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Characterization of heat transfer rates in supercritical ethanol for micro-rocket engine regenerative cooling

IP.com Disclosure Number: IPCOM000128033D
Original Publication Date: 1998-Dec-31
Included in the Prior Art Database: 2005-Sep-14
Document File: 7 page(s) / 23K

Publishing Venue

Software Patent Institute

Related People

Lopata, Jacob Brian: AUTHOR [+3]

Related Documents

http://theses.mit.edu:80/Dienst/UI/2.0/Describe/0018.mit.theses/1998-215: URL

Abstract

An experimental investigation that characterizes heat transfer rates to supercritical ethanol in micro-channels is presented. Forced convection heat transfer data resulted from the use of small diameter circular tubes fed by a pressurized fuel supply. The test sections consisted of resistively heated stainless steel hypodermic tubes -4mm in length with an inside diameter of -95P. Test conditions were such that most of the physical parameters that are expected in the cooling passages of a silicon fabricated MicroRocket engine were duplicated. These included conditions of temperature, pressure, film Reynolds number, bulk Nusselt number, and heat flux. The pressures investigated were 100atm and 300atm, corresponding to reduced pressures of 1.62 and 4.86 respectively. Heat flux values ranged from 3 to 125 W/mm 2 . Experimental results indicate that ethanol is a suitable fuel for a regeneratively cooled MicroRocket engine. At several observed pressures, temperatures and heat fluxes, bulk Nusselt number values exceeded those required in the engine cooling passages. In addition, an analysis of the inside tube wall of one of the test sections indicates that carbon deposition resulting from the pyrolysis of ethanol will not be an issue for MicroRocket engine design. It was also found that established empirical formulas provided poor correlation to experimental data but that one of these equations, suitably modified, provided excellent correlation at 300atm for a restricted range of conditions. Thesis Supervisor: Professor Alan H. Epstein Title: R.C. Maclaurin Professor of Aeronautics and Astronautics Thesis Supervisor: Professor Jack L. Kerrerbrock Title: Professor of Aeronautics and Astronautics [3]

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 This record is the front matter from a document that appears on a server at MIT and is used through permission from MIT. See http://theses.mit.edu:80/Dienst/UI/2.0/Describe/0018.mit.theses/1998-215 for copyright details and for the full document in image form.

CHARACTERIZATION OF HEAT TRANSFER RATES IN SUPERCRITICAL ETHANOL FOR MICRO-ROCKET ENGINE REGENERATIVE COOLING

by

JACOB BRIAN LOPATA
Bachelor of Science in Aerospace Engineering Illinois Institute of Technology, 1996 Submitted in partial fulfillment of the requirements for the degree of MASTER OF SCIENCE at the Massachusetts Institute of Technology September 1998
SIGNATURE OF author: [[signature omitted]]

CERTIFIED BY: [[SIGNATURE OMITTED]]

Professor Alan H. Epstein

R.C. Maclaurin Professor of Aeronautics and Astronautics Thesis Supervisor Professor Jack L. Kerrebrock
Professor of Aeronautics and Astronautics, Emeritus Thesis Supervisor ACCEPTED BY: [[SIGNATURE OMITTED]]

Professor Jaime Peraire Professor of Aeronautics and Astronautics Chair, Graduate Office ARCHIVES MASSACHUSETTS INSTITUTE OF TECHNOLOGY LIBRARIES SEP 22 1998

Massachusetts Institute of Technology Page 1 Dec 31, 1998

Page 2 of 7

Characterization of heat transfer rates in supercritical ethanol for micro-rocket engine regenerative cooling

CHARACTERIZATION OF HEAT TRANSFER RATES IN SUPERCRITICAL ETHANOL FOR MICRO-ROCKET ENGINE REGENERATIVE COOLING

by JACOB BRIAN LOPATA

Submitted to the Department of Aeronautics and Astronautics on August 21, 1998 in Partial Fulfillment of the Requirements for the Degree of Master of Science

ABSTRACT

An experimental investigation that characterizes heat transfer rates to supercritical ethanol in micro-channels is presented. Forced convection heat transfer data resulted from the use of small diameter circular tubes fed by a pressurized fuel supply. The test sections consisted of resistively heated stainless steel hypodermic tubes -4mm in length with an inside diameter of - 95P. Test conditions were such that most of the physical parameters that are expected in the cooling passages of a silicon fabricated MicroRocket engine were duplicated. These included conditions of temperature, pressure, film Reynolds number, bulk Nusselt number, and heat flux. The pressures investigated were 100atm and 300atm, corresponding to reduced pressures of
1.62 and 4.86 respectively. Heat flux values ranged from 3 to 125 W/mm2.

Experimental results indicate that ethanol is a suitable fuel for a regeneratively cooled MicroRocket engine. At several observed pressures, temperatures and heat fluxes, bulk Nusselt number values exceeded those required in the engine cooling passages. In addition, an analysis of the inside tube wall of one of the test sections indicates that carbon deposition resulting from the pyrolysis of ethanol will not be an issue for MicroRocket engine design. It was also found that established empirical formulas provided poor correlation to experimental data but that one of these equatio...