Patent ID: 9726019
Date: 2017-08-08
CPC Classifications: F01D,F02C,F02K,F05D,G01P,Y02T,Y10T

Claim:
1. A gas turbine engine comprising: a fan, a turbine section having a fan drive turbine rotor, and a compressor rotor; a gear reduction effecting a reduction in a speed of said fan relative to an input speed from said fan drive turbine rotor; said compressor rotor having a number of compressor blades in at least one of a plurality of blade rows of said compressor rotor, and said blades configured to operate at least some of the time at a rotational speed, and said number of compressor blades in said at least one of said blade rows and said rotational speed being such that the following formula holds true for said at least one of said plurality of blade rows of the compressor rotor: said rotational speed being an approach speed in revolutions per minute.