NUMERICAL SIMULATION AND EXPERIMENTAL INVESTIGATION OF THRUST PRODUCED BY A HOBBY–SCALE PULSEJET ENGINE
Open Access
- Author:
- Zhu, Mengyao
- Graduate Program:
- Aerospace Engineering
- Degree:
- Master of Science
- Document Type:
- Master Thesis
- Date of Defense:
- July 09, 2015
- Committee Members:
- Michael Matthew Micci, Thesis Advisor/Co-Advisor
Cengiz Camci, Thesis Advisor/Co-Advisor - Keywords:
- pulsejet
lax-wendroff
numerical simulation
experiment
thrust
operating frequency - Abstract:
- The pulsejet is a type of jet engine in which combustion occurs in pulses. It was introduced to the world in the 1860s and the most famous previous application was the “V-1 buzz bomb” during World War II. Because of its high thrust to weight ratio, low cost and simple design, the pulsejet has recently received more research interest, like micro-scale propulsion devices for UAVs, or even large-scale propulsion devices for single stage to orbit Launchers. The objectives of this research include investigating the thrust a hobby scale pulsejet can deliver and its operating frequency, and develop a numerical simulation model for future study. This project investigated pulsejet operation in a combined numerical and experimental approach. The working mechanism of pulsejet engine was studied and a numerical simulation code based on a shock tube model with a quasi-one-dimensional assumption was built using second-order accurate Lax–Wendroff scheme. The code was capable of predicting flow parameters at various locations of the pulsejet engine with different lengths and diameters. A test bed with mounting clamps was manufactured; 10 tests were run on gaseous propane with assistance from an air compressor. The simulation model estimated the 40 cm pulsejet can deliver an average 4.18 N thrust with a 232 Hz operating frequency and the maximum instantaneous thrust was 32N. When the pulsejet was running on different fuel–air equivalence ratios, the working frequency was different. The load-cell was proved to be capable of detecting and recording each combustion events; and the operating frequency could be derived from the thrust data with high accuracy.