Kannaiyan K, Babu V. A comparison of numerical predictions of supersonic combustion of hydrogen using different chemistry models in a model combustor. In 47th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition. 2009. 2009-0716
Kannaiyan, Kumaran ; Babu, V. / A comparison of numerical predictions of supersonic combustion of hydrogen using different chemistry models in a model combustor. 47th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition. 2009.
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