scholarly journals Theoretical and Experimental Heat of Combustion Analysis of Paraffin-Based Fuels as Preburn Characterization for Hybrid Rocket

2020 ◽  
Author(s):  
Yash Pal ◽  
Anthony Raja ◽  
Kavitha Gopalakrishnan
Keyword(s):  
Specific Impulse ◽  
Flame Temperature ◽  
Heat Of Combustion ◽  
Test Results ◽  
Hybrid Rocket ◽  
Bomb Calorimetry ◽  
Energy Characteristics ◽  
Experimental Heat ◽  
Fuel Formulation ◽  
Theoretical Performance

The energy characteristics and theoretical performance of the hybrid rocket fuels are discussed in this paper. Aluminum (Al) and boron (B) metal additives were used to increase the energy density of the paraffin-based solid fuels. To predict the energy characteristics, the heat of combustion was evaluated by adiabatic bomb calorimetry. Theoretical performance parameters such as specific impulse (Isp), flame temperature, and characteristic velocity were obtained with NASA Chemical Equilibrium with Applications (CEA) code. Calorimetric test results revealed that paraffin/polyethylene/boron (P/PE/B)-based fuel formulations exhibited the highest heat of combustion among all the tested fuels. The heat of combustion value of the P/PE/B sample at 25 wt% B loading was found to be 9612 ±16 cal/g and 9293±17 cal/g for the P/PE/Al fuel formulation. The CEA results showed that the addition of Al to paraffin is noneffective in improving specific impulse performance. When B loading increased from 5 to 25 wt% in the P/PE/B, the Isp increased by 47 s compared to pure paraffin. A specific impulse increase implies the possible propellant mass saving. The reduction of the oxidizer and fuel masses may yield increased payload performance for given boundary conditions. The P/PE/B25 formulation has reported the highest value of characteristics velocity (C*) compared to other paraffin-based formulation.

An analytical and experimental study of a hybrid rocket motor

2014 ◽  
Vol 228 (13) ◽  
pp. 2475-2486 ◽  
Author(s):  
Hadi Rezaei ◽  
Mohammad Reza Soltani
Keyword(s):  
Flow Rate ◽  
Low Cost ◽  
Specific Impulse ◽  
Combustion Products ◽  
Rocket Motor ◽  
Chamber Pressure ◽  
Hybrid Rocket ◽  
Hybrid Rocket Motor ◽  
Chemical Propulsion ◽  
Rate Case

The hybrid rocket motor is a kind of chemical propulsion system that has been recently given serious attention by various industries and research centers. The relative simplicity, safety and low cost of this motor, in comparison with other chemical propulsion motors, are the most important reasons for such interest. Moreover, throttle-ability and thrust variability on demand are additional advantages of this type of motor. In this paper, the result of an internal ballistic simulation of hybrid rocket motor in a zero-dimensional form is presented. Further to validate the code, an experimental setup was designed and manufactured. The simulation results are compared with the experimental data and good agreement is achieved. The effect of various parameters on the motor performance and on the combustion products is also investigated. It is found that increasing the oxidizer flow rate, increases the pressure and specific impulse of the motor; however, the slope of the specific impulse for the high flow rate case reduces. In addition, by increasing the combustion chamber pressure, the specific impulse is increased considerably. The initial diameter of the fuel port does not have significant effect on the pressure chamber and on the specific impulse. Addition of a percentage of an oxidizer like ammonium perchlorate to the fuel increases the specific impulse linearly.

scholarly journals Metals and Alloys Additives as Enhancer for Rocket Propulsion: A Review

2021 ◽  
Vol 90 (1) ◽  
pp. 1-9
Author(s):  
Izham Izzat Ismail ◽  
Norhuda Hidayah Nordin ◽  
Muhammad Hanafi Azami ◽  
Nur Azam Abdullah
Keyword(s):  
Specific Impulse ◽  
Flame Temperature ◽  
High Energy ◽  
Combustion Efficiency ◽  
High Energy Density ◽  
Regression Rate ◽  
High Entropy ◽  
Rocket Propulsion ◽  
Wide Range ◽  
Metal Additives

