Analysis of hydrogen injection into the combustor of HyShot-II scramjet engine using ILES

Z.A. Rana, B.J.R. Thornber, D. Drikakis

Research output: Contribution to conferencePaper

Abstract

This paper presents the application of a Finite Volume Godunov-type implicit large eddy simulation method to study fuel injection into the combustion chamber of HyShot-II scramjet engine without combustion. Such a flow is generally termed as transverse jet injection into supersonic cross-flow. The HyShot-II experiment was successfully carried out at the UoQ, Australia. Subsequently, wind tunnel tests were carried out for the HyShot-II geometry for the conditions representing the Mach number of 7.4 at an altitude between 27 km and 35 km at the German Aerospace Centre (DLR). This study is carried out in two parts; part one presented full HyShot-II geometry in 2D in order to obtain the combustion chamber inlet conditions using the real gas effects, which are then utilised in part two where three-dimensional combustion chamber simulations are carried out using the inlet conditions obtained earlier along with hydrogen injection but without combustion. Supersonic turbulent boundary layer in the free-stream is an important aspect of such a flow which has been implemented using a digital filter based turbulent inflow data generator. The purpose of the study is to understand the flow physics and air & fuel mixing inside the HyShot-II scramjet geometry which is vital at the design stages. The work presented analyses the sonic circular hydrogen jet emerging into and mixing with a free-stream turbulent supersonic air flow. The flow physics is investigated for various flow features such as the Mach number, velocity, pressure distributions, counter rotating vortices, horse-shoe vortices, jet penetration & mixing

Conference

Conference49th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition, 2011
CountryUnited States
CityOrlando, FL
Period4/01/117/01/11

Fingerprint

Scramjet
Combustion chambers
Combustors
Hydrogen
Injection
Engine
Combustion
Engines
Mach number
Geometry
Vortex flow
Physics
Fuel injection
Large eddy simulation
Digital filters
Air
Pressure distribution
Wind tunnels
Vortex
Boundary layers

Keywords

  • combustion
  • aerospace engineering
  • combustion chambers
  • digital filters
  • fuel injection
  • supersonic aerodynamics
  • vortex flow
  • implicit large eddy simulations
  • hydrogen jets

Cite this

Rana, Z. A., Thornber, B. J. R., & Drikakis, D. (2011). Analysis of hydrogen injection into the combustor of HyShot-II scramjet engine using ILES. 1-20. Paper presented at 49th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition, 2011, Orlando, FL, United States.
Rana, Z.A. ; Thornber, B.J.R. ; Drikakis, D. / Analysis of hydrogen injection into the combustor of HyShot-II scramjet engine using ILES. Paper presented at 49th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition, 2011, Orlando, FL, United States.20 p.
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abstract = "This paper presents the application of a Finite Volume Godunov-type implicit large eddy simulation method to study fuel injection into the combustion chamber of HyShot-II scramjet engine without combustion. Such a flow is generally termed as transverse jet injection into supersonic cross-flow. The HyShot-II experiment was successfully carried out at the UoQ, Australia. Subsequently, wind tunnel tests were carried out for the HyShot-II geometry for the conditions representing the Mach number of 7.4 at an altitude between 27 km and 35 km at the German Aerospace Centre (DLR). This study is carried out in two parts; part one presented full HyShot-II geometry in 2D in order to obtain the combustion chamber inlet conditions using the real gas effects, which are then utilised in part two where three-dimensional combustion chamber simulations are carried out using the inlet conditions obtained earlier along with hydrogen injection but without combustion. Supersonic turbulent boundary layer in the free-stream is an important aspect of such a flow which has been implemented using a digital filter based turbulent inflow data generator. The purpose of the study is to understand the flow physics and air & fuel mixing inside the HyShot-II scramjet geometry which is vital at the design stages. The work presented analyses the sonic circular hydrogen jet emerging into and mixing with a free-stream turbulent supersonic air flow. The flow physics is investigated for various flow features such as the Mach number, velocity, pressure distributions, counter rotating vortices, horse-shoe vortices, jet penetration & mixing",
keywords = "combustion, aerospace engineering, combustion chambers, digital filters , fuel injection, supersonic aerodynamics, vortex flow, implicit large eddy simulations, hydrogen jets",
author = "Z.A. Rana and B.J.R. Thornber and D. Drikakis",
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Rana, ZA, Thornber, BJR & Drikakis, D 2011, 'Analysis of hydrogen injection into the combustor of HyShot-II scramjet engine using ILES' Paper presented at 49th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition, 2011, Orlando, FL, United States, 4/01/11 - 7/01/11, pp. 1-20.

