Return stage of a multi-staged compressor or expander with twisted guide vanes
US11073162B2 · kind B2 · utility
Assignee
Inventor
Key dates
| Filing date | Jan 9, 2018 |
| Grant date | Jul 27, 2021 |
| Priority date | — |
| Expiry date | May 18, 2038 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2250/70
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A return stage through which a process fluid is designed to flow along a throughflow direction of a radial turbomachine, wherein the return stage extends in annular fashion about an axis and is defined radially inwardly by an inner delimiting contour and radially outwardly by an outer delimiting contour. At least one guide vane stage including guide vanes extends at least along a part of the third section and segments the return stage in the circumferential direction into flow channels, wherein in each case a profile midline of a profile cross section defines an inner track on the side of the inner delimiting contour and an outer track on the side of the outer delimiting contour. A radial turbomachine includes at least one such return stage.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.