GAS TURBINE COMBUSTOR
A gas turbine combustor comprising a burner including: a plurality of fuel nozzles to supply a fuel; a fuel nozzle plate to supports end portions of the fuel nozzles structurally and being configured to distribute the fuel flowing from an upstream side to the fuel nozzles; and a swirler including a plurality of air holes to supply combustion air, characterized in that the fuel nozzle plate is provided with a fuel nozzle receiving hole to receive the fuel nozzle, and the fuel nozzle plate and the fuel nozzle inserted in the fuel nozzle receiving hole are connected to each other from an upstream side of the fuel nozzle plate by welding.
The present application claims priority from Japanese patent application serial No. 2014-157350, filed on Aug. 1, 2014, the content of which is hereby incorporated by reference into this application.
TECHNICAL FIELDThe present invention relates to a gas turbine combustor and, more particularly, to a gas turbine combustor having a fuel nozzle to inject a fuel.
BACKGROUND ARTIn a gas turbine combustor, strict environmental standards for NOx exhausted upon the operation of the gas turbine combustor are set to reduce the load imposed on the environment by an exhaust gas.
The higher the flame temperature, the larger the amount of exhausted NOx. It is, therefore, necessary to achieve uniform combustion by suppressing the formation of flames having locally high temperatures in the gas turbine combustor.
For uniform combustion by the gas turbine combustor, it is effective to improve the fuel dispersibility. In a gas turbine combustor of the prior art, for example, Japanese Patent Laid-Open No. 2013-108667, a plurality of fuel nozzles are respectively arranged in the circumferential and radial directions of a swirler of the gas turbine combustor to improve the fuel dispersibility.
Also, in a gas turbine combustor of the prior art in Japanese Patent Laid-Open No. 2013-053814, a premixing pilot burner is provided at the head of a combustion sleeve which forms a combustion chamber, and a premixing main burner is provided on its outer periphery to sufficiently premix air and a fuel and thereby keep NOx low.
CITATION LIST Patent Literature{Patent Literature 1}
- Japanese Patent Laid-Open No. 2013-108667
{Patent Literature 2}
- Japanese Patent Laid-open No. 2013-053814
The technique of gas turbine combustor described in Patent Literature 1 has the following problem. That is, as the number of fuel nozzles is increased to improve the fuel dispersibility, the distance between individual fuel nozzles or that between a set of fuel nozzles and a neighboring wall reduces.
In addition, the smaller the distance between individual fuel nozzles or that between a set of fuel nozzles and a neighboring wall, the narrower the space surrounding the fuel nozzle. Thus, in the technique of the gas turbine combustor described in Patent Literature 2, in connecting the end portion of the fuel nozzle from the downstream side to a fuel nozzle plate that structurally supports the fuel nozzles, a space sufficient for connection cannot be ensured.
An object of the present invention is to provide a gas turbine combustor with its structural reliability increased by facilitating connection between a fuel nozzle and a fuel nozzle plate, even when the space surrounding the fuel nozzle is narrow, to improve the accuracy of connecting the fuel nozzle and the fuel nozzle plate to each other.
Solution to ProblemA gas turbine combustor according to the present invention comprising a burner including: a plurality of fuel nozzles to supply a fuel; a fuel nozzle plate to supports end portions of the fuel nozzles structurally and being configured to distribute the fuel flowing from an upstream side to the fuel nozzles; and a swirler including a plurality of air holes to supply combustion air, characterized in that the fuel nozzle plate is provided with a fuel nozzle receiving hole to receive the fuel nozzle, and the fuel nozzle plate and the fuel nozzle inserted in the fuel nozzle receiving hole are connected to each other from an upstream side of the fuel nozzle plate by welding.
Advantageous Effects of InventionThe present invention realizes a gas turbine combustor with its structural reliability increased by facilitating connection between a fuel nozzle and a fuel nozzle plate, even when the space surrounding the fuel nozzle is narrow, to improve the accuracy of connecting the fuel nozzle and the fuel nozzle plate to each other.
Embodiments of a gas turbine combustor according to the present invention will be described hereinafter with reference to the accompanying drawings.
