Author

Arumugam

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.

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