Gas Turbine Combustor
A gas turbine combustor includes plural multi-coaxial-injection-hole burners in which plural fuel nozzles and plural air holes provided in an air plate to correspond to the respective fuel nozzles are coaxially arranged. Each of the multi-coaxial-injection-hole burners includes a first coaxial injection burner disposed on an inner circumferential side, and a second coaxial injection burner disposed on an outer circumferential side, and a diameter of the air holes of the first coaxial injection burner is smaller than a diameter of the air holes of the second coaxial injection burner. Combustion for carrying out flame holding of a gas turbine combustor is performed by the first coaxial injection burner, and low NOx combustion of the gas turbine combustor is performed by the second coaxial injection burner.
1 . A gas turbine combustor for combusting a gasified fuel including hydrogen as its component, comprising a plurality of multi-coaxial-injection-hole burners, each of which burners includes a plurality of fuel nozzles and an air plate including a plurality of air-apertures for the respective fuel nozzles,
wherein in each of the multi-coaxial-injection-hole burners, a first part of the fuel nozzles arranged circumferentially and a first part of the air-apertures arranged circumferentially are arranged coaxially so that the fuel nozzles of the first part are for the respective air-apertures of the first part to form a first part of the multi-coaxial-injection-hole burner, a second part of the fuel nozzles arranged circumferentially and a second part of the air-apertures arranged circumferentially are arranged coaxially so that the fuel nozzles of the second part are for the respective air-apertures of the second part to form a second part of the multi-coaxial-injection-hole burner surrounding coaxially the first part of the multi-coaxial-injection-hole burner, and a cross-sectional area of each of the air-apertures in the first part of the multi-coaxial-injection-hole burner is smaller than a cross-sectional area of each of the air-apertures in the second part of the multi-coaxial-injection-hole burner, so that the first part of the multi-coaxial-injection-hole burner keeps a flame of the gas turbine combustor and the second part of the multi-coaxial-injection-hole burner performs low NOx combustion.
2 . The gas turbine combustor according to claim 1 , wherein when the cross-sectional area of each of the air-apertures in the first part of the multi-coaxial-injection-hole burner is D 1 , a total number of the air-apertures in the first part of the multi-coaxial-injection-hole burner is N 1 , the cross-sectional area of each of the air-apertures in the second part of the multi-coaxial-injection-hole burner is D 2 , a total number of the air-apertures in the second part of the multi-coaxial-injection-hole burner is N 2 , and a base of natural logarithm is e, the following formula
D
1
D
2
≈
(
N
2
N
1
)
π
2
2
e
1
+
(
N
2
N
1
)
2
is satisfied.
3 . The gas turbine combustor according to claim 1 , wherein a third part of the fuel nozzles arranged circumferentially and a third part of the air-apertures arranged circumferentially are arranged coaxially so that the fuel nozzles of the third part are for the respective air-apertures of the third part to form a third part of the multi-coaxial-injection-hole burner surrounding coaxially the second part of the multi-coaxial-injection-hole burner, so that the first part of the multi-coaxial-injection-hole burner keeps the flame of the gas turbine combustor and the second and third parts of the multi-coaxial-injection-hole burner perform the low NOx combustion.
4 . A gas turbine combustor for combusting a gasified fuel including hydrogen as its component, comprising a plurality of multi-coaxial-injection-hole burners, each of which burners includes a plurality of fuel nozzles and an air plate including a plurality of air-apertures for the respective fuel nozzles,
wherein in each of the multi-coaxial-injection-hole burners, an i th row of the fuel nozzles arranged circumferentially and an i th row of the air-apertures arranged circumferentially are arranged coaxially so that the fuel nozzles of the i th row are for the respective air-apertures of the i th row to form an i th row of the multi-coaxial-injection-hole burner, an (i+1) th row of the fuel nozzles arranged circumferentially and an (i+1) th row of the air-apertures arranged circumferentially are arranged coaxially so that the fuel nozzles of the (i+1) th row are for the respective air-apertures of the (i+1) th row to form an (i+1) th row of the multi-coaxial-injection-hole burner surrounding coaxially the i th row of the multi-coaxial-injection-hole burner, so that the i th row of the multi-coaxial-injection-hole burner keeps a flame of the gas turbine combustor and the (i+1) th row of the multi-coaxial-injection-hole burner performs low NOx combustion,
and when a cross-sectional area of each of the air-apertures in the i th row of the multi-coaxial-injection-hole burner is D 1 , a total number of the air-apertures in the i th row of the multi-coaxial-injection-hole burner is N 1 , a cross-sectional area of each of the air-apertures in the (i+1) th row of the multi-coaxial-injection-hole burner is D t+1 , a total number of the air-apertures in the (i+1) th row of the multi-coaxial-injection-hole burner is N 1 +1, a base of natural logarithm is e, and i is one of 1, 2, 3 and 4, the following formula
D
i
D
i
+
1
≈
π
·
(
N
i
+
1
N
i
)
π
2
2
e
·
{
1
+
(
N
i
+
1
N
i
)
2
}
is satisfied.