Embodiment 1The arrangement of a gas turbine plant to which a gas turbine combustor according to Embodiment 1 of the present invention is applied will be described below with reference to
In a gas turbine plant 1 to which a gas turbine combustor according to Embodiment 1 shown in
The gas turbine combustor 7 includes an end cover 10 which is provided at the end portion of the gas turbine combustor 7, a cylindrical front outer sleeve 11 which is attached to the end cover 10, and an elongated cylindrical rear outer sleeve 12 which is attached to the rear portion of the front outer sleeve 11.
A disk-shaped swirler 13 having a plurality of air holes 21 is provided inside the front outer sleeve 11 and the rear outer sleeve 12. A fuel nozzle plate 14 having a plurality of fuel nozzles 15 to inject a fuel toward air holes 21 formed in the swirler 13 is provided upstream of the swirler 13. An elongated cylindrical liner 16 to constitute a combustion chamber 23 in which air and a fuel are mixed and burned is provided downstream of the swirler 13.
The compressed air 4 compressed by the compressor 3 passes through an annular passage 17 formed between the rear outer sleeve 12 and the liner 16, and flows into a burner 18 formed in the gas turbine combustor 7.
The burner 18 includes a plurality of fuel nozzles 15 to inject a fuel, a fuel nozzle plate 14 to supports the end portions of the fuel nozzles 15 structurally and serves to distribute the fuel flowing into it from the upstream side to the fuel nozzles 15, and the swirler 13 having a plurality of air holes 21 to be supplied with combustion air, are formed downstream of the fuel nozzle plate 14 including the plurality of fuel nozzles 15.
Also, the compressed air 4 partially flows into the liner 16 from multiple cooling holes, formed in the liner 16, to serve as cooling air 19 for cooling the liner 16.
The fuel 5 supplied to the gas turbine combustor 7 flows into the fuel nozzle plate 14 through a fuel supply pipe 20 provided in the end cover 10, passes through the fuel nozzles 15 from the fuel nozzle plate 14, and is injected toward the plurality of air holes 21 formed in the swirler 13.
At the fuel nozzle-side inlet of the air hole 21 of the swirler 13, the fuel 5 injected by the fuel nozzle 15 and the compressed air 4 supplied through the annular passage 17 formed between the rear outer sleeve 12 and the liner 16 are mixed into an air-fuel mixture 22, which is injected toward the combustion chamber 23 and burned to form a high-temperature flame 24.
The gas turbine combustor 7 according to Embodiment 1 can use not only natural gas but also, for example, a coke oven gas, a refinery off-gas, or a coal gasification gas as the fuel 5.
An upstream end portion 40 of the fuel nozzle 15 that injects a fuel is connected to the fuel nozzle plate 14 in a connecting portion, the connecting portion of which is sealed to prevent leakage of the fuel 5.
Since a downstream end portion 30 of the fuel nozzle 15 is neither connected to nor in contact with the air hole 21 formed in the swirler 13, the compressed air 4 can freely flow into the air hole 21 of the swirler 13.
The upstream end portion 40 of the fuel nozzle 15 is connected to the fuel nozzle plate 14 generally by, for example, bolting, welding, or brazing.
A method of connecting to each other the fuel nozzle 15 and the fuel nozzle plate 14 which form the burner 18 of the gas turbine combustor 7 according to Embodiment 1 will be described below with reference to partial enlarged view shown in
The partial enlarged view of
Note, however, that in Embodiment 1, the method of connecting to each other the fuel nozzle 15 and the fuel nozzle plate 14 which form the burner 18 of the gas turbine combustor 7 is not limited to welding and there can be other methods.
As shown in the partial enlarged view of
However, the method of connecting the fuel nozzle 15 and the fuel nozzle plate 14 to each other according to conventional example shown in
In addition, in the method of connecting the fuel nozzle 15 and the fuel nozzle plate 14 to each other according to conventional example shown in
In the gas turbine combustor 7 according to Embodiment 1 shown in
A connecting portion 45 is formed at the upstream end portion 40 of the fuel nozzle 15, inserted in the fuel nozzle receiving hole 44, and the upstream end portion 41 of the fuel nozzle plate 14 by welding them together from the upstream side of the fuel nozzle plate 14 to connect the upstream end portion 40 of the fuel nozzle 15 to the upstream end portion 41 of the fuel nozzle plate 14.
