Gas turbine engine with anti-icing facility
US4129984A · kind A · utility
Assignee
Inventor
Key dates
| Filing date | May 25, 1977 |
| Grant date | Dec 19, 1978 |
| Priority date | — |
| Expiry date | May 25, 1997 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY10T137/0536
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
The disclosure of this invention pertains to a gas turbine engine with anti-icing facility. The engine has an axial flow compressor having a rotor hub provided at its upstream end with a nose for dividing the air stream into the compressor. The nose has a pointed conical upstream part of limited angle of divergence where ice formation is minimal. The conical part is followed by a toroidally surfaced concave intermediate part defining a transition from the downstream end of the conical part toward the relatively longer diameter of the hub. The increasing angle of divergence of the intermediate part is progressively more prone to ice formation but is also progressively, more able to throw off the ice by centrifugal force. A convex toroidal part forms a surface blending the intermediate part to the hub.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.