Title

Liquid Fuel Rocket Engine

Presenter Information

Alan Gilje

Document Type

Oral Presentation

Location

SURC Ballroom C/D

Start Date

16-5-2013

End Date

16-5-2013

Abstract

Rocket engines are highly complex and technical propulsion devices that are used to position objects in a different orientation or boost them into the atmosphere. The engine itself is composed of a combustion chamber, a nozzle, a cooling jacket, and an injector. This paper explores the design and manufacture of an effective and safe rocket engine that is capable of producing thrust. This was accomplished with complete heat transfer calculations of a bi-propellant chemical reaction, and properties of a material. Thermodynamic analyses were conducted in order to determine the pressures and pressure losses that occur throughout the engine. Bending and stress analysis was also carried out for the mounting fixture, as well as the thickness of the outer walls and bolt sizes. This paper also details the manufacturing methods and operations that were used during the construction of the engine, which includes but is not limited to: lathe and mill machining and welding. The analysis completed led to correct nozzle and combustion chamber dimensions and sizes, as well as cooling pressures and properties necessary. Key Words: Liquid Fuel Rocket Engine, Bi-Propellant, Thermodynamics, Heat Transfer, Stress Analysis, Fluid Dynamics

Poster Number

10

Faculty Mentor(s)

Charles Pringle

Additional Mentoring Department

Industrial and Engineering Technology

This document is currently not available here.

Share

COinS
 
May 16th, 2:15 PM May 16th, 4:45 PM

Liquid Fuel Rocket Engine

SURC Ballroom C/D

Rocket engines are highly complex and technical propulsion devices that are used to position objects in a different orientation or boost them into the atmosphere. The engine itself is composed of a combustion chamber, a nozzle, a cooling jacket, and an injector. This paper explores the design and manufacture of an effective and safe rocket engine that is capable of producing thrust. This was accomplished with complete heat transfer calculations of a bi-propellant chemical reaction, and properties of a material. Thermodynamic analyses were conducted in order to determine the pressures and pressure losses that occur throughout the engine. Bending and stress analysis was also carried out for the mounting fixture, as well as the thickness of the outer walls and bolt sizes. This paper also details the manufacturing methods and operations that were used during the construction of the engine, which includes but is not limited to: lathe and mill machining and welding. The analysis completed led to correct nozzle and combustion chamber dimensions and sizes, as well as cooling pressures and properties necessary. Key Words: Liquid Fuel Rocket Engine, Bi-Propellant, Thermodynamics, Heat Transfer, Stress Analysis, Fluid Dynamics