Fuel nozzle for gas turbine engine combustor
Number of patents in Portfolio can not be more than 2000
United States of America Patent
Stats
-
Nov 16, 2021
Grant Date -
Jul 4, 2019
app pub date -
Jan 4, 2018
filing date -
Jan 4, 2018
priority date (Note) -
In Force
status (Latency Note)
Importance
Abstract
A method and structure for operating a combustion system of a gas turbine engine to mitigate low frequency combustion acoustics is generally provided. The method includes flowing an oxidizer through a fuel nozzle passage defining an inner wall and an outer wall, in which each of the inner wall and the outer wall are contoured from a first radius to a second radius smaller than the first radius; flowing the oxidizer at a higher axial velocity at the inner wall relative to the outer wall upstream of a fuel injection port; flowing a fuel through the fuel injection port to the fuel nozzle passage to mix with the flow of oxidizer to produce a fuel-oxidizer mixture; and igniting the fuel-oxidizer mixture downstream of the fuel injection port.
First Claim
Other Claims data not available
Family
International Classification(s)
- 2018 Application Filing Year
- F23R Class
- 333 Applications Filed
- 229 Patents Issued To-Date
- 68.77 % Issued To-Date
Cited Art Landscape
Patent Citation Ranking
- 2 Citation Count
- F23R Class
- 46 % this patent is cited more than
- 4 Age
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