| CPC F23R 3/286 (2013.01) [F02C 7/222 (2013.01); F23R 3/045 (2013.01); F23R 3/14 (2013.01); F23D 14/62 (2013.01)] | 18 Claims |
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1. A combustor nozzle comprising:
at least one cluster composed of a plurality of tubes, wherein each of the at least one cluster comprises:
a main tube, from among the plurality of tubes, through which air and fuel flow, the main tube having an axial height and defining an axial direction from upstream to downstream according to a flow direction of the air and the fuel through the main tube;
a plurality of sub-tubes, from among the plurality of tubes, arranged with a circumferential pattern to form a circumference, wherein the main tube is located at a center of the circumference;
a fuel supply part including a fuel conduit extending parallel to the axial direction and a plurality of wing parts radially protruding from the fuel conduit;
wherein, for each of the at least one cluster, at least a portion of the fuel conduit is positioned inside the main tube to supply the fuel,
wherein a total count of the fuel supply part in each of the at least one cluster is one,
wherein, for each of the at least one cluster, each of the plurality of wing parts has a radially inward end that is coupled to the fuel conduit and a radially outward end that is in contact with an inner peripheral surface of the main tube,
wherein, for each of the at least one cluster, each of the plurality of wing parts has an upstream half portion and a downstream half portion,
wherein, for each of the plurality of wing parts in each of the at least one cluster, an upstream end corner of the upstream half portion and a downstream end corner of the downstream half portion are formed round,
wherein, for each of the plurality of wing parts in each of the at least one cluster, a thickness of the upstream half portion is defined in a circumferential direction about the fuel conduit and comprises a first maximum thickness T1, and the first maximum thickness T1 remains constant for a height of the upstream half portion in the axial direction,
wherein, for each of the plurality of wing parts in each of the at least one cluster, a thickness of the downstream half portion is defined in the circumferential direction and the thickness gradually increases from upstream to downstream over a height of the downstream half portion in the axial direction, such that a concavely curved surface is formed on an outer circumferentially facing surface of the downstream half portion,
wherein, for each of the plurality of wing parts in each of the at least one cluster, the first maximum thickness T1 of the upstream half portion occurs at a first axial location P1, the thickness of the downstream half portion comprises a second maximum thickness T2 at a second axial location P2, and the first maximum thickness T1 is smaller than the second maximum thickness T2, such that, at the first axial location P1, the radially inward end of each wing part of the plurality of wing parts is spaced apart in the circumferential direction from the radially inward end of an adjacent wing part of the plurality of wing parts, and at the second axial location P2, the radially inward end of each wing part of the plurality of wing parts is in contact with the radially inward end of the adjacent wing part of the plurality of wing parts in the circumferential direction.
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