Rotor with non-uniform blade tip clearance
US10408231B2 · kind B2 · utility
1Cited by
10References
20Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Sep 13, 2017 |
| Grant date | Sep 10, 2019 |
| Priority date | — |
| Expiry date | Feb 23, 2038 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2260/961
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A rotor for a gas turbine engine comprises a rotor having a hub and blades around the hub, and extending from the hub to tips. The tips include first and second tip portions between their respective tip leading edge and tip trailing edge. Tips are spaced from a rotational axis of the rotor by spans. A mean span of a first tip portion of a first blade is greater than a mean span of a corresponding first tip portion of a second blade. A mean span of a second tip portion the first blade is less than a mean span of a corresponding second tip portion of the second blade.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.