More specifically, since the gas turbine combustor 7 of Embodiment 1 has the fuel nozzle 15 that does not extend to the upstream side of the fuel nozzle plate 14, an operation space wide enough to connect the fuel nozzle 15 and the fuel nozzle plate 14 to each other is ensured on the upstream side of the fuel nozzle plate 14. This improves both the accuracy of connecting the fuel nozzle 15 and the fuel nozzle plate 14 to each other and, with the improvement in connecting accuracy, the structural reliability of the connecting portion between the fuel nozzle 15 and the fuel nozzle plate 14 is heightened.
Also, with the method of connecting to each other the fuel nozzle 15 and the fuel nozzle plate 14 which form the burner 18 of the gas turbine combustor 7 according to Embodiment 1, when combustion oscillation occurs upon burning of the air-fuel mixture 22 containing the fuel 5 and the compressed air 4 in the combustion chamber 23 of the gas turbine combustor 7 so that any fuel nozzle 15 oscillates perpendicularly to the central axis of the fuel nozzle 15, the side surface of the fuel nozzle 15 comes into contact with the inner surface of the fuel nozzle receiving hole 44, formed in the fuel nozzle plate 14 to receive the fuel nozzle 15, thus suppressing the oscillation. This makes it possible to reduce the load acting on the connecting portion 45 that is formed on the fuel nozzle plate 14 and the fuel nozzle 15 to weld them together.
Moreover, forming a small space between the side surface of the fuel nozzle 15 and the inner surface of the fuel nozzle receiving hole 44 of the fuel nozzle plate 14 makes it possible to generate a frictional force between the side surface of the fuel nozzle 15 and the inner surface of the fuel nozzle receiving hole 44 of the fuel nozzle plate 14 upon their contact. The obtained frictional force can produce an effect of damping oscillation acting on the fuel nozzle 15.
Present Embodiment 1 realizes a gas turbine combustor with its structural reliability increased by facilitating connection between a fuel nozzle and a fuel nozzle plate, even when the space surrounding the fuel nozzle is narrow, to improve the accuracy of connecting the fuel nozzle and the fuel nozzle plate to each other.
Embodiment 2A method of connecting to each other a fuel nozzle 15 and a fuel nozzle plate 14 which form a burner 18 of a gas turbine combustor 7 according to Embodiment 2 of the present invention will be described below with reference to a partial enlarged view shown in
The partial enlarged view of
The partial enlarged view of
The burner 18 of the gas turbine combustor 7 according to Embodiment 2 shown in
A connecting portion 45 is formed at the upstream end portion 40 of the large-diameter stepped portion 50, formed on the fuel nozzle 15, and the upstream end portion 41 of the fuel nozzle plate 14, facing the upstream portion of the large-diameter stepped portion 51 formed in the fuel nozzle receiving hole 44, by welding them together from the upstream side of the fuel nozzle plate 14 to connect the upstream end portion 40 of the fuel nozzle 15 to the upstream end portion 41 of the fuel nozzle plate 14.
In the burner 18 of the gas turbine combustor 7 according to Embodiment 2 shown in
With the above-mentioned structure, even if the connecting portion 45 between the upstream end portion 40 of the fuel nozzle 15 and the upstream end portion of the fuel nozzle receiving hole 44 formed to extend through the fuel nozzle plate 14 is damaged and broken, the lower surface of the large-diameter stepped portion 50 formed at the upstream end portion 40 of the fuel nozzle 15 abuts against the lower surface of the large-diameter stepped portion 51, formed in the fuel nozzle receiving hole 44 formed in the fuel nozzle plate 14, to prevent the movement of the fuel nozzle 15. This, in turn, prevents the fuel nozzle 15 from falling off the fuel nozzle receiving hole 44 of the fuel nozzle plate 14 to the downstream side and damaging other components of the gas turbine combustor.
Also, the use of the stepped portions 50 and 51 allows the fuel nozzle 15 to be positioned in its axial direction 52.
Present Embodiment 2 realizes a gas turbine combustor with its structural reliability increased by facilitating connection between a fuel nozzle and a fuel nozzle plate, even when the space surrounding the fuel nozzle is narrow, to improve the accuracy of connecting the fuel nozzle and the fuel nozzle plate to each other.
