Patent ID: 9733266
Date: 2017-08-15
CPC Classifications: F01D,F02C,F02K,F05D,G01P,Y02T,Y10T

Claim:
1. A gas turbine engine comprising: a fan; a turbine section having a first turbine including a first turbine rotor; a compressor rotor; a gear reduction configured to effect a reduction in a speed of the fan relative to an input speed from the first turbine rotor; and wherein each of the compressor rotor and the first turbine rotor includes a number of blades in each of a plurality of blade rows, the number of blades configured to operate at least some of the time at a rotational speed, and the number of blades and the rotational speed being such that the following formula holds true for at least a majority of the blade rows of the first turbine rotor, but does not hold true for any of the blade rows of the compressor rotor: the rotational speed being an approach speed in revolutions per minute.