Analysis of hydrogen injection into the combustor of HyShot-II scramjet engine using ILES. / Rana, Z.A.; Thornber, B.J.R.; Drikakis, D.

2011. 1-20 Paper presented at 49th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition, 2011, Orlando, FL, United States.

Research output: Contribution to conferencePaper

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AU - Thornber, B.J.R.

AU - Drikakis, D.

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N2 - This paper presents the application of a Finite Volume Godunov-type implicit large eddy simulation method to study fuel injection into the combustion chamber of HyShot-II scramjet engine without combustion. Such a flow is generally termed as transverse jet injection into supersonic cross-flow. The HyShot-II experiment was successfully carried out at the UoQ, Australia. Subsequently, wind tunnel tests were carried out for the HyShot-II geometry for the conditions representing the Mach number of 7.4 at an altitude between 27 km and 35 km at the German Aerospace Centre (DLR). This study is carried out in two parts; part one presented full HyShot-II geometry in 2D in order to obtain the combustion chamber inlet conditions using the real gas effects, which are then utilised in part two where three-dimensional combustion chamber simulations are carried out using the inlet conditions obtained earlier along with hydrogen injection but without combustion. Supersonic turbulent boundary layer in the free-stream is an important aspect of such a flow which has been implemented using a digital filter based turbulent inflow data generator. The purpose of the study is to understand the flow physics and air & fuel mixing inside the HyShot-II scramjet geometry which is vital at the design stages. The work presented analyses the sonic circular hydrogen jet emerging into and mixing with a free-stream turbulent supersonic air flow. The flow physics is investigated for various flow features such as the Mach number, velocity, pressure distributions, counter rotating vortices, horse-shoe vortices, jet penetration & mixing

AB - This paper presents the application of a Finite Volume Godunov-type implicit large eddy simulation method to study fuel injection into the combustion chamber of HyShot-II scramjet engine without combustion. Such a flow is generally termed as transverse jet injection into supersonic cross-flow. The HyShot-II experiment was successfully carried out at the UoQ, Australia. Subsequently, wind tunnel tests were carried out for the HyShot-II geometry for the conditions representing the Mach number of 7.4 at an altitude between 27 km and 35 km at the German Aerospace Centre (DLR). This study is carried out in two parts; part one presented full HyShot-II geometry in 2D in order to obtain the combustion chamber inlet conditions using the real gas effects, which are then utilised in part two where three-dimensional combustion chamber simulations are carried out using the inlet conditions obtained earlier along with hydrogen injection but without combustion. Supersonic turbulent boundary layer in the free-stream is an important aspect of such a flow which has been implemented using a digital filter based turbulent inflow data generator. The purpose of the study is to understand the flow physics and air & fuel mixing inside the HyShot-II scramjet geometry which is vital at the design stages. The work presented analyses the sonic circular hydrogen jet emerging into and mixing with a free-stream turbulent supersonic air flow. The flow physics is investigated for various flow features such as the Mach number, velocity, pressure distributions, counter rotating vortices, horse-shoe vortices, jet penetration & mixing

KW - combustion

KW - aerospace engineering

KW - combustion chambers

KW - digital filters

KW - fuel injection

KW - supersonic aerodynamics

KW - vortex flow

KW - implicit large eddy simulations

KW - hydrogen jets

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M3 - Paper

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ER -

Rana ZA, Thornber BJR, Drikakis D. Analysis of hydrogen injection into the combustor of HyShot-II scramjet engine using ILES. 2011. Paper presented at 49th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition, 2011, Orlando, FL, United States.