Flowfield Calculation Coupled with Fuel Surface Regression in Combustion Chamber for Swirling-Oxidizer-Type Hybrid Rocket Engine

2013 ◽  
Author(s):  
Takaya Koda ◽  
Yousuke Ogino ◽  
Keisuke Sawada
Keyword(s):  
Combustion Chamber ◽  
Rocket Engine ◽  
Hybrid Rocket ◽  
Fuel Surface ◽  
Hybrid Rocket Engine

scholarly journals Investigation of Dual-Vortical-Flow Hybrid Rocket Engine without Flame Holding Mechanism

2018 ◽  
Vol 2018 ◽  
pp. 1-13 ◽  
Author(s):  
A. Lai ◽  
T.-H. Chou ◽  
S.-S. Wei ◽  
J.-W. Lin ◽  
J.-S. Wu ◽  
...  
Keyword(s):  
Fire Test ◽  
Fluid Model ◽  
Rocket Engine ◽  
Pressure Oscillation ◽  
Vortical Flow ◽  
Reacting Flow ◽  
Fire Tests ◽  
Hybrid Rocket ◽  
Fuel Surface ◽  
Hybrid Rocket Engine

A 250 kgf thrust hybrid rocket engine was designed, tested, and verified in this work. Due to the injection and flow pattern of this engine, this engine was named dual-vortical-flow engine. This propulsion system uses N2O as oxidizer and HDPE as fuel. This engine was numerically investigated using a CFD tool that can handle reacting flow with finite-rate chemistry and coupled with the real-fluid model. The engine was further verified via a hot-fire test for 12 s. The ground Isp of the engine was 232 s and 221 s for numerical and hot-fire tests, respectively. An oscillation frequency with an order of 100 Hz was observed in both numerical and hot-fire tests with less than 5% of pressure oscillation. Swirling pattern on the fuel surface was also observed in both numerical and hot-fire test, which proves that this swirling dual-vortical-flow engine works exactly as designed. The averaged regression rate of the fuel surface was found to be 0.6~0.8 mm/s at the surface of disk walls and 1.5~1.7 mm/s at the surface of central core of the fuel grain.

Rotational and Quasiviscous Cold Flow Models for Axisymmetric Hybrid Propellant Chambers

2010 ◽  
Vol 132 (10) ◽  
Author(s):  
Joseph Majdalani ◽  
Michel Akiki
Keyword(s):  
Rocket Engine ◽  
Navier Stokes ◽  
Mathematical Treatment ◽  
Hybrid Rocket ◽  
Mean Flow ◽  
Viscous Effects ◽  
Navier Stokes Equation ◽  
Flow Models ◽  
Hybrid Rocket Engine ◽  
Wall Injection

In this work, we present two simple mean flow solutions that mimic the bulk gas motion inside a full-length, cylindrical hybrid rocket engine. Two distinct methods are used. The first is based on steady, axisymmetric, rotational, and incompressible flow conditions. It leads to an Eulerian solution that observes the normal sidewall mass injection condition while assuming a sinusoidal injection profile at the head end wall. The second approach constitutes a slight improvement over the first in its inclusion of viscous effects. At the outset, a first order viscous approximation is constructed using regular perturbations in the reciprocal of the wall injection Reynolds number. The asymptotic approximation is derived from a general similarity reduced Navier–Stokes equation for a viscous tube with regressing porous walls. It is then compared and shown to agree remarkably well with two existing solutions. The resulting formulations enable us to model the streamtubes observed in conventional hybrid engines in which the parallel motion of gaseous oxidizer is coupled with the cross-streamwise (i.e., sidewall) addition of solid fuel. Furthermore, estimates for pressure, velocity, and vorticity distributions in the simulated engine are provided in closed form. Our idealized hybrid engine is modeled as a porous circular-port chamber with head end injection. The mathematical treatment is based on a standard similarity approach that is tailored to permit sinusoidal injection at the head end.

Optimization of a H2O2 Gas Generator for a Hybrid Rocket Engine

2013 ◽  
Author(s):  
Martina Faenza ◽  
Federico Moretto ◽  
Alberto Bettella ◽  
Daniele Pavarin
Keyword(s):  
Rocket Engine ◽  
Hybrid Rocket ◽  
Gas Generator ◽  
Hybrid Rocket Engine
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