A rocket's engine usually uses fuel and oxygen as propellants to increase the rocket's projection during launch. Nowadays, metallic ingredients are commonly used in the rocket’s operation to increase its performance. Metallic ingredients have a high energy density, flame temperature, and regression rate that are important factors in the propulsion process. There is a wide range of additives have been reported so far as catalysts for rocket propulsion. The studies show that the presence of metal additives improves the regression rate, specific impulse and combustion efficiency. Herein, the common energetic additives for rocket propulsion such as metal and light metals are reviewed. Besides the effect of these energetic particles on the regression behaviors of base (hybrid) fuel has been exclusively discussed. This paper also proposed a new alloy namely high entropy alloys (HEAs) as a new energetic additive that can potentially increase the performance of the rocket propellant system.

Design and Testing of a Lab-Scale Hybrid Rocket Motor to Evaluate Swirl Injection Characteristics

2018 ◽  
pp. 185-210
Author(s):  
Susane R. Gomes ◽  
Leopoldo J. Rocco
Keyword(s):  
Swirling Flow ◽  
Specific Impulse ◽  
Operating Conditions ◽  
Geometrical Parameters ◽  
Operating Pressure ◽  
Hybrid Rocket ◽  
Rocket Motors ◽  
Mathematical Background ◽  
Design And Testing ◽  
Firing Tests

This research aims to provide a methodology for the project of labscale hybrid motors. This development began with the thermal analysis of the fuel grain using the Flynn, Wall and Ozawa method, generating simulation entry data to maximize the motor performance. The simulation was performed with the Chemical Equilibrium Specific Impulse Code. Based on the optimum oxidizer to fuel ratio, the literature was used to supply the mathematical background to calculate the motor geometrical parameters whose operating conditions were determined throughout the simulation. Finally, firing tests were conducted to verify the reliability of the project methodology. The firing tests were performed with three injectors: two swirling and one axial. The tests showed that the higher the operating pressure the more suitable is the project, meaning the methodology developed works best in hybrid rocket motors with high operating pressures. Additionally, it was shown that the swirling flow injectors produce higher efficiency.

scholarly journals Theoretical Performance Evaluation of a Marine Solid Propellant Water-Breathing Ramjet Propulsor

2019 ◽  
Vol 8 (1) ◽  
pp. 8 ◽  
Author(s):  
Nachum E. Eisen ◽  
Alon Gany
Keyword(s):  
Performance Evaluation ◽  
Ammonium Perchlorate ◽  
Solid Propellant ◽  
Specific Impulse ◽  
Marine Water ◽  
Metal Particles ◽  
Conceptual Scheme ◽  
Thrust Coefficient ◽  
Theoretical Results ◽  
Theoretical Performance

This work analyzes and presents theoretical performance of a marine water-breathing ramjet propulsor. A conceptual scheme of the motor is shown, the equation of thrust is presented, and the dependence on cruise velocity and depth are discussed. Different propellant compositions, representing a wide variety of formulations suitable for propelling a water-breathing ramjet, are investigated. The theoretical results reveal that the specific impulse of a water-breathing ramjet can increase by as much as 30% compared to a standard rocket, when using a conventional hydroxyl terminated polybutadiene (HTPB)-ammonium perchlorate (AP) propellant, which does not react chemically with the water. When employing a water-reactive propellant containing metal particles such as magnesium or aluminum, the specific impulse may be more than doubled. The thrust coefficient of the propulsor was computed at different cruise velocities and depths and was found to be greater than the predictable drag even at significant depth.

Advanced cryogenic solid hybrid rocket engine developments - Concept and test results

1998 ◽  
Author(s):  
Christopher St. Clair ◽  
Daniel Gramer ◽  
Eric Rice ◽  
William Knuth
Keyword(s):  
Rocket Engine ◽  
Test Results ◽  
Hybrid Rocket ◽  
Hybrid Rocket Engine

Full Scale Testing of a Low Swirl Fuel Injector Concept for Ultra-Low NOx Gas Turbine Combustion Systems

