GLTRS--Glenn
TITLE AND SUBTITLE:
Magnetogasdynamic Power Extraction and Flow Conditioning for a Gas Turbine

AUTHOR(S):
Igor V. Adamovich, J. William Rich, Steven J. Schneider, and Isaiah M. Blankson

REPORT DATE:
October 2003

FUNDING NUMBERS:
WBS-22-274-00-0217

PERFORMING ORGANIZATION NAME(S) AND ADDRESS(ES):
National Aeronautics and Space Administration
John H. Glenn Research Center at Lewis Field
Cleveland, Ohio 44135-3191

PERFORMING ORGANIZATION REPORT NUMBER:
E-14170

SPONSORING/MONITORING AGENCY NAME(S) AND ADDRESS(ES):
National Aeronautics and Space Administration
Washington, DC 20546-0001

REPORT TYPE AND DATES COVERED:
Technical Memorandum

SPONSORING/MONITORING AGENCY REPORT NUMBER:
NASA TM-2003-212612
AIAA-2003-4289

SUPPLEMENTARY NOTES:
Prepared for the 34th Plasmadynamics and Laser Conference sponsored by the American Institute of Aeronautics and Astronautics, Orlando, Florida, June 23-26, 2003. Igor V. Adamovich and J. William Rich, Ohio State University, Columbus, Ohio 43210; and Steven J. Schneider and Isaiah M. Blankson, NASA Glenn Research Center. Responsible person, Steven J. Schneider, organization code 5430, 216-977-7484.

ABSTRACT:
An extension of the Russian AJAX concept to a turbojet is being explored. This magnetohydrodynamic (MHD) energy bypass engine cycle incorporating conventional gas turbine technology has MHD flow conditioning at the inlet to electromagnetically extract part of the inlet air kinetic energy. The electrical power generated can be used for various on-board vehicle requirements including plasma flow control around the vehicle or it may be used for augmenting the expanding flow in the high speed nozzle by MHD forces to generate more thrust. In order to achieve this interaction, the air needs to be ionized by an external means even up to fairly high flight speeds, and the leading candidates may be classified as electrical discharge devices. The present kinetic modeling calculations suggest that the use of electron beams with characteristics close to the commercially available e-beam systems (electron energy ~60 keV, beam current ~0.2 mA/cm2) to sustain ionization in intermediate pressure, low-temperature (P = 0.1 atm, T = 300 K) supersonic air flows allows considerable reduction of the flow kinetic energy (up to 10 to 20 percent in M = 3 flows). The calculations also suggest that this can be achieved at a reasonable electron beam efficiency (η ~5), even if the e-beam window losses are taken into account. At these conditions, the exit NO and O atom concentrations due to e-beam initiated chemical reactions do not exceed 30 ppm. Increasing the beam current up to ~2 mA/cm2, which corresponds to a maximum electrical conductivity of σmax ~0.8 mho/m at the loading parameter of K = 0.5, would result in a much greater reduction of the flow kinetic energy (up to 30 to 40 percent). The MHD channel efficiency at these conditions would be greatly reduced (to η ~1) due to increased electron recombination losses in the channel. At these conditions, partial energy conversion from kinetic energy to heat would result in a significant total pressure loss (P0/P0i ~0.3). The total pressure loss can be reduced operating at the loading parameter closer to unity, at the expense of the reduced electrical power output. Raising the beam current would also result in the increase of the exit O atom concentrations (up to 600 ppm) and NO (up to 150 ppm).