5 . The gas turbine combustor according to claim 1 , wherein the air-apertures arranged circumferentially are distributed along an imaginary circumferential line, and a central axis of each of the air-apertures arranged circumferentially extends in a respective tangential direction of the imaginary circumferential line.
6 . The gas turbine combustor according to claim 5 , wherein the central axis of each of the air-apertures arranged circumferentially extends in a respective radial direction of the imaginary circumferential line to urge the air radially inward.
7 . The gas turbine combustor according to claim 4 , wherein the air-apertures of each of the i th row and the (i+1) th row arranged circumferentially are distributed along an imaginary circumferential line, and a central axis of each of the air-apertures of each of the i th row and the (i+1) th row extends in a respective tangential direction of the imaginary circumferential line.
8 . The gas turbine combustor according to claim 7 , wherein the central axis of each of the air-apertures of each of the i th row and the (i+1) th row extends in a respective radial direction of the imaginary circumferential line to urge the air radially inward.
9 . A gas turbine combustor for combusting a gasified fuel including hydrogen as its component, comprising a plurality of multi-coaxial-injection-hole burners, each of which burners includes a plurality of fuel nozzles and an air plate including a plurality of air-apertures for the respective fuel nozzles,
wherein the air plate includes a protrusion of one of cone-shape and truncated-cone-shape protruding at an outlet side of the air plate from which outlet side a mixture of the fuel and an air discharged, and
in each of the multi-coaxial-injection-hole burners, a first part of the fuel nozzles arranged circumferentially and a first part of the air-apertures arranged circumferentially are arranged coaxially so that the fuel nozzles of the first part are for the respective air-apertures of the first part to form a first part of the multi-coaxial-injection-hole burner surrounding the protrusion, a second part of the fuel nozzles arranged circumferentially and a second part of the air-apertures arranged circumferentially are arranged coaxially so that the fuel nozzles of the second part are for the respective air-apertures of the second part to form a second part of the multi-coaxial-injection-hole burner surrounding coaxially the first part of the multi-coaxial-injection-hole burner, a third part of the fuel nozzles arranged circumferentially and a third part of the air-apertures arranged circumferentially are arranged coaxially so that the fuel nozzles of the third part are for the respective air-apertures of the third part to form a third part of the multi-coaxial-injection-hole burner surrounding coaxially the second part of the multi-coaxial-injection-hole burner, a cross-sectional area of each of the air-apertures in the first part of the multi-coaxial-injection-hole burner is smaller than a cross-sectional area of each of the air-apertures in the second part of the multi-coaxial-injection-hole burner, and a cross-sectional area of each of the air-apertures in the second part of the multi-coaxial-injection-hole burner is smaller than a cross-sectional area of each of the air-apertures in the third part of the multi-coaxial-injection-hole burner, so that the first part of the multi-coaxial-injection-hole burner keeps a flame of the gas turbine combustor and the second and third parts of the multi-coaxial-injection-hole burner performs low NOx combustion.
10 . The gas turbine combustor according to claim 9 , wherein the air-apertures arranged circumferentially are distributed along an imaginary circumferential line, and a central axis of each of the air-apertures arranged circumferentially extends in a respective tangential direction of the imaginary circumferential line.
11 . The gas turbine combustor according to claim 10 , wherein the central axis of each of the air-apertures arranged circumferentially extends in a respective radial direction of the imaginary circumferential line to urge the air radially inward.