Washington State University Liquid Fuel Rocket Engine€¦ · Another rocket team called Smart...
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Washington State University Liquid Fuel Rocket Engine Why build a rocket? We sought out to design a low cost, time constrained, Liquid Fuel rocket. We are a team of undergraduate students with no prior experience in propulsion design. What is an injector? Injectors focus streams of fuel and oxidizer to allow them to mix and create an atomized cloud in the combustion chamber. Why is it important? The design of the injectors influence the mass flow rate and mixture ratio of fuel and oxidizer into the engine. The volume, pressure, and temperature of the combustion chamber is influenced by the injector design. Why Design Analysis? We the assumed flight parameters to help determine the design parameters of our rocket. What Program was used? A program called EES (which stands for Engineering Equation Solver) was used in determining the parameters. What Parameters were determined? The mass flow rate of our rocket, Thrust, volume flow rate of ethanol, and volume flow rate of LOX. What other resources helped? Another rocket team called Smart Rockets based out of the University of Dresden, Germany, a rocket project referred to as “Robert’s Rocket project” and the text used for the class called Sutton’s Rocket Propulsion Elements 8th Edition and Modern Engineering for Design of Liquid- Propellant Rocket Engines. First Low Pressure Test The low pressure test was done to test the design of our injectors. What is low pressure? Pressures around 100 psi is where we tested at and it ended up being a very successful test. What’s next? The high pressure test, which will be in the pressure of about 500 psi. Ideas for our combustion chamber: - Regenerative cooling with ethanol - Tubular cooling jacket - Transportation cooling in nozzle region -Wall thickness -Thin walled pressure vessel -Heat transfer rate Ethanol And Liquid Oxygen (LOX) were selected for our fuel and oxidizer respectively. Why Ethanol and LOX? These were selected to enable the design of a low cost and quick to build engine. These were also selected because of the availability of knowledge on engines using the same propellant combinations including the V2 rocket. Franco Spadoni, Marshall Crenshaw, David Nguyen, Lucas Verge, Kevin Cavender, Andrew Doornik, Mario Reillo, David Estrada, Matt Will, Den Donahou, John Feiler, Zach Hein, Justin Stanton, Conner McBride, and Mack Bailey A Liquid fuel rocket engine where the fuel and oxidizer are forced into the combustion chamber by a compressed inert gas. Our system uses Helium gas compressed to 20 MPa to feed Ethanol fuel and liquid Oxygen oxidizer into the injector plate. Our injector is an unlike pentad model where 4 fuel streams impinge on a central oxidizer stream. System Diagram of the Rocket What drove us? Propellant Selection Our Injector Design Analysis Model Chamber/Nozzle Why a Pentad Injector?
Transcript of Washington State University Liquid Fuel Rocket Engine€¦ · Another rocket team called Smart...
Washington State UniversityLiquid Fuel Rocket Engine
Why build a rocket?We sought out to design a low cost, time constrained, Liquid Fuel rocket. We are a team of undergraduate students with no prior experience in propulsion design.
What is an injector?Injectors focus streams of fuel and oxidizer to allow them to mix and create an atomized cloud in the combustion chamber. Why is it important?The design of the injectors influence the mass flow rate and mixture ratio of fuel and oxidizer into the engine. The volume, pressure, and temperature of the combustion chamber is influenced by the injector design.
Why Design Analysis? We the assumed flight parameters to help determine the design parameters of our rocket.
What Program was used?A program called EES (which stands for Engineering Equation Solver) was used in determining the parameters.
What Parameters were determined?The mass flow rate of our rocket, Thrust, volume flow rate of ethanol, and volume flow rate of LOX.
What other resources helped?Another rocket team called Smart Rockets based out of the University of Dresden, Germany, a rocket project referred to as “Robert’s Rocket project” and the text used for the class called Sutton’s Rocket Propulsion Elements 8th Edition and Modern Engineering for Design of Liquid-Propellant Rocket Engines.
First Low Pressure TestThe low pressure test was done to test the design of our injectors. What is low pressure? Pressures around 100 psi is where we tested at and it ended up being a very successful test. What’s next?The high pressure test, which will be in the pressure of about 500 psi.
Ideas for our combustion chamber:- Regenerative cooling with ethanol- Tubular cooling jacket- Transportation cooling in nozzle region-Wall thickness-Thin walled pressure vessel-Heat transfer rate
Ethanol And Liquid Oxygen (LOX) were selected for our fuel and oxidizer respectively.
Why Ethanol and LOX?These were selected to enable the design of a low cost and quick to build engine. These were also selected because of the availability of knowledge on engines using the same propellant combinations including the V2 rocket.
Franco Spadoni, Marshall Crenshaw, David Nguyen, Lucas Verge, Kevin Cavender, Andrew Doornik, Mario Reillo, David Estrada, Matt Will, Den Donahou, John Feiler, Zach Hein, Justin Stanton, Conner McBride, and Mack Bailey
A Liquid fuel rocket engine where the fuel and oxidizer are forced into the combustion chamber
by a compressed inert gas. Our system uses Helium gas compressed to 20 MPa to feed
Ethanol fuel and liquid Oxygen oxidizer into the injector plate. Our injector is an unlike pentad
model where 4 fuel streams impinge on a central oxidizer stream.
System Diagram of the Rocket
What drove us?
Propellant Selection
Our Injector
Design Analysis Model
Chamber/Nozzle
Why a Pentad Injector?
