COMBUSTOR APPARATUS
Number of patents in Portfolio can not be more than 2000
United States of America
Stats
-
N/A
Issued Date -
Nov 28, 2024
app pub date -
May 1, 2024
filing date -
May 1, 2024
priority date (Note) -
Published
status (Latency Note)
Importance
Abstract
A fuel swirl nozzle for a gas turbine engine comprises, in axial fuel flow sequence, a fuel inlet portion, a fuel stem portion, and a fuel/air swirler portion. An inlet to the fuel stem portion is fluidly sealed against the fuel inlet portion, and an outlet from the fuel stem portion is fluidly sealed against the fuel/air swirler portion. The fuel/air swirler portion has a cross-sectional profile that is generally dolioform shaped along an axis parallel to the engine's longitudinal axis, and has a first end and a second end. The first end of the fuel/air swirler portion has an air inlet face, and the second end of the fuel/air swirler portion has a fuel/air mixture outlet face. The first end comprises a rim portion enclosing the air inlet face in which the rim portion has a rim portion radius (rrim) normal to an outer circumference of the inlet face.
First Claim
Other Claims data not available