Abstract
The oxidation of fuel sulfur to S(6) (SO{sub 3}+H{sub 2}SO{sub 4}) in a supersonic (Concorde) and a subsonic (ATTAS) aircraft engine is estimated numerically. The results indicate between 2% and 10% of the fuel sulfur is emitted as S(6). It is also shown that conversion in the turbine is limited by the level of atomic oxygen at the combustor exit, resulting in a higher oxidation efficiency as the sulfur mass loading is decreased. SO{sub 2} and SO{sub 3} are the primary sulfur oxidation products, with less than 1% of fuel sulfur converted to H{sub 2}SO{sub 4}. For the Concorde, H{sub 2}SO{sub 4} was primarily formed during the supersonic expansion through the divergent nozzle. (author) 20 refs.
Miake-Lye, R C;
Anderson, M R;
Brown, R C;
Kolb, C E;
[1]
Sorokin, A A;
Buriko, Y I
[2]
- Aerodyne Research, Inc., Billerica, MA (United States). Center for Chemical and Environmental Physics
- Scientific Research Center `Ecolen`, Moscow (Russian Federation)
Citation Formats
Miake-Lye, R C, Anderson, M R, Brown, R C, Kolb, C E, Sorokin, A A, and Buriko, Y I.
The conversion of SO{sub 2} to SO{sub 3} in gas turbine engines.
France: N. p.,
1997.
Web.
Miake-Lye, R C, Anderson, M R, Brown, R C, Kolb, C E, Sorokin, A A, & Buriko, Y I.
The conversion of SO{sub 2} to SO{sub 3} in gas turbine engines.
France.
Miake-Lye, R C, Anderson, M R, Brown, R C, Kolb, C E, Sorokin, A A, and Buriko, Y I.
1997.
"The conversion of SO{sub 2} to SO{sub 3} in gas turbine engines."
France.
@misc{etde_623591,
title = {The conversion of SO{sub 2} to SO{sub 3} in gas turbine engines}
author = {Miake-Lye, R C, Anderson, M R, Brown, R C, Kolb, C E, Sorokin, A A, and Buriko, Y I}
abstractNote = {The oxidation of fuel sulfur to S(6) (SO{sub 3}+H{sub 2}SO{sub 4}) in a supersonic (Concorde) and a subsonic (ATTAS) aircraft engine is estimated numerically. The results indicate between 2% and 10% of the fuel sulfur is emitted as S(6). It is also shown that conversion in the turbine is limited by the level of atomic oxygen at the combustor exit, resulting in a higher oxidation efficiency as the sulfur mass loading is decreased. SO{sub 2} and SO{sub 3} are the primary sulfur oxidation products, with less than 1% of fuel sulfur converted to H{sub 2}SO{sub 4}. For the Concorde, H{sub 2}SO{sub 4} was primarily formed during the supersonic expansion through the divergent nozzle. (author) 20 refs.}
place = {France}
year = {1997}
month = {Dec}
}
title = {The conversion of SO{sub 2} to SO{sub 3} in gas turbine engines}
author = {Miake-Lye, R C, Anderson, M R, Brown, R C, Kolb, C E, Sorokin, A A, and Buriko, Y I}
abstractNote = {The oxidation of fuel sulfur to S(6) (SO{sub 3}+H{sub 2}SO{sub 4}) in a supersonic (Concorde) and a subsonic (ATTAS) aircraft engine is estimated numerically. The results indicate between 2% and 10% of the fuel sulfur is emitted as S(6). It is also shown that conversion in the turbine is limited by the level of atomic oxygen at the combustor exit, resulting in a higher oxidation efficiency as the sulfur mass loading is decreased. SO{sub 2} and SO{sub 3} are the primary sulfur oxidation products, with less than 1% of fuel sulfur converted to H{sub 2}SO{sub 4}. For the Concorde, H{sub 2}SO{sub 4} was primarily formed during the supersonic expansion through the divergent nozzle. (author) 20 refs.}
place = {France}
year = {1997}
month = {Dec}
}