Thermal characteristics of an N2O catalytic igniter with metal foam for hybrid rocket motors

“…A previous study [2] suggested that the regression rate was sensitive to the geometries [3][4][5], flight conditions [6], and the fuel types [7][8][9]. The thermodynamic performance of SFRJ, scramjet, and hybrid rockets were extensively investigated and reported in the literature [10][11][12][13][14][15][16][17][18][19][20]. A systematic investigation on a small-scale solid fuel ramjet and the combustion characteristic of boronfueled SFRJ were conducted in the Israel Institute of Technology, via both experimental and numerical approaches [21][22][23][24].…”

Section: Introductionmentioning

confidence: 99%

Numerical Investigation of Inlet Thermodynamic Conditions on Solid Fuel Ramjet Performances

Zhao

Chen

et al. 2021

International Journal of Aerospace Engineering

View full text Add to dashboard Cite

In this work, 2D numerical RANS (Reynolds Average Navier-Stokes) simulations were carried out to investigate the thermodynamic performance of a solid fuel ramjet (SFRJ) with different inlet conditions. This is achieved by using an in-house FORTRAN code to simulate a 2D turbulent, reacting, unsteady flow in the ramjet engine. The inlet conditions are characterized by three key parameters: (1) swirl number ( S N ), (2) mass flow rate ( m ̇ air ), and (3) inlet temperature ( T in ). With the code numerically validated by benchmarking with a number of computed cases, it is applied to perform systematic studies on the turbulent flow recirculation, combustion, and heat transfer characteristics. It is found that increasing S N , m ̇ air , or T in can dramatically enhance the combustion heat release rate, regression rate, and combustor average temperature. Furthermore, the analysis on the chemical reaction intermediate (CO) reveals that the chemical reaction is more sufficient with increased m ̇ air , but S N = 0 . In addition, a secondary vortex is generated at the corner of the backward facing step in the presence of a swirl flow resulting from the instability of the shear layer. Finally, the nonlinear correlations between the heat transfer, combustion characteristics, and flow field characteristics and the corresponding inlet thermodynamic parameters are identified.

show abstract

Ignition of a polymer propellant of hybrid rocket motor by a hot particle

2017

View full text Add to dashboard Cite

Thermal characteristics of an N2O catalytic igniter with metal foam for hybrid rocket motors

Cited by 7 publications

References 13 publications

A study on the unsteady flow characteristics in a vestibule for an injection and pressurization smoke-control system

A study on the unsteady flow characteristics in a vestibule for an injection and pressurization smoke-control system

Numerical Investigation of Inlet Thermodynamic Conditions on Solid Fuel Ramjet Performances

Ignition of a polymer propellant of hybrid rocket motor by a hot particle

Contact Info

Product

Resources

About