2006 ◽  
Author(s):  
Waseem Nazeer ◽  
Kenneth Smith ◽  
Patrick Sheppard ◽  
Robert Cheng ◽  
David Littlejohn
Keyword(s):  
Natural Gas ◽  
Gas Turbine ◽  
Flame Temperature ◽  
Pressure Oscillation ◽  
Test Results ◽  
Combustion System ◽  
Fuel Injector ◽  
Annular Combustor ◽  
Swirl Injector ◽  
Gas Turbine Combustion

The continued development of a low swirl injector for ultra-low NOx gas turbine applications is described. An injector prototype for natural gas operation has been designed, fabricated and tested. The target application is an annular gas turbine combustion system requiring twelve injectors. High pressure rig test results for a single injector prototype are presented. On natural gas, ultra-low NOx emissions were achieved along with low CO. A turndown of approximately 100°F in flame temperature was possible before CO emissions increased significantly. Subsequently, a set of injectors was evaluated at atmospheric pressure using a production annular combustor. Rig testing again demonstrated the ultra-low NOx capability of the injectors on natural gas. An engine test of the injectors will be required to establish the transient performance of the combustion system and to assess any combustor pressure oscillation issues.

Peregrine Hybrid Rocket Motor Ground Test Results

2012 ◽  
Author(s):  
Greg Zilliac ◽  
Benjamin Waxman ◽  
Eric Doran ◽  
Jonathan Dyer ◽  
Arif Karabeyoglu ◽  
...  
Keyword(s):  
Rocket Motor ◽  
Test Results ◽  
Hybrid Rocket ◽  
Hybrid Rocket Motor ◽  
Ground Test

Prediction of Combustion Efficiency and NOx Levels for Diffusion Flame Combustors in HAT Cycles

2002 ◽  
Author(s):  
Alexandr A. Belokon ◽  
Konstantin M. Khritov ◽  
Lev A. Klyachko ◽  
Sergey A. Tschepin ◽  
Vladimir M. Zakharov ◽  
...  
Keyword(s):  
Diffusion Flame ◽  
Atmospheric Pressure ◽  
Flame Temperature ◽  
Combustion Efficiency ◽  
Inlet Temperature ◽  
Preliminary Design ◽  
Test Results ◽  
Loading Parameter ◽  
Design Analyses ◽  
The Impact

Diffusion flame combustor test results are presented for methane firing in steam/air mixtures containing up to 20% steam. The tests were conducted at atmospheric pressure with combustor inlet temperatures up to 700K. Steam and air were fully premixed before combustion. Combustion efficiency and NOX levels were measured. The well-known Θ loading parameter was modified by replacing the combustor inlet temperature with the flame temperature. The flame temperature was defined as the stoichiometric temperature of the steam/air mixture. The combustion efficiency obtained with and without steam correlated nicely with this modified loading parameter. Calculated NOX levels agreed well with the measurements, where NOX was predicted using the flamelet technique. This approach makes it possible to predict combustor efficiencies with steam by using combustor performance data taken without steam. Preliminary design analyses of gas turbine cycles with significant steam addition can now easily include the impact of the steam on combustor performance.

Characteristics of NEPE Propellant with Ammonium Dinitramide (ADN)

2011 ◽  
Vol 399-401 ◽  
pp. 279-283
Author(s):  
Wei Qiang Pang ◽  
Hui Xiang Xu ◽  
Yang Li ◽  
Xiao Bing Shi
Keyword(s):  
Thermal Decomposition ◽  
Specific Impulse ◽  
Flame Temperature ◽  
Minimum Free Energy ◽  
Ammonium Dinitramide ◽  
Mechanical Sensitivity ◽  
Nitrate Ester ◽  
Nickel Chromium ◽  
Wire Method ◽  
Nepe Propellant

The theoretical performances of NEPE (nitrate ester plasticized polyether) propellant with and without ADN were calculated with minimum free energy method. The burning characteristics and the thermal decomposition of propellants were determined by nickel chromium wire method and TG- DTG, respectively. The SEM of NEPE propellants and the mechanical sensitivity were also detected. The results show that the specific impulse and the adiabatic flame temperature are increase with an increase in the content of ADN oxidizer. The burning rate and pressure exponent of propellant with a change of pat content of ADN can be boosted higher than those of the AP formulations.

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