Micro-heat engines, gas turbines, and rocket engines the met microengine project

A. H. Epstein; S. D. Senturia; O. Al-Midani; G. Anathasuresh; A. Ayon; K. Breuer; K. S. Chen; F. F. Ehrich; E. Esteve; L. Frechette; G. Gauba; R. Ghodssi; C. Groshenry; S. A. Jacobson; J. L. Kerrebrock; J. H. Lang; C. C. Lin; A. London; J. Lopata; A. Mehra; J. O.Mur Miranda; S. Nagle; D. J. Orr; E. Piekos; M. A. Schmidt; G. Shirley; S. M. Spearing; C. S. Tan; Y. S. Tzeng; L. A. Waitz

Micro-heat engines, gas turbines, and rocket engines the met microengine project

A. H. Epstein, S. D. Senturia, O. Al-Midani, G. Anathasuresh, A. Ayon, K. Breuer, K. S. Chen, F. F. Ehrich, E. Esteve, L. Frechette, G. Gauba, R. Ghodssi, C. Groshenry, S. A. Jacobson, J. L. Kerrebrock, J. H. Lang, C. C. Lin, A. London, J. Lopata, A. MehraJ. O.Mur Miranda, S. Nagle, D. J. Orr, E. Piekos, M. A. Schmidt, G. Shirley, S. M. Spearing, C. S. Tan, Y. S. Tzeng, L. A. Waitz

Department of Mechanical Engineering

Research output: Contribution to conference › Paper › peer-review

77 Citations (Scopus)

Abstract

This is a report on work in progress on microelectrical and mechanical systems (MEMS)-based gas turbine engines, turbogenerators, and rocket engines currently under development at MIT. Fabricated in large numbers in parallel using semiconductor manufacturing techniques, these engines are based on micro-high speed rotating machinery with the same power density as that achieved in their more familiar, full-sized brethren. The micro-gas turbine is designed as a 1 cm diameter by 3 mm thick SiC heat engine producing 10-20 W of electric power or 0.05- 0.1 N of thrust while consuming under 10 grams/hr of H₂. Later versions may produce up to 100 W using hydrocarbon fuels. A liquid fuel, bi-propellant rocket motor of similar size could develop over 3 Ib of thrust. The rocket motor would be complete with turbopumps and control valves on the same chip. A key conclusion from the analytical and experimental work to date is that micro- heat engines of this sort do appear feasible. These devices may enable new concepts in propulsion, fluid control, and portable power generation.

Original language	English
Publication status	Published - 1997
Event	28th Fluid Dynamics Conference, 1997 - Snowmass Village, United States Duration: 1997 Jun 29 → 1997 Jul 2

Other

Other	28th Fluid Dynamics Conference, 1997
Country/Territory	United States
City	Snowmass Village
Period	97-06-29 → 97-07-02

All Science Journal Classification (ASJC) codes

General Engineering

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Epstein, A. H., Senturia, S. D., Al-Midani, O., Anathasuresh, G., Ayon, A., Breuer, K., Chen, K. S., Ehrich, F. F., Esteve, E., Frechette, L., Gauba, G., Ghodssi, R., Groshenry, C., Jacobson, S. A., Kerrebrock, J. L., Lang, J. H., Lin, C. C., London, A., Lopata, J., ... Waitz, L. A. (1997). Micro-heat engines, gas turbines, and rocket engines the met microengine project. Paper presented at 28th Fluid Dynamics Conference, 1997, Snowmass Village, United States.

@conference{33b3336f10f44eb3be1c0e6c2167121c,

title = "Micro-heat engines, gas turbines, and rocket engines the met microengine project",

abstract = "This is a report on work in progress on microelectrical and mechanical systems (MEMS)-based gas turbine engines, turbogenerators, and rocket engines currently under development at MIT. Fabricated in large numbers in parallel using semiconductor manufacturing techniques, these engines are based on micro-high speed rotating machinery with the same power density as that achieved in their more familiar, full-sized brethren. The micro-gas turbine is designed as a 1 cm diameter by 3 mm thick SiC heat engine producing 10-20 W of electric power or 0.05- 0.1 N of thrust while consuming under 10 grams/hr of H2. Later versions may produce up to 100 W using hydrocarbon fuels. A liquid fuel, bi-propellant rocket motor of similar size could develop over 3 Ib of thrust. The rocket motor would be complete with turbopumps and control valves on the same chip. A key conclusion from the analytical and experimental work to date is that micro- heat engines of this sort do appear feasible. These devices may enable new concepts in propulsion, fluid control, and portable power generation.",

