Injection nozzle, combustor including same nozzle, and gas turbine including same combustor

1. An injection nozzle for injecting fuel and compressed air into a combustion chamber of a combustor of a gas turbine, the injection nozzle comprising:

an inlet portion receiving the fuel and a first portion of the compressed air;

an outlet portion located downstream of the inlet portion in a flow direction of a mixture of the fuel and compressed air, and configured to discharge the mixture of the fuel and the compressed air to the combustion chamber; and

an intermediate portion obliquely installed between the inlet portion and the outlet portion and connected to each of the inlet portion at an upstream end of the intermediate portion relative to the flow direction and the outlet portion at a downstream end of the intermediate portion relative to the flow direction, wherein a centerline of the intermediate portion extends from the upstream end of the intermediate portion to the downstream end of the intermediate portion,

an auxiliary supply unit installed in the inlet portion to supply an auxiliary air to the intermediate portion, the auxiliary air being a second portion of the compressed air; and

a sealing unit obliquely installed in the intermediate portion and connected to the auxiliary supply unit to seal the auxiliary supply unit at a downstream end of the auxiliary supply unit relative to the flow direction,

wherein a plurality of intermediate walls form the intermediate portion and the plurality of intermediate walls comprise a first intermediate wall located at a first side of the centerline of the intermediate portion and a second intermediate wall located at a second side of the centerline of the intermediate portion opposite to the first intermediate wall, and

a plurality of outlet walls form the outlet portion and the plurality of outlet walls comprise a first outlet wall extending from the first intermediate wall and a second outlet wall extending from the second intermediate wall, and

a plurality of sealing walls form the sealing unity and the plurality of sealing walls comprise a first sealing wall facing to the first intermediate wall and a second sealing wall facing to the second intermediate wall, and

an angle A is defined as an angle between a first extension line extending from the first outlet wall and the first intermediate wall,

an angle B is defined as an angle between the second outlet wall and the second intermediate wall,

an angle C is defined as an angle between a second extension line extending from the second outlet wall and the second sealing wall,

an angle D is defined as an angle between the first outlet wall and a third extension line extending from the first sealing wall,

an angle A is larger than the angle D and the angle B is larger than the angle C.

2. The injection nozzle according to claim 1 , wherein an inner width of the intermediate portion increases toward the downstream end of the intermediate portion relative to the flow direction.

3. The injection nozzle according to claim 1 , wherein

a third intermediate wall of the plurality of intermediate walls is located at a third side of the centerline of the intermediate portion and connected to each of the first intermediate wall and the second intermediate wall;

a fourth intermediate wall of the plurality of intermediate walls is located at a fourth side of the centerline of the intermediate portion opposite to the third intermediate wall and connected to each of the first intermediate wall and the second intermediate wall;

the intermediate portion is formed such that a first inner width between the first intermediate wall and the second intermediate wall increases towards the downstream end of the intermediate portion relative to the flow direction and a second inner width between the third intermediate wall and the fourth intermediate wall is constant or decreases toward the downstream end of the intermediate portion relative to the flow direction.

4. The injection nozzle according to claim 1 , wherein an angle E is defined as an angle between the second extension line extending from the second outlet wall and the second intermediate wall, and the angle A is larger than the angle E.

5. The injection nozzle according to claim 1 , wherein

a third intermediate wall of the plurality of intermediate walls is located at a third side of the centerline of the intermediate portion and connected to each of the first intermediate wall and the second intermediate wall;

a fourth intermediate wall of the plurality of intermediate walls is located at a fourth side of the centerline of the intermediate portion opposite to the third intermediate wall and connected to each of the first intermediate wall and the second intermediate wall;

a first width between the first sealing wall and the first intermediate wall increases toward the downstream end of the intermediate portion relative to the flow direction, and a second width between the third intermediate wall and the fourth intermediate wall is constant or decreases toward the downstream end of the intermediate portion relative to the flow direction, and

a third width between the second sealing wall and the second intermediate wall increases toward the downstream end of the intermediate portion relative to the flow direction.

6. The injection nozzle according to claim 1 , wherein

the auxiliary supply unit includes a plurality of auxiliary supply units arranged spaced apart from each other, and

the sealing unit includes a plurality of sealing units arranged spaced apart from each other.

7. The injection nozzle according to claim 1 , wherein both of the intermediate portion and the sealing unit are inclined from the inlet portion toward a same direction relative to the flow direction.

