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A fuel/air mixing disk for use in a fuel/air mixing combustor assembly is provided. The disk includes a first face, a second face, and at least one fuel plenum disposed therebetween. A plurality of fuel/air mixing tubes extend through the pre-mixing disk, each mixing tube including an outer tube wal

A fuel/air mixing disk for use in a fuel/air mixing combustor assembly is provided. The disk includes a first face, a second face, and at least one fuel plenum disposed therebetween. A plurality of fuel/air mixing tubes extend through the pre-mixing disk, each mixing tube including an outer tube wall extending axially along a tube axis and in fluid communication with the at least one fuel plenum. At least a portion of the plurality of fuel/air mixing tubes further includes at least one fuel injection hole have a fuel injection hole diameter extending through said outer tube wall, the fuel injection hole having an injection angle relative to the tube axis. The invention provides good fuel air mixing with low combustion generated NOx and low flow pressure loss translating to a high gas turbine efficiency, that is durable, and resistant to flame holding and flash back.

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1. A fuel/air mixing disk for use in a fuel/air mixing combustor assembly comprising: a plurality of adjacent, pie-shaped sectors, each sector having a first face, a second face, and an annular wall coupling the first and second faces together and separating the first and second faces to provide at

1. A fuel/air mixing disk for use in a fuel/air mixing combustor assembly comprising: a plurality of adjacent, pie-shaped sectors, each sector having a first face, a second face, and an annular wall coupling the first and second faces together and separating the first and second faces to provide at least one fuel plenum disposed between the first and second faces and bounded by the annular wall and adapted to be in fluid communication with a fuel flow passage extending from an end cover of the combustor assembly transverse to the first face and intersecting the first face at a central position of at least one sector of the disk away from the annular wall; anda plurality of fuel/air mixing tubes extending through each sector between the first face and the second face, each mixing tube including an outer tube wall extending axially along a tube axis between an inlet end and an exit end and in fluid communication with the at least one fuel plenum, each mixing tube being attached at its respective inlet end to the first face and at its respective outlet end to the second face,at least a portion of the plurality of fuel/air mixing tubes further including at least one fuel injection hole having a fuel injection hole diameter extending through said outer tube wall, said at least one fuel injection hole having an injection angle relative to said tube axis, said injection angle being in the range of 20 to 90 degrees, andwherein a recession distance between said fuel injection hole and said exit end along said tube axis is about 5 to 100 times greater than said fuel injection hole diameter. 2. The fuel/air mixing disk of claim 1, wherein said recession distance is equal to or less than 1.5 inches and said tube diameter is in the range of 0.05 and 0.3 inches. 3. The fuel/air mixing disk of claim 1, wherein the recession distance is in the range of 0.3 to 1 inches and said tube diameter is in the range of 0.05 and 0.3 inches. 4. The fuel/air mixing disk of claim 3, wherein the fuel injection hole diameter of said at least one fuel injection hole is equal to or less than 0.03 inches. 5. The fuel/air mixing disk of claim 1, wherein said injection angle is about 50 to 60 degrees measured with respect to the tube axial direction. 6. The fuel/air mixing disk of claim 1, comprising a plurality of fuel injection holes having a plurality of fuel injection hole diameters. 7. The fuel/air mixing disk of claim 1, comprising a plurality of fuel injection holes having a plurality of fuel injection hole angles. 8. The fuel/air mixing disk of claim 7, wherein said plurality of fuel injection holes comprises about 2 to 8 fuel injection holes. 9. The fuel/air mixing disk of claim 1, wherein the inlet end of at least a portion of the fuel/air mixing tubes includes a tapered geometry. 10. The fuel/air mixing disk of claim 1, wherein each sector has an individual fuel inlet port. 11. The fuel/air mixing disk of claim 1, wherein the at least one fuel plenum includes a plurality of cavities separated by a flow conditioner. 12. A fuel/air mixing disk for use in a fuel/air premixing combustor assembly comprising: a plurality of adjacent, pie-shaped sectors, each sector having a first face, a second face, and an annular wall coupling the first and second faces together and separating the first and second faces to provide at least one fuel plenum disposed between the first and second faces and bounded by the annular wall and adapted to be in fluid communication with a fuel flow passage extending from an end cover of the combustor assembly transverse to the first face and intersecting the first face at a central position of at least one sector of the disk away from the annular wall; anda plurality of fuel/air mixing tubes extending through each sector between the first face and the second face, each mixing tube including an outer tube wall extending axially along a tube axis between an inlet end and an exit end and in fluid communication with the at least one fuel plenum, and an inner tube surface having an inner diameter,each of the plurality of fuel/air mixing tubes further including at least one fuel injection hole having a fuel injection hole diameter extending through said outer tube wall, said at least one fuel injection hole having an injection angle relative to said tube axis, said inner diameter of said inner tube surface being from 2 to 20 times greater than said fuel injection hole diameter, andwherein a recession distance between said fuel injection hole and said exit end along said tube axis is about 1 to 100 times greater than said fuel injection hole diameter. 13. The fuel/air mixing disk of claim 12, wherein said injection angle being in the range of 20 and 90 degrees. 14. The fuel/air mixing disk of claim 12, wherein said fuel injection hole diameter is about equal to or less than 0.03 inches. 15. The fuel/air mixing disk of claim 12, further comprising a recession distance extending between said fuel injection hole and said exit end along said tube axis, said recession distance being between 5 to 100 times greater than said fuel injection hole diameter. 16. The fuel/air mixing disk of claim 15, wherein said inner diameter of said inner tube surface is less than 0.2 inches. 17. The fuel/air mixing disk of claim 12, wherein each sector has an individual fuel inlet port. 18. A method of mixing high-hydrogen or synthetic gas fuel in a premixed direct injection disk for a turbine combustor, said method comprising; providing a plurality of adjacent, pie-shaped sectors, each sector having a first face, a second face, and an annular wall coupling the first and second faces together and separating the first and second faces to provide at least one fuel plenum disposed between the first and second faces and bounded by the annular wall and adapted to be in fluid communication with a fuel flow passage extending from an end cover of the combustor assembly transverse to the first face and intersecting the first face at a central position of at least one sector of the disk away from the annular wall;wherein each sector further comprises fuel/air mixing tubes extending between the first face and the second face, each of said plurality of mixing tubes extending axially along a flow path between an inlet end and an exit end and having at least one injection hole in fluid communication with the at least one fuel plenum, said at least one injection hole being oriented at an angle in the range of 20 to 90 degrees relative to a tube axis, each of said plurality of tubes including an outer tube wall extending axially along a tube axis between said inlet end and said exit end;injecting a first fluid into said plurality of mixing tubes at said inlet end;providing a gaseous high-hydrogen fuel or a gaseous synthetic fuel into said at least one fuel plenum;injecting the high-hydrogen fuel or synthetic fuel from the at least one fuel plenum into said mixing tubes through the plurality of injection holes; andmixing said first fluid and said high hydrogen fuel or synthetic fuel to a mixedness of greater than 50% fuel and first fluid mixture at said exit end of said tubes. 19. The method of claim 18, wherein said mixedness occurs at a location between 0.6 and 0.8 inches downstream of said fuel injection holes. 20. The method of claim 18, wherein each tube comprises within the range of about 1 to 8 fuel injection holes.