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公开(公告)号:US20170343574A1
公开(公告)日:2017-11-30
申请号:US15662528
申请日:2017-07-28
发明人: David A. Topol , Bruce L. Morin , Detlef Korte
CPC分类号: G01P3/48 , F01D5/02 , F01D5/12 , F02C3/04 , F02C3/10 , F02C7/24 , F02C7/32 , F02C7/36 , F02K3/06 , F05D2200/13 , F05D2200/14 , F05D2220/32 , F05D2220/36 , F05D2260/40311 , F05D2260/96 , Y02T50/673 , Y10T29/49236 , Y10T29/4932
摘要: A gas turbine engine has a fan, a turbine section having a first turbine including a first turbine rotor, a compressor rotor, and a gear reduction that effects a reduction in a speed of the fan relative to an input speed from the first turbine rotor. 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 plurality of the blade rows of the first turbine rotor: (number of blades×rotational speed)/60≧5500, and the rotational speed being an approach speed in revolutions per minute, and the following formula holds true for at least a plurality of the blade rows of the compressor rotor: (number of blades×rotational speed)/60≦10000, the rotational speed being an approach speed in revolutions per minute.