Advanced Search
DSpace@MIT

Acoustic and thermal packaging of small gas turbines for portable power

Research and Teaching Output of the MIT Community

Show simple item record

dc.contributor.advisor Zoltán S. Spakovszky. en_US
dc.contributor.author Tanaka, Shinji, S.M. Massachusetts Institute of Technology en_US
dc.contributor.other Massachusetts Institute of Technology. Dept. of Aeronautics and Astronautics. en_US
dc.date.accessioned 2010-02-09T16:56:22Z
dc.date.available 2010-02-09T16:56:22Z
dc.date.copyright 2009 en_US
dc.date.issued 2009 en_US
dc.identifier.uri http://hdl.handle.net/1721.1/51648
dc.description Thesis (S.M.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 2009. en_US
dc.description Includes bibliographical references (p. 201-203). en_US
dc.description.abstract To meet the increasing demand for advanced portable power units, for example for use in personal electronics and robotics, a number of studies have focused on portable small gas turbines. This research is concerned with gas turbine generator units in the 1 kW range. The compact and small-scale architecture of the portable gas turbine engine poses major challenges in the acoustic treatment that is required to attenuate the broadband and tonal noise of the high-speed turbomachinery. The challenge in the thermal management is the relatively large required cooling mass flow and the short flow mixing length, constrained by package size considerations. The objective is to conceive a proof-of-concept engine package with exhaust temperatures of 60 °C and a noise signature below 50 dBA at a distance of 7 m. Various liner materials and configurations were investigated in an anechoic chamber using a modular silencer test rig. Acoustic liners based on porous fiber material were developed for both cold intake and hot exhaust gas silencers to reduce the broadband noise. The source noise simulations combined with the measured silencer noise reduction show noise levels below 50 dBA in all directions. A parametric silencer configuration study was carried out to determine the trade-off between liner volume, surface area, and noise reduction. The liner material was demonstrated to withstand hot gas conditions at 700 °C. en_US
dc.description.abstract (cont.) A mixer/ejector based cooling scheme was proposed and experimentally investigated using vortex generator rings and multi-walled ejectors to enhance the mixing. Although the augmentations achieved a satisfactory mass flow ratio of 16.8:1, hot spots still exist at the exit of the relatively long mixer duct due to the high area-ratio of the ejector configuration. It was concluded that implementation of the scheme into the package is not practical. To overcome this mixing challenge, an alternative cooling scheme was conceived. An inverted dilution liner mixes hot core gas flowing radially through a perforated cylinder with cold fan air. The mixing length is reduced due to jet induced streamwise vortices. The performance of the device was investigated using three-dimensional computational fluid dynamics simulations, which demonstrated improved mixing and uniform, low temperatures of less than 70 °C at the mixer exit. Noise reduction and flow mixing guidelines are established together with a concept package configuration, generally applicable to small scale gas turbine devices. en_US
dc.description.statementofresponsibility by Shinji Tanaka. en_US
dc.format.extent 203 p. en_US
dc.language.iso eng en_US
dc.publisher Massachusetts Institute of Technology en_US
dc.rights M.I.T. theses are protected by copyright. They may be viewed from this source for any purpose, but reproduction or distribution in any format is prohibited without written permission. See provided URL for inquiries about permission. en_US
dc.rights.uri http://dspace.mit.edu/handle/1721.1/7582 en_US
dc.subject Aeronautics and Astronautics. en_US
dc.title Acoustic and thermal packaging of small gas turbines for portable power en_US
dc.type Thesis en_US
dc.description.degree S.M. en_US
dc.contributor.department Massachusetts Institute of Technology. Dept. of Aeronautics and Astronautics. en_US
dc.identifier.oclc 496822374 en_US


Files in this item

Name Size Format Description
496822374.pdf 32.37Mb PDF Preview, non-printable (open to all)
496822374-MIT.pdf 32.37Mb PDF Full printable version (MIT only)

This item appears in the following Collection(s)

Show simple item record

MIT-Mirage