FIELD: agitation.
SUBSTANCE: invention relates to gas turbine units, in particular to fuel injectors with an inner premix tube air wipe. Inner premix tube for a fuel injector of a gas turbine engine includes a transition end, a tip end, and a premix tube inner surface. Transition end includes an annular disk portion and a redirection portion extending radially inward and axially from the annular disk portion. Transition end also includes a plurality of wipe passages extending through the transition end. Tip end includes a cylindrical portion with a hollow right circular cylinder shape. Premix tube inner surface is a radially outer surface including the redirection portion outer surface and the cylindrical portion outer surface. Fuel injector of a gas turbine engine and a method of overhaul thereof are also provided.
EFFECT: wipe passages are configured to direct air along the premix tube inner surface pushing the fuel off the premix tube inner surface and preventing fuel from accumulating on the premix tube inner surface, which may prevent or reduce the coking, auto ignition, flash back or flame holding.
10 cl, 6 dwg
Title | Year | Author | Number |
---|---|---|---|
OUTER PREMIX BARREL VENT AIR SWEEP | 2014 |
|
RU2657080C2 |
TAPERED GAS TURBINE ENGINE LIQUID GALLERY | 2014 |
|
RU2664904C2 |
SHROUDED PILOT LIQUID TUBE | 2014 |
|
RU2657075C2 |
GAS TURBINE ENGINE WITH FUEL INJECTOR EQUIPPED WITH INNER HEAT SHIELD | 2015 |
|
RU2672205C2 |
HEAT-INSULATED FUEL ATOMISER FOR GAS TURBINE ENGINE | 2015 |
|
RU2696158C2 |
COMBUSTION CHAMBER SPACER RING WITH CONTROLLED AIR PASSAGE | 2016 |
|
RU2707355C2 |
FUEL INJECTOR WITH GAS DISTRIBUTION THROUGH PLURALITY OF TUBES | 2016 |
|
RU2721627C2 |
FUEL INJECTOR WITH DOUBLE INJECTION OF MAIN FUEL | 2016 |
|
RU2719131C2 |
GAS TURBINE ENGINE COMPRESSOR ROTOR ASSEMBLY WITH BALANCING SYSTEM | 2013 |
|
RU2660981C2 |
FILTER ELEMENT WITH END CAP ASSEMBLY AND CAST GASKET | 2020 |
|
RU2783390C1 |
Authors
Dates
2018-06-08—Published
2014-05-02—Filed