LOW NOISE COMPRESSOR ROTOR FOR GEARED TURBOFAN ENGINE

摘要

A gas turbine engine has a fan and a turbine having a fan drive turbine rotor. The fan drive turbine rotor drives a compressor rotor. A gear reduction effects a reduction in the speed of the fan relative to an input speed from the fan drive turbine rotor that drives the compressor rotor. The compressor rotor has a number of compressor blades in at least one of a plurality of rows of the compressor rotor. The blades operate at least some of the time at a rotational speed. The number of compressor blades in at least one row and the rotational speed are such that the following formula holds true for at least one row of the compressor rotor turbine: (number of blades×rotational speed)/60 s≧5500 Hz, and the rotational speed is in revolutions per minute. A method of designing a gas turbine engine and a compressor module are also disclosed.

主权项

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 number of blades×said rotational speed)/60 s≧5500 Hz; and said rotational speed being in revolutions per minute.