Development of a Kerosene and Liquid Oxygen Gas Generator
Faculty Mentor Name
Andy Gerrick
Format Preference
Poster
Abstract
Gas generators are a critical subcomponent of turbopump systems, which are required to power large rocket engines. Low-thrust rocket engines (typically under 5,000 lbf) often use a blowdown feed system, in which high-pressure inert gases such as nitrogen or helium are used to pressurize the propellant tanks and drive propellant injection into the combustion chamber. While this approach is simple and effective for small engines and tank volumes, it becomes increasingly heavy and technically limiting as engine thrust and propellant tank size increase. For larger engines, turbopumps provide substantial mass savings at the cost of significantly increased system complexity. A turbopump consists of pumps driven by a turbine to raise the pressure of the propellants prior to injection. Gas generators supply the high-energy gas flow needed to drive this turbine, typically by combusting the same propellants used by the main engine.
Although gas generators share many similarities with rocket engines, they present a unique set of technical challenges beyond those encountered in conventional combustion chambers. Because the gas generator is located upstream of the turbine, it requires superior propellant mixing and uniform combustion products compared to a main engine. In addition, turbine material constraints require the combustion gases to be at significantly lower temperatures, which necessitates operation at extreme oxidizer-to-fuel ratios.
The Janus R engine a 3,000 lbf kerosene and liquid oxygen rocket engine designed by Embry-Riddle Aeronautical University students was used to establish the requirements for the preliminary design of a small turbopump. From these requirements, the design criteria for a kerosene and liquid oxygen gas generator were derived. The manufacturing and testing campaign for this gas generator is scheduled to take place during the current semester.
Development of a Kerosene and Liquid Oxygen Gas Generator
Gas generators are a critical subcomponent of turbopump systems, which are required to power large rocket engines. Low-thrust rocket engines (typically under 5,000 lbf) often use a blowdown feed system, in which high-pressure inert gases such as nitrogen or helium are used to pressurize the propellant tanks and drive propellant injection into the combustion chamber. While this approach is simple and effective for small engines and tank volumes, it becomes increasingly heavy and technically limiting as engine thrust and propellant tank size increase. For larger engines, turbopumps provide substantial mass savings at the cost of significantly increased system complexity. A turbopump consists of pumps driven by a turbine to raise the pressure of the propellants prior to injection. Gas generators supply the high-energy gas flow needed to drive this turbine, typically by combusting the same propellants used by the main engine.
Although gas generators share many similarities with rocket engines, they present a unique set of technical challenges beyond those encountered in conventional combustion chambers. Because the gas generator is located upstream of the turbine, it requires superior propellant mixing and uniform combustion products compared to a main engine. In addition, turbine material constraints require the combustion gases to be at significantly lower temperatures, which necessitates operation at extreme oxidizer-to-fuel ratios.
The Janus R engine a 3,000 lbf kerosene and liquid oxygen rocket engine designed by Embry-Riddle Aeronautical University students was used to establish the requirements for the preliminary design of a small turbopump. From these requirements, the design criteria for a kerosene and liquid oxygen gas generator were derived. The manufacturing and testing campaign for this gas generator is scheduled to take place during the current semester.