US Patent 8448895 Gas turbine engine compressor arrangement
Patent 8448895 was granted and assigned to United Technologies on May, 2013 by the United States Patent and Trademark Office.
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Patent abstract
A gas turbine engine includes a fan section and a low spool that includes a low pressure compressor section. The low pressure compressor section includes eight (8) or less stages. A high spool includes a high pressure compressor section that has between eight to fifteen (8-15) stages. An overall compressor pressure ratio is provided by the combination of the low pressure compressor section and the high pressure compressor. A gear train is defined along an engine centerline axis. The low spool is operable to drive the fan section through the gear train.
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Patent Inventor Names
Brian D. Merry0
Christopher M. Dye0
Frederick M. Schwarz0
Gabriel L. Suciu0
Steven B. Johnson0
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US Patent 08448895 Gas turbine engine compressor arrangement US Patent 8448895 Gas turbine engine compressor arrangement
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Patent Number
08448895
Patent Number
8448895
Edits on 16 Dec, 2021
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US Patent 08448895 Gas turbine engine compressor arrangement
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Is a
Current assignee
Patent jurisdiction
Patent number
08448895
Date of patent
May 28, 2013
Patent application number
13484361
Date Filed
May 31, 2012
Patent primary examiner
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