Gas turbine engine combustors
US5187937A · kind A · utility
17Cited by
5References
7Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Feb 19, 1991 |
| Grant date | Feb 23, 1993 |
| Priority date | — |
| Expiry date | Feb 19, 2011 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A gas turbine engine combustor, eg of annular combustor configuration, has air inlets, typically in the dilution zone, which incorporate vortex generators operative to trip the inlet jet flow causing stabilizing vortex flow at the lateral edges of the jet. The vortex generators can comprise an inwardly directed abrupt change of section between forward and rearward parts of the air inlets. The rearward section of the air inlets can have a configuration operative to reinforce the jet stabilizing effect of the vortex flow. The combustor exhibits improved uniformity of jet and crossflow mixing.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.