Invention Application
- Patent Title: COMBUSTOR DILUTION HOLE
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Application No.: US17317131Application Date: 2021-05-11
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Publication No.: US20220364510A1Publication Date: 2022-11-17
- Inventor: Gurunath Gandikota , Varun Lakshmanan , Perumallu Vukanti , Allen M. Danis , Michael A. Benjamin
- Applicant: General Electric Company
- Applicant Address: US NY Schenectady
- Assignee: General Electric Company
- Current Assignee: General Electric Company
- Current Assignee Address: US NY Schenectady
- Main IPC: F02C7/18
- IPC: F02C7/18 ; F23R3/28 ; F02C7/22 ; F23R3/16 ; F23R3/06

Abstract:
A turbofan gas turbine engine configured to reduce hotspots within combustors. The engine includes an axis and a combustor that is circumferentially disposed about the axis. The combustor includes an annular combustor liner that includes a front portion and a rear portion. The annular combustor liner is joined to an annular combustor dome via front portion and defines a chamber and a nozzle is mounted within the annular combustor dome and is configured to inject fuel into a plurality of swirlers. At least one or more dilution openings is circumferentially distributed around the liner such that a region is fluidly connected through the annular combustor liner to the chamber. Each one of the pluralities of dilution openings includes an opening and a radial support wall that is positioned aft of the opening such that the radial support wall extends into the chamber.
Public/Granted literature
- US11572835B2 Combustor dilution hole Public/Granted day:2023-02-07
Information query
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