GAS TURBINE ENGINE WITH LOW STAGE COUNT LOW PRESSURE TURBINE
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United States of America Patent
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app pub date -
Oct 1, 2015
filing date -
Jun 2, 2008
priority date (Note) -
Abandoned
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Abstract
A gas turbine engine according to an example of the present disclosure includes, among other things, a fan section, a first compressor section including three (3) or more stages, a second compressor section including between eight (8) and thirteen (13) stages, and a first turbine section operable for driving the first compressor section, the first turbine section including between three (3) and six (6) stages, a second turbine section operable for driving the second compressor section, and a gear train defined along an engine centerline axis. One of the first turbine section and the second turbine section is operable to drive the fan section through the gear train.
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