Embodiment 3A method of connecting to each other a fuel nozzle 15 and a fuel nozzle plate 14 which form a burner 18 of a gas turbine combustor 7 according to Embodiment 3 of the present invention will be described below with reference to a partial enlarged view shown in
The partial enlarged view of
In the burner 18 of the gas turbine combustor 7 according to Embodiment 3 shown in
In the burner 18 of the gas turbine combustor 7 according to Embodiment 3, the fuel nozzle 15 has a tapered outer shape portion 60 in which a portion of the fuel nozzle 15 projecting to the downstream side from the fuel nozzle receiving hole 44 formed to extend through the fuel nozzle plate 14 has its outer diameter being gradually smaller from its basal portion toward a downstream end portion 30.
In the burner 18 of the gas turbine combustor 7 according to Embodiment 3, the fuel nozzle 15 has the tapered outer shape portion 60 in which a portion of the fuel nozzle 15 projecting to the downstream side from the fuel nozzle receiving hole 44 has its outer diameter being gradually smaller toward the downstream end portion 30. This allows the fuel nozzle 15 to be relatively lightweight by the weight of the portion gradually smaller in outer diameter of the fuel nozzle 15. It is, therefore, possible to reduce the load acting upon combustion oscillation on the connecting portion 45 that connects the upstream end portion 40 of the fuel nozzle 15 to the upstream end portion 41 of the fuel nozzle plate 14.
Present Embodiment 3 realizes a gas turbine combustor with its structural reliability increased by facilitating connection between a fuel nozzle and a fuel nozzle plate, even when the space surrounding the fuel nozzle is narrow, to improve the accuracy of connecting the fuel nozzle and the fuel nozzle plate to each other.
Embodiment 4A method of connecting to each other a fuel nozzle 15 and a fuel nozzle plate 14 which form a burner 18 of a gas turbine combustor 7 according to Embodiment 4 of the present invention will be described below with reference to a partial enlarged view shown in
The partial enlarged view of
In the burner 18 of the gas turbine combustor 7 according to Embodiment 4 shown in
With the above-mentioned structure, even if a connecting portion 45 between the upstream end portion 40 of the fuel nozzle 15 and the upstream end portion 41 of the fuel nozzle plate 14 is damaged and broken, the lower surface of the large-diameter stepped portion 50 formed on the fuel nozzle 15 abuts against the lower surface of the large-diameter stepped portion 51, formed upstream of the fuel nozzle receiving hole 44 formed in the fuel nozzle plate 14, to prevent the movement of the fuel nozzle 15. This structure prevents the fuel nozzle 15 from falling off the fuel nozzle receiving hole 44 of the fuel nozzle plate 14 to the downstream side and damaging other components of the gas turbine combustor.
Further, the fuel nozzle 15 has a tapered outer shape portion 60 in which a portion of the fuel nozzle 15 projecting to the downstream side from the fuel nozzle receiving hole 44 formed to extend through the fuel nozzle plate 14 has its outer diameter being gradually smaller from its basal portion toward a downstream end portion 30, as in the shape of the fuel nozzle 15 described in Embodiment 3.
In the burner 18 of the gas turbine combustor 7 according to Embodiment 4, the fuel nozzle 15 has the tapered outer shape portion 60 in which a portion of the fuel nozzle 15 projecting to the downstream side from the fuel nozzle receiving hole 44 formed in the fuel nozzle plate 14 has its outer diameter being gradually smaller toward the downstream end portion 30. This allows the fuel nozzle 15 to be relatively lightweight by the weight of the portion gradually smaller in outer diameter of the fuel nozzle 15. It is, therefore, possible to reduce the load acting upon combustion oscillation on the connecting portion 45 that connects the upstream end portion 40 of the fuel nozzle 15 to the upstream end portion 41 of the fuel nozzle plate 14.
In the burner 18 of the gas turbine combustor 7 according to Embodiment 4 shown in
Present Embodiment 4 realizes a gas turbine combustor with its structural reliability increased by facilitating connection between a fuel nozzle and a fuel nozzle plate, even when the space surrounding the fuel nozzle is narrow, to improve the accuracy of connecting the fuel nozzle and the fuel nozzle plate to each other.