8. A combustor comprising:

a nozzle casing configured to receive compressed air from a compressor and to receive fuel from an outside;

a liner located downstream of the nozzle casing in a flow direction of a mixture of the fuel and the compressed air, and defining a combustion chamber in which the mixture of the fuel and the compressed air is combusted;

a transition piece located downstream of the liner relative to the flow direction and configured to supply combustion gas generated in the combustion chamber to a turbine; and

an injection nozzle located in the nozzle casing to inject the mixture of the fuel and the compressed air into the combustion chamber,

wherein the injection nozzle comprises:

an inlet portion receiving the fuel and a portion of the compressed air;

an outlet portion located downstream of the inlet portion in the flow direction and configured to discharge the mixture of the fuel and the compressed air to the combustion chamber; and

an intermediate portion obliquely installed between the inlet portion and the outlet portion and connected to each of the inlet portion at an upstream end of the intermediate portion relative to the flow direction and the outlet portion at a downstream end of the intermediate portion relative to the flow direction, wherein a centerline of the intermediate portion extends from the upstream end of the intermediate portion to the downstream end of the intermediate portion,

an auxiliary supply unit installed in the inlet portion to supply an auxiliary air to the intermediate portion, the auxiliary air being a second portion of the compressed air; and

a sealing unit obliquely installed in the intermediate portion and connected to the auxiliary supply unit to seal the auxiliary supply unit at a downstream end of the auxiliary supply unit relative to the flow direction,

wherein a plurality of intermediate walls form the intermediate portion and the plurality of intermediate walls comprise a first intermediate wall and a second intermediate wall located opposite to the first intermediate wall, and

a plurality of outlet walls form the outlet portion and the plurality of outlet walls comprise a first outlet wall extending from the first intermediate wall and the second outlet wall extending from the second intermediate wall,

an angle X is defined as an angle between a first extension line extending from the first outlet wall and the first intermediate wall and an angle Y is defined as an angle between a second extension line extending from the second outlet wall and the second intermediate wall, and the angle X is larger than the angle Y.

9. The combustor according to claim 8 , wherein an inner width of the intermediate portion increases toward a downstream end of the intermediate portion relative to the flow direction.

10. The combustor according to claim 8 , wherein

the first intermediate wall is located at a first side of the centerline of the intermediate portion and the second intermediate wall is located at a second side of the centerline of the intermediate portion opposite to the first intermediate wall,

a third intermediate wall of the plurality of intermediate walls is located at a third side of the centerline of the intermediate portion and connected to each of the first intermediate wall and the second intermediate wall,

a fourth intermediate wall of the plurality of intermediate walls is located at a fourth side of the centerline of the intermediate portion opposite to the third intermediate wall and connected to each of the first intermediate wall and the second intermediate wall,

the intermediate portion is formed such that a first inner width between the first intermediate wall and the second intermediate wall increases toward the downstream end of the intermediate portion relative to the flow direction and a second inner width between the third intermediate wall and the fourth intermediate wall is constant or decreased toward the downstream end of the intermediate portion relative to the flow direction.

11. The combustor according to claim 8 , wherein

the auxiliary supply unit includes a plurality of auxiliary supply units arranged space apart from each other, and the sealing unit includes a plurality of sealing units arranged spaced apart from each other.

12. A gas turbine comprising:

a compressor configured to take in air and to compress the air;

a combustor configured to mix fuel with compressed air supplied from the compressor and combust the mixture of the fuel and the compressed air in a combustion chamber to produce combustion gas; and

a turbine rotated by the combustion gas to generate electric power,

wherein the combustor comprises:

a nozzle casing;

a liner located downstream of the nozzle casing in a flow direction of the mixture of the fuel and the compressed air, and defining the combustion chamber,

a transition piece located downstream of the liner relative to the flow direction and configured to supply the combustion gas to the turbine; and

an injection nozzle located in the nozzle casing to inject the mixture of the fuel and the compressed air into the combustion chamber,

wherein the injection nozzle comprises:

an inlet portion receiving the fuel and a first portion of the compressed air;

an outlet portion located downstream of the inlet portion in the flow direction and configured to discharge the mixture of the fuel and the compressed air to the combustion chamber; and

an intermediate portion obliquely installed between the inlet portion and the outlet portion and connected to each of the inlet portion at the upstream end of the intermediate portion relative to the flow direction and the outlet portion at a downstream end of the intermediate portion relative to the flow direction, wherein a centerline of the intermediate portion extends from the upstream end of the intermediate portion to the downstream end of the intermediate portion,

an auxiliary supply unit installed in the inlet portion to supply an auxiliary air to the intermediate portion, the auxiliary air being a second portion of the compressed air; and

a sealing unit obliquely installed in the intermediate portion and connected to the auxiliary supply unit to seal the auxiliary supply unit at a downstream end of the auxiliary supply unit relative to the flow direction,

wherein a plurality of intermediate walls form the intermediate portion and the plurality of intermediate walls comprise a first intermediate wall and a second intermediate wall located opposite to the first intermediate wall, and

a plurality of outlet walls form the outlet portion and the plurality of outlet walls comprise a first outlet wall extending from the first intermediate wall and a second outlet wall extending from the second intermediate wall, and

an angle X is defined as an angle between a first extension line extending from the first outlet wall and the first intermediate wall and an angle Y is defined as an angle between a second extension line extending from the second outlet wall and the second intermediate wall, and the angle X is larger than angle Y.