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Counterrotatable booster compressor assembly for a gas turbine engineA counterrotatable booster compressor assembly for a gas turbine engine having a counterrotatable fan section with a first fan blade row connected to a first drive shaft and a second fan blade row axially spaced from the first fan blade row and connected to a second drive shaft, the counterrotatable booster compressor assembly including a first compressor blade row connected to the first drive shaft and a second compressor blade row interdigitated with the first compressor blade row and connected to the second drive shaft. A portion of each fan blade of the second fan blade row extends through a flowpath of the counterrotatable booster compressor so as to function as a compressor blade in the second compressor blade row. The counterrotatable booster compressor further includes a first platform member integral with each fan blade of the second fan blade row at a first location so as to form an inner flowpath for the counterrotatable booster compressor and a second platform member integral with each fan blade of the second fan blade row at a second location so as to form an outer flowpath for the counterrotatable booster compressor.
Document ID
20080005193
Acquisition Source
Headquarters
Document Type
Other - Patent
Authors
Moniz, Thomas Ory
Orlando, Robert Joseph
Date Acquired
August 24, 2013
Publication Date
May 25, 2004
Subject Category
Mechanical Engineering
Report/Patent Number
Patent Number: US-PATENT-6,739,120
Patent Application Number: US-PATENT-APPL-SN-134172
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
Patent
US-PATENT-6,739,120
Patent Application
US-PATENT-APPL-SN-134172
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