Notched gas turbine combustor cowl
US10619856B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Nov 10, 2017 |
| Grant date | Apr 14, 2020 |
| Priority date | — |
| Expiry date | Aug 31, 2038 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A gas turbine engine includes a combustion system. The combustion system may include a combustor positioned in a chamber created by an outer wall. A compressor, such as a centrifugal compressor may provide a flow of compressed air into the chamber along an inner surface of the outer wall since an inlet for the flow of compressed air is outboard of the combustor. The pressurized flow of air may be redirected by a cowl included in the chamber. The cowl may include a collar defining a notch in the cowl. The collar may redirect the flow of pressurized air so as to minimize a high velocity component of the flow of pressurized air flowing radially toward a central axis of the engine prior to entering a head of a fuel nozzle included in the combustion system.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.