Tip-to-tail numerical simulation of a hypersonic air-breathing engine with ethylene fuel. (November 2016)

• Record Type: Journal Article
• Authors: Dharavath, Malsur; Manna, P.; Chakraborty, Debasis
• Is Part Of: Acta astronautica. Volume 128(2016)
• Page Start: 107
• Page End: 118
• Publication Date: 2016-11
• Subjects: Reacting flow -- Scramjet -- Hypersonic vehicle -- CFD -- Combustion efficiency; Astronautics -- Periodicals; Outer space -- Exploration -- Periodicals; Astronautics; Periodicals; 629.405
• DOI: 10.1016/j.actaastro.2016.07.014
• Languages: English
• ISSNs: 0094-5765

Abstract

Abstract: End to end CFD simulations of external and internal flow paths of an ethylene fueled hypersonic airbreathing vehicle with including forebody, horizontal fins, vertical fins, intake, combustor, single expansion ramp nozzle are carried out. The performance of the scramjet combustor and vehicle net thrust-drag is calculated for hypersonic cruise condition. Three-dimensional Navier–Stokes equations are solved along with SST-k–ω turbulence model using the commercial CFD software CFX-14 . Single step chemical reaction based on fast chemistry assumption is used for combustion of gaseous ethylene fuel. Simulations captured complex shock structures including the shocks generated from the vehicle nose and compression ramps, impingement of cowl-shock on vehicle undersurface and its reflection in the intake and combustor etc. Various thermochemical parameters are analyzed and performance parameters are evaluated for nonreacting and reacting cases. Very good mixing (~98%) of fuel with incoming air stream is observed. Positive thrust–drag margins are obtained for fuel equivalence ratio of 0.6 and computed combustion efficiency is observed to be 94 %. Effect of equivalence ratio on the vehicle performance is studied parametrically. Though the combustion efficiency has come down by 8% for fuel equivalence ratio of 0.8, net vehicle thrust is increased by 44%. Heat flux distribution on the various walls of the whole vehicle including combustor is estimated for the isothermal wall condition of 1000 K in reacting flow. Higher local heat flux values are observed at all the leading edges of the vehicle (i.e., nose, wing, fin and cowl leading edges) and strut regions of the combustor. Highlights: Ethylene fueled hypersonic airbreathing vehicle is explored using end to end CFD. 3D RANS equations are solved with SST- kω turbulence model and EDC combustion model. Parametric studies performed for fuel equivalence ratio. Positive thrust–drag margins obtained. Convective heat flux rates are estimated for all vehicle surfaces.