2026-09-20T10:39:25Zhttps://dspace.mit.edu/server/oai/requestoai:dspace.mit.edu:1721.1/322412022-01-13T07:54:11Zcom_1721.1_7582com_1721.1_7581col_1721.1_131023
Alan H. Epstein.
Diez, Shana, 1980-
Massachusetts Institute of Technology. Dept. of Aeronautics and Astronautics.
Massachusetts Institute of Technology. Department of Aeronautics and Astronautics
2006-03-29T18:27:01Z
2006-03-29T18:27:01Z
2003
2003
http://hdl.handle.net/1721.1/32241
54983177
Thesis (S.M.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 2003.
Includes bibliographical references (p. 175-176).
The demonstration micro turbopump was designed to prove the feasibility of pumping a liquid using a turbopump on the micro scale. This thesis presents the first data indicating positive pumping from the demonstration micro turbopump. Data pertaining to both the turbomachinery as well as the bearing systems for these preliminary tests is shown and discussed. The pressure rise through the pump, turbine pressure ratio, respective powers, and a system efficiency are presented. Bearing theory and static flow test data are discussed. The pump design is detailed. Modelling data is presented to help describe the operational difficulties with the highly coupled aft bearing system. These operational difficulties lead to the redesign of the aft bearing system, which is described in detail. Other operational procedures developed and discussed include the pump start up procedure and the use of the inverted journal bearing.
by Shana Diez.
S.M.
176 p.
8057280 bytes
8056685 bytes
application/pdf
application/pdf
eng
Massachusetts Institute of Technology
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http://dspace.mit.edu/handle/1721.1/7582
Aeronautics and Astronautics.
Preliminary performance characteristics of a microfabricated turbopump
Thesis
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