GAS TURBINE ENGINE COMBUSTOR WITH OPENINGS
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United States of America Patent
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N/A
Issued Date -
Sep 26, 2024
app pub date -
May 14, 2024
filing date -
Mar 21, 2023
priority date (Note) -
Published
status (Latency Note)
Importance
Abstract
A gas turbine engine includes a compressor section, a combustor section, and a turbine section in fore-to-aft serial flow arrangement and defines an engine centerline. The combustor section includes a combustor liner at least partially defining a combustor chamber and a dome wall, coupled to the combustor liner, and defining a forward end of the combustion chamber. A fuel nozzle is located on the dome wall and fluidly coupled to the combustion chamber. A first set of compressed air openings emit compressed air into the combustion chamber along a first flow path and a second set of compressed air openings emit compressed air into the combustion chamber along a second flow path. The first and second flow paths intersect at an intersection point to form a sheet of air.
First Claim
Other Claims data not available