Embodiment 5A method of connecting to each other a fuel nozzle 15 and a fuel nozzle plate 14 which form a burner 18 of a gas turbine combustor 7 according to Embodiment 5 of the present invention will be described below with reference to a partial enlarged view shown in
The partial enlarged view of
In the burner 18 of the gas turbine combustor 7 according to Embodiment 5 shown in
A connecting portion 45 is formed on the inner wall surface defining the tapered portion 70, formed near an upstream end portion 41 of the fuel nozzle plate 14, and the outer wall surface defining the tapered portion 72, formed near an upstream end portion 40 of the fuel nozzle 15 inserted in the fuel nozzle receiving hole 44, by welding them together from the upstream side of the fuel nozzle plate 14 to connect the fuel nozzle 15 to the fuel nozzle plate 14.
The fuel nozzle 15 has an outer wall surface defining the tapered portion 72 in which a portion of the fuel nozzle 15 formed near the upstream end portion 40 has an outer diameter larger than that of the downstream portion of the fuel nozzle 15. Also, the fuel nozzle receiving hole 44 has an inner wall surface defining the tapered portion 70 in which a portion of the fuel nozzle receiving hole 44 formed near the upstream end portion 41 of the fuel nozzle plate 14 has an inner diameter larger than that of the downstream portion of the fuel nozzle receiving hole 44. This structure allows the outer wall surface defining the tapered portion 72 of the fuel nozzle 15 to abut against the inner wall surface defining the tapered portion 70 of the fuel nozzle receiving hole 44 to prevent the fuel nozzle 15 from falling off the fuel nozzle receiving hole 44 to the downstream side.
With the above-mentioned structure, even if the connecting portion 45 between the upstream end portion 40 of the fuel nozzle 15 and the upstream end portion 41 of the fuel nozzle receiving hole 44 is damaged and broken, the outer wall surface defining the tapered portion 72 formed near the upstream end portion 40 of the fuel nozzle 15 abuts against the inner wall surface defining the tapered portion 70, formed in the fuel nozzle receiving hole 44 near the upstream end portion 41 of the fuel nozzle plate 14, to prevent the movement of the fuel nozzle 15. This structure prevents the fuel nozzle 15 from falling off the fuel nozzle receiving hole 44 of the fuel nozzle plate 14 to the downstream side and damaging other components of the gas turbine combustor.
Also, the use of the tapered portion 72 formed on the fuel nozzle 15 allows the fuel nozzle 15 to be positioned in its axial direction 52 and radial direction 71 with respect to the tapered portion 70 of the fuel nozzle receiving hole 44 formed on the fuel nozzle plate 14.
Present Embodiment 5 realizes a gas turbine combustor with its structural reliability increased by facilitating connection between a fuel nozzle and a fuel nozzle plate, even when the space surrounding the fuel nozzle is narrow, to improve the accuracy of connecting the fuel nozzle and the fuel nozzle plate to each other.
Embodiment 6A method of connecting to each other a fuel nozzle 15 and a fuel nozzle plate 14 which form a burner 18 of a gas turbine combustor 7 according to Embodiment 6 of the present invention will be described below with reference to a partial enlarged view shown in
The partial enlarged view of
The burner 18 in the gas turbine combustor 7 according to Embodiment 6 shown in
A connecting portion 45 is formed on an upstream end portion 41 of the fuel nozzle plate 14 and the large-diameter flanged portion 80, formed at the upstream end portion 40 of the fuel nozzle 15, by welding them together from the upstream side of the fuel nozzle plate 14 to connect the lower surface of the upstream end portion 40 of the fuel nozzle 15 to the upstream end portion 41 of the fuel nozzle plate 14.
In Embodiment 6, the flanged portion 80 formed at the upstream end portion 40 of the fuel nozzle 15 has an outer diameter larger than the inner diameter of the fuel nozzle receiving hole 44 of the fuel nozzle plate 14. With this structure, even if the connecting portion 45 that connects the lower surface of the upstream end portion 40 of the fuel nozzle 15 to the upstream end portion 41 of the fuel nozzle plate 14 is damaged, the fuel nozzle 15 is prevented from falling off the fuel nozzle receiving hole 44 of the fuel nozzle plate 14 to the downstream side and damaging other components of the gas turbine combustor.
Also, the fuel nozzle 15 can be positioned in its axial direction 52 in a contact portion 81 where the lower surface of the upstream end portion 40 defining the flanged portion 80 of the fuel nozzle 15 comes into contact with the upstream end portion 41 of the fuel nozzle plate 14.
