High altitude starting two-stage fuel injection apparatus
US5261224A · kind A · utility
Assignee
Inventors
Key dates
| Filing date | Nov 2, 1992 |
| Grant date | Nov 16, 1993 |
| Priority date | — |
| Expiry date | Nov 2, 2012 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF23R3/346
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
Difficulties in achieving reliable starts in gas turbine engines operating at high altitude are avoided in a gas turbine engine including a rotary compressor (10), a rotary turbine wheel (12) coupled to the compressor (10) to drive the same, and a nozzle (42) for directing gases of combustion against the turbine wheel (12). An annular combustor (34) has an outlet (40) connected to the nozzle (42) and an opposed dome (38) that is axially spaced from the outlet (40). At least three sets of air injection openings (80, 92, 100) are axially spaced from one another with one set (82) in close proximity to the dome (38). Fuel injectors (86, 94) are associated with two of the sets (80, 92, 100), including the one set (80) and another of the sets (92) that is nearest the one set (80). The air injection openings of the sets (80 and 92) and the fuel injectors (86, 94) are constructed, arranged and sized so that the air/fuel ratio of air injected by each of the sets (80, 92) is no more than about 5/1 and the remaining set of air injection openings (100) is constructed, arranged and sized so that the total air/fuel ratio of air and fuel through all of the sets (80, 92, 100) and fuel injectors (8…
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.