SUBJECT TERMS:
Magnetohydrodynamics; Hypersonic inlets; Launch vehicles

NUMBER OF PAGES:
21

PDF AVAILABLE FROM URL:
2003/TM-2003-212612.pdf ( 938 KB )
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Magnetogasdynamic Power Extraction and Flow Conditioning for a Gas Turbine GLTRS--Glenn
TITLE AND SUBTITLE:
Magnetogasdynamic Power Extraction and Flow Conditioning for a Gas Turbine

AUTHOR(S):
Igor V. Adamovich, J. William Rich, Steven J. Schneider, and Isaiah M. Blankson

REPORT DATE:
October 2003

FUNDING NUMBERS:
WBS-22-274-00-0217

PERFORMING ORGANIZATION NAME(S) AND ADDRESS(ES):
National Aeronautics and Space Administration
John H. Glenn Research Center at Lewis Field
Cleveland, Ohio 44135-3191

PERFORMING ORGANIZATION REPORT NUMBER:
E-14170

SPONSORING/MONITORING AGENCY NAME(S) AND ADDRESS(ES):
National Aeronautics and Space Administration
Washington, DC 20546-0001

REPORT TYPE AND DATES COVERED:
Technical Memorandum

SPONSORING/MONITORING AGENCY REPORT NUMBER:
NASA TM-2003-212612
AIAA-2003-4289

SUPPLEMENTARY NOTES:
Prepared for the 34th Plasmadynamics and Laser Conference sponsored by the American Institute of Aeronautics and Astronautics, Orlando, Florida, June 23-26, 2003. Igor V. Adamovich and J. William Rich, Ohio State University, Columbus, Ohio 43210; and Steven J. Schneider and Isaiah M. Blankson, NASA Glenn Research Center. Responsible person, Steven J. Schneider, organization code 5430, 216-977-7484.

ABSTRACT:
An extension of the Russian AJAX concept to a turbojet is being explored. This magnetohydrodynamic (MHD) energy bypass engine cycle incorporating conventional gas turbine technology has MHD flow conditioning at the inlet to electromagnetically extract part of the inlet air kinetic energy. The electrical power generated can be used for various on-board vehicle requirements including plasma flow control around the vehicle or it may be used for augmenting the expanding flow in the high speed nozzle by MHD forces to generate more thrust. In order to achieve this interaction, the air needs to be ionized by an external means even up to fairly high flight speeds, and the leading candidates may be classified as electrical discharge devices. The present kinetic modeling calculations suggest that the use of electron beams with characteristics close to the commercially available e-beam systems (electron energy ~60 keV, beam current ~0.2 mA/cm2) to sustain ionization in intermediate pressure, low-temperature (P = 0.1 atm, T = 300 K) supersonic air flows allows considerable reduction of the flow kinetic energy (up to 10 to 20 percent in M = 3 flows). The calculations also suggest that this can be achieved at a reasonable electron beam efficiency (h ~5), even if the e-beam window losses are taken into account. At these conditions, the exit NO and O atom concentrations due to e-beam initiated chemical reactions do not exceed 30 ppm. Increasing the beam current up to ~2 mA/cm2, which corresponds to a maximum electrical conductivity of smax ~0.8 mho/m at the loading parameter of K = 0.5, would result in a much greater reduction of the flow kinetic energy (up to 30 to 40 percent). The MHD channel efficiency at these conditions would be greatly reduced (to h ~1) due to increased electron recombination losses in the channel. At these conditions, partial energy conversion from kinetic energy to heat would result in a significant total pressure loss (P0/P0i ~0.3). The total pressure loss can be reduced operating at the loading parameter closer to unity, at the expense of the reduced electrical power output. Raising the beam current would also result in the increase of the exit O atom concentrations (up to 600 ppm) and NO (up to 150 ppm).

SUBJECT TERMS:
Magnetohydrodynamics; Hypersonic inlets; Launch vehicles

NUMBER OF PAGES:
21

PDF AVAILABLE FROM URL:
2003/TM-2003-212612.pdf ( 938 KB )
This page contains an Adobe® Acrobat® Reader PDF file. The PDF documents have been created to show thumbnails of each page. If the thumbnails do not display properly, download the file to the hard drive and view through Acrobat® Reader. You can download Acrobat® Reader for free.

NASA NASA GLTRS--Glenn

A service of the NASA Glenn Research Center Logistics and Technical Information Division

Suggestions or questions about this site can be directed to:

NASA official: Technical Publications Manager, Sue.E.Butts@nasa.gov

Web curator: Caroline.A.Rist@grc.nasa.gov

Privacy Policy and Important Notices