Numerical Investigation on Internal Regressing Shapes of Solid-Fuel Scramjet Combustor

Pei, Xin-Yan; Wu, Zhiwen; Wei, Zhijun; Liu, Junyi

doi:10.2514/1.b34681

Cited by 24 publications

(9 citation statements)

References 23 publications

Supporting

Mentioning

Contrasting

Unclassified

Order By: Relevance

“…The numerical results are a little higher than the experiments' because of the simulation conditions of one step reaction mechanism and HTPB pyrolyzation assumption, which overestimate the temperature compared with the experiment and further, as well as the velocity. The detailed introduction of the simulation model and the verification for its reliability has been given in our previous works [16].…”

Section: Code Validationmentioning

confidence: 99%

Numerical investigation on cavity structure of solid-fuel scramjet combustor

Pei

Hou

2014

Acta Astronautica

Self Cite

View full text Add to dashboard Cite

Section: Code Validationmentioning

confidence: 99%

Numerical investigation on cavity structure of solid-fuel scramjet combustor

Pei

Hou

2014

Acta Astronautica

Self Cite

View full text Add to dashboard Cite

“…As fuel regresses, on the basis of the diameter and the fuel regression rate at the former moment, the diameter at the next moment can be worked out. The combustor area differential along the axis at the next moment can then be calculated by equation (14).…”

Section: The Boundary Conditionsmentioning

confidence: 99%

Numerical and Experimental study on the Solid Fuel Scramjet Combustor with a cavity flame holder

Wang¹,

Chi²,

Liu³

et al. 2014

50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference

View full text Add to dashboard Cite

The specific thrust level and variation rule of solid fuel scramjet combustor were researched both by numerical and experimental methods. A methane-burning vitiated air heater was designed and made to simulate flight environment of Mach 6 at 25km altitude. Based on the two dimensional flow field structures, a new quasi-one dimensional numerical method was established. The typical unsteady matter of solid fuel scramjet combustion and flow was transformed into a steady calculation of every moment in this method. And it can be used to simulate the parametric changing process of combustor quickly. Self-ignition and fuel regression rate characteristics in current experiment were consistent with results from previous works. And the agreement between the numerical and experimental results was generally good too. The specific thrust can reach the level of (600 ~ 800) N/kg· s in the designed flight environment. It was found that the specific thrust decrease with the total pressure loss increase during the working process. NomenclatureA = area B = pre-exponential factor of solid fuel pyrolysis c p = specific heat at constant pressure c ps = specific heat of solid fuel d = diameter dA = unit area increments D e = hydraulic diameter f dF = unit friction dm = unit mass increments f dQ = unit heat increments f f = friction coefficient F = thrust h = convective heat transfer coefficient H = flight altitude h g = effective vaporization heat m = mass flow rate Ma = Mach number f Nu = Nusselt number Pr = Prantdtl number p = pressure q = effective combustion heat of solid fuel Q = The low calorific value of solid fuel 1 PhD student, School of Aerospace Engineering, 2 r = fuel regression rate L = perimeter t = combustor working time T f = fluid temperature near the wall T so = initial temperature of solid fuel v = velocity Greek  = dynamic coefficient of viscosity  = heat conductivity coefficient of fluid  = density  = combustion efficiency  = gradient Subscripts a = ground atmospheric environment ground = ground test condition e = at the exit of combustor f = fluid flight = flight environment parameters i = time coordinate point ideal = ideal condition j = axial coordinate point s = solid phase sp = specific w = wall 0 = total parameter

show abstract

“…According to the fuel phase, scramjets are classified into two groups: liquid scramjets using hydrocarbon or hydrogen as fuel and solid scramjets using polymethylmethacrylate or HTPB as fuel. 1 Compared with the liquid fuel scramjet, solid fuel scramjet [2][3][4][5][6][7] has the advantages of simpler structure, higher energy density, lower maintenance cost, and faster reaction.…”

Section: Introductionmentioning

confidence: 99%

Numerical research on the performance of solid fuel rocket scramjet combustor

Huang

Feng

et al. 2021

Proceedings of the Institution of Mechanical Engineers, Part G:

View full text Add to dashboard Cite

Combustion efficiency is the main factor affecting the performance of solid fuel rocket scramjet. To reveal the influence of combustor configuration on performance and further improve combustion efficiency, the influence of the width-height ratio of the rectangle-section combustor on the performance of solid fuel rocket scramjet is investigated numerically in this article. Three-dimensional compressible Reynolds-averaged Navier-Stokes equations coupled with shear stress transport k– ω turbulence model are employed to simulate the aerodynamics. The Euler–Lagrange approach is used to calculate the multiphase flow. Combustion of carbon particles is modeled by the improved Moving Flame Front model. Accuracy of the present numerical model is validated by the experimental data of a rectangle-section combustor from literature. Results show that as the width-height ratio increases, the combustion efficiency increases first and then decreases. The influence of cavity and its position on the performance are also investigated. Results show that cavity can significantly improve combustion efficiency. The effect of cavity position on performance is related to the distribution of particles.

show abstract

Numerical Investigation on Internal Regressing Shapes of Solid-Fuel Scramjet Combustor

Cited by 24 publications

References 23 publications

Numerical investigation on cavity structure of solid-fuel scramjet combustor

Numerical investigation on cavity structure of solid-fuel scramjet combustor

Numerical and Experimental study on the Solid Fuel Scramjet Combustor with a cavity flame holder

Numerical research on the performance of solid fuel rocket scramjet combustor

Contact Info

Product

Resources

About