Dual flow impeller
US6499953B1 · kind B1 · utility
13Cited by
24References
19Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Sep 29, 2000 |
| Grant date | Dec 31, 2002 |
| Priority date | — |
| Expiry date | Sep 30, 2020 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF04D29/285
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A multi-stage compressor rotor for a gas turbine engine comprises an axial-flow rotor followed by a centrifugal rotor. The axial-flow rotor and the centrifugal rotor are diffusion bonded together to form a unitary dual flow impeller having blades with continues axial-flow and centrifugal stage sections. By eliminating the gap between the axial flow and centrifugal stages, unsynchronized air deflection between the successive arrays of blades is prevented, thereby improving the aerodynamic performance of the compressor rotor.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.