Turbine engine with high efficiency fuel atomization
This patent describes a gas turbine engine compressor. It comprises: a rotary compressor; a turbine wheel coupled to the compressor drive to same; an annular nozzle proximate and turbine wheel for directing gases of combustion at the turbine wheel; an annular combustor defining an annular combustion spaced disposed about the turbine wheel and in fluid communication with both the compressor and the nozzle, the combustor receiving fuel from a source and air from the compressor and combusting the same to generate the gases of combustion; fuel injectors at circumferentially spaced locations about the combustor, at least one of the fuel injectors having two discharge orifices, at least one of the fuel injectors having means for defining an elongated restricted passage of such size and length that flow of fuel through the passage will be laminar; means for defining a fuel impingement surface within the combustor and in the path of fuel discharge by the one fuel injector through either of the two discharge orifices, and fuel supply means for the fuel injectors including means for independently controlling the flow of fuel to at least one of the two discharge orifices of the one fuel injector.
- Assignee:
- Sundstrand Corp., Rockford, IL (USA)
- Patent Number(s):
- A; US 4967562
- Application Number:
- PPN: US 7-283081
- OSTI ID:
- 5628017
- Country of Publication:
- United States
- Language:
- English
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