Gas turbine engine flow path geometry
US9568009B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Nov 27, 2013 |
| Grant date | Feb 14, 2017 |
| Priority date | — |
| Expiry date | Aug 2, 2035 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A flow path surface of a gas turbine engine at the location of a bladed component is disclosed in which the flow path surface includes a cylindrical upstream side and a conical downstream side. The bladed component is located at the intersection of the cylindrical upstream side and the conical downstream side. The cylindrical upstream side can extend from a leading edge of the bladed component, or a point upstream of it, to a location between the leading edge and trailing edge of the component. The conical downstream side can extend past the trailing edge of the bladed component. The bladed component can be a fan blade or a compressor blade.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.