WASTE HEAT RECOVERY FROM A GAS TURBINE ENGINE USING A HEAT EXCHANGER AND ASSOCIATED CENTRIFUGAL COMPRESSOR VOLUTE DESIGN AND SIMULATION
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Authors
Kaim, Michael
Subjects
energy
waste heat recovery
gas turbine engine
waste heat recovery
gas turbine engine
Advisors
Hobson, Garth V.
Seivwright, Douglas L.
Date of Issue
2019-06
Date
Publisher
Monterey, CA; Naval Postgraduate School
Language
Abstract
The U.S. Department of Defense has implemented an initiative to become more energy efficient across all services. The Naval Postgraduate School supported development towards this goal by studying the possibility of energy generation using waste heat recovery within shipboard gas turbine engine exhaust. This research included the development of a heat exchanger ultimately to use compressed CO2 as the working fluid to run a Brayton cycle. In support of this research, this thesis continued previous research regarding the Rolls Royce M250 helicopter engine and the heat exchanger previously designed. The heat exchanger was modified and the coils replaced using lessons learned from the previous iteration, and a second heat exchanger was built to match the first. The heat exchangers were installed on the engine’s dual exhaust in order to gather measurements to determine how they would affect engine performance. The heat exchangers were tested using nitrogen to determine effectiveness. Additionally, a centrifugal compressor volute was designed utilizing a commercial impeller. An ANSYS CFD model was developed and tested to create a map of the compressor’s performance utilizing air. The compressor was then manufactured using 3D printing technology and run using an independent electric motor so that the compressor and turbine can be run uncoupled at different speeds. This thesis was critical in the continuing development of a shipboard waste heat recovery system.
Type
Thesis
Description
Series/Report No
Department
Mechanical and Aerospace Engineering (MAE)
Organization
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NPS Report Number
Sponsors
Funder
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Citation
Distribution Statement
Approved for public release; distribution is unlimited.
Rights
This publication is a work of the U.S. Government as defined in Title 17, United States Code, Section 101. Copyright protection is not available for this work in the United States.