Patent ID: 9624834
Date: 2017-04-18
CPC Classifications: F01D,F02C,F05D,Y02T,Y10T

Claim:
1. A gas turbine engine comprising: a fan and a turbine section having a fan drive turbine rotor, and a compressor rotor; a gear reduction effecting a reduction in the 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 rows of said compressor rotor, and said blades operating at least some of the time at a rotational speed, and said number of compressor blades in said at least one row and said rotational speed being such that the following formula holds true for said at least one row of the compressor rotor: said rotational speed being an approach speed in revolutions per minute; and wherein a pressure ratio across the fan drive turbine rotor being greater than about 5.