Geared turbofan with integrally bladed rotor
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United States of America Patent
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Aug 28, 2018
Grant Date -
Dec 10, 2015
app pub date -
May 12, 2015
filing date -
Jun 10, 2014
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Abstract
A gas turbine comprises a compressor module, with a lower pressure compressor section including a plurality of stages, with at least one of the plurality of stages being an integrally bladed rotor. A higher pressure compressor section includes a plurality of stages with at least one of the plurality of stages being an integrally bladed rotor. A fan drive turbine shaft drives a fan rotor through a gear reduction. The fan rotor delivers a portion of air into a bypass duct, and a portion of air into the compressor module. A bypass ratio defined by the volume of air delivered into the bypass duct compared to the volume of air delivered into the compressor module is greater than or equal to about 6.0.
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