Invention Grant
- Patent Title: Nozzle with multi-tube fuel passageway for gas turbine engines
- Patent Title (中): 用于燃气涡轮发动机的多管燃料通道的喷嘴
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Application No.: US14164791Application Date: 2014-01-27
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Publication No.: US09562692B2Publication Date: 2017-02-07
- Inventor: Steven Williams , Timothy A. Fox , Reinhard Schilp
- Applicant: Siemens Aktiengesellschaft
- Applicant Address: DE München
- Assignee: SIEMENS AKTIENGESELLSCHAFT
- Current Assignee: SIEMENS AKTIENGESELLSCHAFT
- Current Assignee Address: DE München
- Main IPC: F23R3/34
- IPC: F23R3/34 ; F23R3/36 ; F23R3/38 ; F23R3/22 ; F23R3/28 ; F23D14/22 ; F23D14/24 ; F02C7/266 ; F23D11/38 ; F23D11/42 ; F23D3/22

Abstract:
A pilot fuel nozzle for a combustor includes an igniter forming a central body extending along a longitudinal center of the nozzle. A nozzle tip includes a plurality of circumferentially spaced fuel passages and a plurality of circumferentially spaced air passages extending to an outer side of the nozzle tip. The central body extends through a center of the nozzle tip for producing a spark to ignite a fuel/air mixture adjacent to the nozzle tip. A plurality of fuel tubes extend along the central body, each of the fuel tubes having an outlet end engaged on the nozzle tip for delivery of fuel from the nozzle tip into a combustion chamber of the combustor An outer sleeve surrounds the fuel tubes and defines an annular space in fluid communication with the air passages of the nozzle tip between the outer sleeve and the central body.
Public/Granted literature
- US20150047361A1 NOZZLE WITH MULTI-TUBE FUEL PASSAGEWAY FOR GAS TURBINE ENGINES Public/Granted day:2015-02-19
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