author = "Epstein, {A. H.} and Senturia, {S. D.} and O. Al-Midani and G. Anathasuresh and A. Ayon and K. Breuer and Chen, {K. S.} and Ehrich, {F. F.} and E. Esteve and L. Frechette and G. Gauba and R. Ghodssi and C. Groshenry and Jacobson, {S. A.} and Kerrebrock, {J. L.} and Lang, {J. H.} and Lin, {C. C.} and A. London and J. Lopata and A. Mehra and Miranda, {J. O.Mur} and S. Nagle and Orr, {D. J.} and E. Piekos and Schmidt, {M. A.} and G. Shirley and Spearing, {S. M.} and Tan, {C. S.} and Tzeng, {Y. S.} and Waitz, {L. A.}",

note = "Publisher Copyright: {\textcopyright} 1997 by Alan H. Epstein. Published by the American Institute of Aeronautics and Astronautics, Inc.; 28th Fluid Dynamics Conference, 1997 ; Conference date: 29-06-1997 Through 02-07-1997",

year = "1997",

language = "English",

}

Epstein, AH, Senturia, SD, Al-Midani, O, Anathasuresh, G, Ayon, A, Breuer, K, Chen, KS, Ehrich, FF, Esteve, E, Frechette, L, Gauba, G, Ghodssi, R, Groshenry, C, Jacobson, SA, Kerrebrock, JL, Lang, JH, Lin, CC, London, A, Lopata, J, Mehra, A, Miranda, JOM, Nagle, S, Orr, DJ, Piekos, E, Schmidt, MA, Shirley, G, Spearing, SM, Tan, CS, Tzeng, YS & Waitz, LA 1997, 'Micro-heat engines, gas turbines, and rocket engines the met microengine project', Paper presented at 28th Fluid Dynamics Conference, 1997, Snowmass Village, United States, 97-06-29 - 97-07-02.

TY - CONF

T1 - Micro-heat engines, gas turbines, and rocket engines the met microengine project

AU - Epstein, A. H.

AU - Senturia, S. D.

AU - Al-Midani, O.

AU - Anathasuresh, G.

AU - Ayon, A.

AU - Breuer, K.

AU - Chen, K. S.

AU - Ehrich, F. F.

AU - Esteve, E.

AU - Frechette, L.

AU - Gauba, G.

AU - Ghodssi, R.

AU - Groshenry, C.

AU - Jacobson, S. A.

AU - Kerrebrock, J. L.

AU - Lang, J. H.

AU - Lin, C. C.

AU - London, A.

AU - Lopata, J.

AU - Mehra, A.

AU - Miranda, J. O.Mur

AU - Nagle, S.

AU - Orr, D. J.

AU - Piekos, E.

AU - Schmidt, M. A.

AU - Shirley, G.

AU - Spearing, S. M.

AU - Tan, C. S.

AU - Tzeng, Y. S.

AU - Waitz, L. A.

PY - 1997

Y1 - 1997

N2 - This is a report on work in progress on microelectrical and mechanical systems (MEMS)-based gas turbine engines, turbogenerators, and rocket engines currently under development at MIT. Fabricated in large numbers in parallel using semiconductor manufacturing techniques, these engines are based on micro-high speed rotating machinery with the same power density as that achieved in their more familiar, full-sized brethren. The micro-gas turbine is designed as a 1 cm diameter by 3 mm thick SiC heat engine producing 10-20 W of electric power or 0.05- 0.1 N of thrust while consuming under 10 grams/hr of H2. Later versions may produce up to 100 W using hydrocarbon fuels. A liquid fuel, bi-propellant rocket motor of similar size could develop over 3 Ib of thrust. The rocket motor would be complete with turbopumps and control valves on the same chip. A key conclusion from the analytical and experimental work to date is that micro- heat engines of this sort do appear feasible. These devices may enable new concepts in propulsion, fluid control, and portable power generation.

AB - This is a report on work in progress on microelectrical and mechanical systems (MEMS)-based gas turbine engines, turbogenerators, and rocket engines currently under development at MIT. Fabricated in large numbers in parallel using semiconductor manufacturing techniques, these engines are based on micro-high speed rotating machinery with the same power density as that achieved in their more familiar, full-sized brethren. The micro-gas turbine is designed as a 1 cm diameter by 3 mm thick SiC heat engine producing 10-20 W of electric power or 0.05- 0.1 N of thrust while consuming under 10 grams/hr of H2. Later versions may produce up to 100 W using hydrocarbon fuels. A liquid fuel, bi-propellant rocket motor of similar size could develop over 3 Ib of thrust. The rocket motor would be complete with turbopumps and control valves on the same chip. A key conclusion from the analytical and experimental work to date is that micro- heat engines of this sort do appear feasible. These devices may enable new concepts in propulsion, fluid control, and portable power generation.

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UR - http://www.scopus.com/inward/citedby.url?scp=80053611902&partnerID=8YFLogxK

M3 - Paper

AN - SCOPUS:80053611902

T2 - 28th Fluid Dynamics Conference, 1997

Y2 - 29 June 1997 through 2 July 1997

ER -

Micro-heat engines, gas turbines, and rocket engines the met microengine project

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