Hybrid spinner nose configuration in a gas turbine engine having a bypass duct
US5182906A · kind A · utility
Assignee
Inventors
Key dates
| Filing date | Apr 3, 1992 |
| Grant date | Feb 2, 1993 |
| Priority date | — |
| Expiry date | Apr 3, 2012 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF02C7/05
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A gas turbine engine has a forward rotor, a row of fan blades radially extending from the rotor, and a core turbine engine located rearwardly of the fan blades and rotor and coupled to the rotor for rotatably driving the rotor. An outer annular nacelle surrounds the rotor, fan blades and core engine. An inner annular splitter fairing is disposed rearwardly of the fan blades, surrounds the core engine, and is spaced radially inwardly from the nacelle so as to define therebetween a bypass air flow duct located outwardly from the core engine and rearwardly of the fan blades for producing thrust upon rotation of the rotor and fan blades. A hybrid shape spinner nose is attached about the rotor and projects forwardly therefrom within the nacelle and forwardly of the fan blades. The hybrid shape spinner nose has a forward substantially conical section spaced forwardly of the fan blades, a rearward substantially conical section projecting forwardly of and merging rearwardly with the fan blades, and a transition connecting the forward and rearward sections such that the spinner nose is provided with a compound, substantially conical configuration in which the slope of the forward substantia…
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.