LOW NOISE TURBINE FOR GEARED TURBOFAN ENGINE
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United States of America Patent
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Issued Date -
Jan 28, 2016
app pub date -
Jul 10, 2015
filing date -
Jan 31, 2012
priority date (Note) -
Abandoned
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Abstract
A gas turbine engine comprises a fan, a compressor section including a compressor having a low pressure portion and a high pressure portion, a combustor section, and a turbine having a downstream portion. A gear reduction effects a reduction in the speed of the fan relative to an input speed to the fan. The downstream portion of the turbine has a number of turbine blades in each of a plurality of rows of the downstream turbine portion. The turbine blades operate at least some of the time at a rotational speed. The number of blades and the rotational speed are such that the following formula holds true for at least one of the blade rows of the downstream turbine: (number of blades×speed)/60≧5500. The rotational speed is an approach speed in revolutions per minute. A method of designing a gas turbine engine and a turbine module are also disclosed.
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