LOW NOISE TURBINE FOR GEARED TURBOFAN ENGINE
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United States of America Patent
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app pub date -
Jul 10, 2015
filing date -
Jan 31, 2012
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Abandoned
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Abstract
A gas turbine engine comprises a fan and a turbine having a fan drive rotor. There is also a second turbine rotor. A gear reduction effects a reduction in the speed of the fan relative to an input speed from the fan drive rotor. The fan drive rotor has a number of turbine blades in at least one of a plurality of rows of the fan drive rotor, and the turbine blades operate at least some of the time at a rotational speed. The number of turbine blades in the at least one row and the rotational speed are such that the following formula holds true for the at least one row of the fan drive turbine: (number of blades×speed)/60≧5500 Hz. The rotational speed is in revolutions per minute. A method of designing a gas turbine engine, and a turbine module are also disclosed.
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