Centripetal accelerator for air exhaustion in a cooling device of a gas turbine combined with the compressor disc
US4595339A · kind A · utility
Assignee
Inventor
Key dates
| Filing date | Sep 6, 1984 |
| Grant date | Jun 17, 1986 |
| Priority date | — |
| Expiry date | Sep 6, 2004 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF04D29/321
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A compressor disc assembly with an integral centripetal accelerator for the exhaustion of air for use in a cooling device of a gas turbine, the bleeding of air at the surface of the compressor drum being effected by orifices situated in the platforms of the blades and in the median plane of the compressor disc. The assembly is formed from two half discs. The centripetal accelerator includes several sectors detachably mounted in the space defined between the two half discs of the compressor, each sector being formed from two half shells having on their internal face ribs in the form of centripetal blades by which the half shells are assembled together. The invention is utilized for cooling a gas turbine by bleeding air from the compressor.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.