Pre-mixing injection system for a turbojet engine
US5592819A · kind A · utility
Assignee
Inventors
Key dates
| Filing date | Mar 8, 1995 |
| Grant date | Jan 14, 1997 |
| Priority date | — |
| Expiry date | Mar 8, 2015 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A pre-mixing injection system to feed a fuel/air mixture to a combustion zone in a turbojet engine combustion chamber is disclosed having a pre-mixing tube defining a convergent pre-mixing zone and a diverging intermediate zone between the fuel and air injection devices, and the combustion zone of the combustion chamber. The convergent pre-mixing zone has an inlet adjacent to the fuel injector and air swirlers to accept the fuel/air mixture into the pre-mixing tube. The pre-mixing zone converges in a direction from the inlet to an outlet which is in communication with the inlet of the divergent intermediate zone. The divergent intermediate zone has an outlet which is, in turn, in communication with the combustion zone of the turbojet engine combustion chamber. The divergent intermediate zone is defined by an inner wall and an outer wall spaced from the inner wall so as to define a generally frusto-conical chamber between them. The outer wall has a plurality of cooling holes to enable cooling air to pass through the outer wall into cooling contact with the inner wall. The frusto-conical chamber has a downstream evacuation passage to allow cooling air to pass from the frusto-conical …
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.