公开(公告)号：US08834099B1

公开(公告)日：2014-09-16

申请号：US14159760

申请日：2014-01-21

Applicant: United Technologies Corporation

Inventor： David A. Topol ,  Bruce L. Morin

IPC: F01D1/02

CPC classification number: F01D5/12 ,  F01D5/02 ,  F05D2220/327 ,  F05D2260/40311 ,  F05D2260/96 ,  Y02T50/673

Abstract: A gas turbine engine comprises a fan and a turbine section having a first turbine rotor. The first turbine rotor drives a compressor rotor. A gear reduction effects a reduction in the speed of the fan relative to an input speed from a fan drive turbine 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: (the number of blades×the rotational speed)/(60 seconds/minute)≧5500 Hz; and the rotational speed being in revolutions per minute. A compressor module and a method of designing a gas turbine engine are also disclosed.

Abstract translation: 燃气涡轮发动机包括风扇和具有第一涡轮转子的涡轮部分。 第一涡轮转子驱动压缩机转子。 齿轮减速效应相对于来自风扇驱动涡轮转子的输入速度降低了风扇的速度。 压缩机转子在压缩机转子的多排中的至少一排中具有多个压缩机叶片。 叶片在旋转速度下至少运行一些时间。 至少一行中的压缩机叶片的数量和转速使得至少一排压缩机转子的以下公式成立：（叶片数×转速）/（60秒/分钟）≥ 5500 Hz; 转速为每分钟转。 还公开了压缩机模块和设计燃气涡轮发动机的方法。