Invention Grant
- Patent Title: Fuel nozzle for gas turbine engine combustor
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Application No.: US15861791Application Date: 2018-01-04
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Publication No.: US11175045B2Publication Date: 2021-11-16
- Inventor: Michael Anthony Benjamin , Girish Venkata Satya Sesha Goda , Habeeb Kunnummal Manat , Karthikeyan Sampath
- Applicant: General Electric Company
- Applicant Address: US NY Schenectady
- Assignee: General Electric Company
- Current Assignee: General Electric Company
- Current Assignee Address: US NY Schenectady
- Agency: Venable LLP
- Agent Edward A. Kmett; Michele V. Frank
- Main IPC: F23R3/28
- IPC: F23R3/28 ; F23R3/10 ; F23R3/18 ; F23R3/14 ; F23C7/00 ; F23R3/34

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.
Public/Granted literature
- US20190203929A1 Fuel Nozzle for Gas Turbine Engine Combustor Public/Granted day:2019-07-04
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