Library Subscription: Guest
Begell Digital Portal Begell Digital Library eBooks Journals References & Proceedings Research Collections
International Journal of Energetic Materials and Chemical Propulsion
ESCI SJR: 0.149 SNIP: 0.16 CiteScore™: 0.29

ISSN Print: 2150-766X
ISSN Online: 2150-7678

International Journal of Energetic Materials and Chemical Propulsion

DOI: 10.1615/IntJEnergeticMaterialsChemProp.v5.i1-6.140
pages 101-115

SURFACE HEAT RELEASE OF HTPB-BASED FUELS IN OXYGEN RICH ENVIRONMENTS

Grant A. Risha
The Pennsylvania State University-Altoona, Altoona, Pennsylvania 16601, USA
George C. Harting
Department of Mechanical and Nuclear Engineering, The Pennsylvania State University, University Park, PA 16802, USA
Arie Peretz
Rafael Ltd., Haifa, Israel
Donald E. Koch
Department of Mechanical and Nuclear Engineering, The Pennsylvania State University, University Park, PA 16802, USA
H. Stephen Jones
Lockheed Martin Michoud Space Systems, New Orleans, LA 70189, USA
Joseph P. Arves
Lockheed Martin Michoud Space Systems, New Orleans, LA 70189, USA

ABSTRACT

An experimental study was conducted to determine the dependence of the regression rate of two solid-fuel formulations (cured HTPB and JIRAD fuel) on operating conditions near the head-end of a hybrid motor. Cylindrical fuel samples were burned in a windowed combustor at pressures ranging from 0.79 to 3.55 MPa. The burning was sustained by a diffusion flame created over the fuel surface by an impinging oxidizer jet. The gaseous oxidizer, delivered at an initial temperature between 220 to 298 K, was a mixture of oxygen and nitrogen, with the oxygen mass fraction ranging from 0.21 to 1.00. For both fuels, the regression rate increased with oxidizer mass flow rate, oxygen mass fraction, and oxidizer temperature, but decreased at higher pressures in the range tested. Measured regression rates, surface temperatures, and operating parameters were used to validate a simple power-law regression rate correlation for each fuel. The heats of decomposition of these solid fuels were determined from a fast thermolysis study using a gas chromatograph/mass spectrometer equipped with a pyrolyzer. The pyrolysis activation energy of HTPB was lower than that of JIRAD fuel. Therefore, HTPB is more reactive. Additionally, the amount of surface heat release was found to decrease with increasing solid fuel regression rate for both fuels, which suggests that higher blowing rates reduce the amount of oxygen available for reaction at the surface. The surface heat release for each fuel was correlated using a power law expression.


Articles with similar content:

GLYCIDYL AZIDE POLYMER−COMBUSTION MECHANISM AND ITS APPLICATION TO HYBRID ROCKET MOTORS
International Journal of Energetic Materials and Chemical Propulsion, Vol.11, 2012, issue 4
Makihito Nishioka, Keiichi Hori
GAP DISTANCE EFFECT ON BURNING RATE OF TWO OPPOSING JA2 PROPELLANT GRAINS
International Journal of Energetic Materials and Chemical Propulsion, Vol.6, 2007, issue 6
Peter J. Ferrara
CHARACTERIZATION OF NOZZLE EROSION BEHAVIOR UNDER ROCKET MOTOR OPERATING CONDITIONS
International Journal of Energetic Materials and Chemical Propulsion, Vol.9, 2010, issue 6
Brian Evans, Kenneth K. Kuo, Andrew C. Cortopassi
COMBUSTION OF BIMODAL ALUMINUM PARTICLES AND ICE MIXTURES
International Journal of Energetic Materials and Chemical Propulsion, Vol.11, 2012, issue 3
Steven F. Son, Grant A. Risha, Vigor Yang, Terrence L. Connell, Jr., Richard A. Yetter
INVESTIGATION OF SOLID OXIDIZER AND GASEOUS FUEL COMBUSTION PERFORMANCE USING AN ELEVATED PRESSURE COUNTERFLOW EXPERIMENT FOR REVERSE HYBRID ROCKET ENGINE
International Journal of Energetic Materials and Chemical Propulsion, Vol.11, 2012, issue 6
Grant A. Risha, Terrence L. Connell, Jr., Reed H. Johansson, Gregory Young, Richard A. Yetter