Fuel nozzle for gas turbine engine

Patent · Tue Sep 02 04:00:00 EDT 1986

OSTI ID:5231357

Pane, Jr, F C; Matthews, J A; Wright, R R; Sarnik, J M; Frasca, T

A fuel nozzle for a gas turbine engine is described including a single casted support member having a radially extending base portion and an axially extending portion, a fuel passageway in the casted support member extending from the base portion to the end of the axial extending portion with a smooth radius turn from the radially extending portion to the axial extending portion and a transition from the turn from a circular to an annular cross section, a single casted head portion including a first frustoconically shaped inner member having an annular fuel swirler orifice formed therein connected in flow relationship with the fuel passageway, a second frustoconically shaped outer member spaced from and surrounding the frustoconically shaped inner member being supported thereto by circumferentially disposed vanes therebetween and defining with the end of the axially extending portion a fuel passage connected in flow relationship to the fuel swirler office. The end of the first frustoconically shaped inner member defines a film lip, means for joining the head portion at the end remote from the film lip to the single casted support member at a juncture adjacent the fuel orifice, and an open ended axial flow passageway for conducting air therethrough.

• Assignee: United Technologies Corp., Hartford, CT
• Patent Number(s): US 4609150
• OSTI ID: 5231357
• Country of Publication: United States
• Language: English

Related Subjects

33 ADVANCED PROPULSION SYSTEMS
330103* -- Internal Combustion Engines-- Turbine
AIR FLOW
AUTOMOTIVE FUELS
ENGINES
FLUID FLOW
FUELS
GAS FLOW
GAS TURBINE ENGINES
HEAT ENGINES
INTERNAL COMBUSTION ENGINES
MECHANICAL STRUCTURES
NOZZLES
OPENINGS
ORIFICES
SPACE DEPENDENCE
SUPPORTS
VORTEX FLOW