Geared turbofan engine having a reduced number of fan blades and improved acoustics
US10184340B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Feb 21, 2014 |
| Grant date | Jan 22, 2019 |
| Priority date | — |
| Expiry date | Oct 8, 2035 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A rotor blade comprises an airfoil extending radially from a root section to a tip section and axially from a leading edge to a trailing edge, the leading and trailing edges defining a curvature therebetween. The curvature determines a relative exit angle at a relative span height between the root section and the tip section, based on an incident flow velocity at the leading edge of the airfoil and a rotational velocity at the relative span height. In operation of the rotor blade, the relative exit angle determines a substantially flat exit pressure ratio profile for relative span heights from 75% to 95%, wherein the exit pressure ratio profile is constant within a tolerance of 10% of a maximum value of the exit pressure ratio profile.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.