Small airblast fuel nozzle with high efficiency inner air swirler
This patent describes a airblast fuel nozzle for a gas turbine engine. It comprises: a nozzle body having a longitudinal inner air swirl chamber with a downstream discharge orifice, means for discharging fuel from the nozzle body and a plurality of air inlet passages circumferentially spaced apart around the nozzle body upstream of the fuel discharge orifice and extending from the inner air swirl chamber to the exterior of the nozzle body for receiving air flow, each air inlet passage having an inner section converging toward and intersecting with the inner air swirl chamber and an outer section converging toward and intersecting with the inner section, the inner section having an outlet communicating with the inner air swirl chamber and an inlet communicating with the outer section, the outer section having an outlet communicating with the inlet of the inner section and an inlet on the exterior of the nozzle body for receiving the air flow, the convergence of the outer section and inner section being selected to provide an effective air flow area through the outer section greater than the effective air flow area through the inner section, the inner section and outer section of each air inlet passage being relatively canted in the same circumferential direction and oriented relative to the air swirl chamber to, in effect, provide a distance X between centerlines of the air swirl chamber and the inner section that increases the air swirl strength achievable in the air swirl chamber at a given air pressure value at the inlet of the outer section.
- Assignee:
- Fuel Systems Textron Inc., Zeeland, MI (United States)
- Patent Number(s):
- US 5086979; A
- Application Number:
- PPN: US 7-376751
- OSTI ID:
- 5278955
- Resource Relation:
- Patent File Date: 7 Jul 1989
- Country of Publication:
- United States
- Language:
- English
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