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A fuel injector arrangement for a turbine engine is disclosed. The fuel injector arrangement may have a combustion chamber, a plenum, an injector, and a premixing chamber configured to receive the injector. The premixing chamber may be at least partially disposed within the plenum and open to the co

A fuel injector arrangement for a turbine engine is disclosed. The fuel injector arrangement may have a combustion chamber, a plenum, an injector, and a premixing chamber configured to receive the injector. The premixing chamber may be at least partially disposed within the plenum and open to the combustion chamber. The premixing chamber may have at least one passageway configured to allow air from the plenum to enter and mix with fuel from the injector to form an air/fuel mixture within the premixing chamber, and a porous annular wall configured to allow air from the plenum to enter and create a lean boundary layer at the porous annular wall.

대표청구항 ▼

1. A fuel injector arrangement, comprising a combustion chamber; a plenum; an injector comprising a tubular member extending along a centerline axis of the fuel injector arrangement, the tubular member terminating at a distal tip, at least one fuel orifice formed in the distal tip; and a premixing c

1. A fuel injector arrangement, comprising a combustion chamber; a plenum; an injector comprising a tubular member extending along a centerline axis of the fuel injector arrangement, the tubular member terminating at a distal tip, at least one fuel orifice formed in the distal tip; and a premixing chamber configured to receive the injector and being at least partially disposed within the plenum and open to the combustion chamber, the premixing chamber having: a mounting member containing at least one radial to axial passageway configured to allow air from the plenum to enter and mix with fuel from the injector to form an air/fuel mixture within the premixing chamber; and an annular side wall made of porous material located downstream of the mounting member and the distal tip of the injector, configured to allow air from the plenum to enter the premixing chamber and create a lean boundary layer at the annular side wall made of porous material. 2. The fuel injector arrangement of claim 1, further including at least one vane configured to inhibit swirl of the air entering the premixing chamber from the at least one radial to axial passageway. 3. The fuel injector arrangement of claim 2, wherein the at least one vane is disposed within the at least one radial to axial passageway. 4. The fuel injector arrangement of claim 2, wherein the at least one vane is operatively connected to the injector. 5. The fuel injector arrangement of claim 2, further including a thermal insulator associated with the injector. 6. The fuel injector arrangement of claim 5, wherein the thermal insulator is an air gap. 7. The fuel injector arrangement of claim 1, wherein the air from the at least one radial to axial passageway enters the premixing chamber at a location upstream of where the fuel from the injector enters the premixing chamber. 8. The fuel injector arrangement of claim 1, wherein a velocity of the air/fuel mixture at a center of the premixing chamber is greater than a velocity of the lean boundary layer. 9. The fuel injector arrangement of claim 8, wherein a velocity of the lean boundary layer is about zero. 10. The fuel injector arrangement of claim 1, wherein the air entering the premixing chamber via the annular side wall made of porous material forces the air/fuel mixture away from the annular side wall made of porous material. 11. The fuel injector arrangement of claim 1, wherein the injector is thermally insulated. 12. The fuel injector arrangement of claim 1, wherein the at least one orifice is oriented to spray fuel radially outward into the premixing chamber. 13. The fuel injector arrangement of claim 1, wherein annular side wall the made of porous material is fabricated from one of a ceramic, metallic, or cera-metallic material. 14. The fuel injector arrangement of claim 1, wherein the lean boundary layer is incombustible. 15. The fuel injector arrangement of claim 1, wherein an equivalence ratio of the lean boundary layer is below a combustion limit for conditions existing at the lean boundary layer. 16. The fuel injector of claim 1, further including: the mounting member operatively connects the fuel injector to the plenum; andat least one cooling fin connected to the mounting member. 17. A method of mixing fuel and air within a turbine engine comprising: a fuel injector arrangement, comprising a combustion chamber; a plenum; an injector comprising a tubular member extending along a centerline axis of the fuel injector arrangement, the tubular member terminating at a distal tip, at least one fuel orifice formed in the distal tip; and a premixing chamber configured to receive the injector and being at least partially disposed within the plenum and open to the combustion chamber, the premixing chamber having: a mounting member containing at least one radial to axial passageway configured to allow air from the plenum to enter and mix with fuel from the injector to form an air/fuel mixture within the premixing chamber; and an annular side wall made of porous material located downstream of the mounting member and the distal tip of the injector, configured to allow air from the plenum to enter the premixing chamber and create a lean boundary layer at the annular side wall made of porous material, the method comprising directing fuel into the premixing chamber, directing a flow of the air into the premixing chamber to create the air fuel/mixture within the premixing chamber; allowing the air/fuel mixture to exit an open end of the premixing chamber; diffusing the air into the premixing chamber through a wall of the premixing chamber to create the lean boundary layer at the annular side wall made of porous material; and combusting the air/fuel mixture after the air/fuel mixture exits the open end of the premixing chamber. 18. The method of claim 17, further including inhibiting swirling of the flow of air directed into the chamber. 19. The method of claim 17, wherein: a velocity of the air/fuel mixture at a center of the chamber is greater than a velocity of the lean boundary layer at the wall; andan equivalence ratio of the lean boundary layer is below a combustion limit for conditions existing at the lean boundary layer. 20. A turbine engine, comprising: a compressor section configured to pressurize air; a plenum configured to receive at least a portion of the pressurized air; an open ended premixing chamber at least partially disposed within the plenum and having a radial to axial passageway located at a first end to allow a flow of pressurized air from the plenum to enter the premixing chamber, and an annular side wall made of porous material configured to allow pressurized air from the plenum to diffuse into the premixing chamber and create a lean boundary layer at the annular side wall made of porous material; a fuel injector associated with the first end of the premixing chamber, the fuel injector being configured to inject fuel that mixes with the flow of pressurized air to form an air/fuel mixture; the fuel injector having a tubular member extending along a centerline axis of the premixing chamber, the tubular member terminating at a distal tip, at least one fuel orifice formed in the distal tip, wherein the annular side wall made of porous material is located downstream of the distal tip of the fuel injector, a combustion chamber configured to receive and combust the air/fuel mixture to generate a flow of exhaust; and a turbine section configured to convert at least a portion of a thermal energy in the flow of exhaust to mechanical energy. 21. A fuel injector arrangement, comprising: a mounting member containing at least one radial to axial passageway, a plurality of cooling fins attached on the mounting member, an injector at least partially disposed within the mounting member; and a central body at least partially defined by a premixing chamber extending axially from the mounting member and being configured to receive the injector. 22. The fuel injector arrangement of claim 21, wherein the plurality of cooling elements are pin fins extending in an axial length of the premixing chamber.