Low noise compressor and turbine for geared turbofan engine
US9733266B2 · kind B2 · utility
Assignees
Inventors
Key dates
| Filing date | Sep 20, 2016 |
| Grant date | Aug 15, 2017 |
| Priority date | — |
| Expiry date | Sep 20, 2036 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY10T29/4932
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
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 configured to effect 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 majority of the blade rows of the first turbine rotor, but does not hold true for any of the blade rows of the compressor rotor: (number of blades×rotational speed)/60≧5500, and the rotational speed being an approach speed in revolutions per minute.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.