Date of Award
4-2004
Degree Name
Master of Science in Engineering
Department
Mechanical and Aerospace Engineering
Department
Mechanical and Aeronautical Engineering
First Advisor
Dr. Richard B. Hathaway
Second Advisor
Dr. Jerry Hamelink
Third Advisor
Dr. Bade Shrestha
Access Setting
Masters Thesis-Open Access
Abstract
This research entails examining the Hopkins Rotor Mechanism (HRM) for the perspective of commercial viability. Factors that were studied herein include basic operating characteristics, combustion effects, dimensional changes and behaviors unique to the HRM that may impose limits to commercial viability were also examined.
To compare specific characteristics of the HRM engine, in a comparable four-stroke mode, hypothetical 200, 400 and 600 cubic centimeter (cc) single cylinder reciprocating engines, each with compression ratio of 10, 15 and 20 were used as a basis for comparison. For similar outputs this resulted in the use of a 100, 200, 300 cc HRM configuration each with compression ratio of 10, 15 and 20. The geometric variables and combustion variables of The HRM combustion chamber is analyzed and compared with the baseline reciprocating engine.
Recommended Citation
Arumugam, Sathyanarayanan, "Analysis of Combustion Chamber Design Variables in Planetary Rotary Engine" (2004). Masters Theses. 4844.
https://scholarworks.wmich.edu/masters_theses/4844