Present Embodiment 6 realizes a gas turbine combustor with its structural reliability increased by facilitating connection between a fuel nozzle and a fuel nozzle plate, even when the space surrounding the fuel nozzle is narrow, to improve the accuracy of connecting the fuel nozzle and the fuel nozzle plate to each other.
Embodiment 7A method of connecting to each other a fuel nozzle 15 and a fuel nozzle plate 14 which form a burner 18 of a gas turbine combustor 7 according to Embodiment 7 of the present invention will be described below with reference to a partial enlarged view shown in
The partial enlarged view of
The burner 18 in the gas turbine combustor 7 according to Embodiment 7 shown in
In the method of connecting the fuel nozzle 15 and the fuel nozzle plate 14 to each other according to conventional structure shown in
Present Embodiment 7 realizes a gas turbine combustor with its structural reliability increased by facilitating connection between a fuel nozzle and a fuel nozzle plate, even when the space surrounding the fuel nozzle is narrow, to improve the accuracy of connecting the fuel nozzle and the fuel nozzle plate to each other.
LIST OF REFERENCE SIGNS
-
- 1: gas turbine plant
- 2: air
- 3: compressor
- 4: compressed air
- 5: fuel
- 6: combustor exit gas
- 7: gas turbine combustor
- 8: gas turbine
- 9: electric generator
- 10: end cover
- 11: front outer sleeve
- 12: rear outer sleeve
- 13: swirler
- 14: fuel nozzle plate
- 15: fuel nozzle
- 16: liner
- 17: passage between rear outer sleeve and liner
- 18: burner
- 19: cooling air for cooling
- 20: fuel supply pipe
- 21: air hole in swirler
- 22: air-fuel mixture containing fuel and compressed air
- 23: combustion chamber
- 24: flame
- 30: downstream end portion of fuel nozzle
- 40: upstream end portion of fuel nozzle
- 40b: side surface of fuel nozzle on upstream side
- 41: upstream end portion of fuel nozzle plate
- 41b: downstream end portion of fuel nozzle plate
- 43: space surrounding fuel nozzle
- 44: fuel nozzle receiving hole
- 42, 45: connecting portion
- 50: stepped portion of fuel nozzle
- 51: stepped portion of fuel nozzle receiving hole
- 52: axial direction of fuel nozzle
- 60: tapered outer shape portion
- 70, 71: tapered portion
- 71: radial direction of fuel nozzle
- 80: flanged portion of upstream end portion of fuel nozzle
- 81: contact portion between flanged portion of fuel nozzle and fuel nozzle plate
- 90: orifice portion
Claims
1. A gas turbine combustor comprising a burner including:
- a plurality of fuel nozzles to supply a fuel;
- a fuel nozzle plate to supports end portions of the fuel nozzles structurally and being configured to distribute the fuel flowing from an upstream side to the fuel nozzles; and
- a swirler including a plurality of air holes to supply combustion air,
- characterized in that
- the fuel nozzle plate is provided with a fuel nozzle receiving hole to receive the fuel nozzle, and
- the fuel nozzle plate and the fuel nozzle inserted in the fuel nozzle receiving hole are connected to each other from an upstream side of the fuel nozzle plate by welding.
2. The gas turbine combustor according to claim 1, wherein an upstream portion of the fuel nozzle inserted in the fuel nozzle receiving hole to receive the fuel nozzle is formed to have an outer diameter larger than an outer diameter of a downstream portion of the fuel nozzle.
3. The gas turbine combustor according to claim 2, wherein an upstream portion of the fuel nozzle receiving hole is formed to have an inner diameter larger than an inner diameter of a downstream portion of the fuel nozzle receiving hole.
4. The gas turbine combustor according to claim 1, wherein the fuel nozzle is provided with a flange at an upstream end portion of the fuel nozzle to have an outer diameter larger than an inner diameter of the fuel nozzle receiving hole inserted in the fuel nozzle.
5. The gas turbine combustor according to claim 3, wherein a first stepped portion is provided with an upstream portion of the fuel nozzle receiving hole formed in the fuel nozzle plate to receive the fuel nozzle is formed to have an inner diameter larger than an inner diameter of a downstream portion of the fuel nozzle receiving hole; and
- a second stepped portion is provided with an upstream portion of the fuel nozzle inserted in the fuel nozzle receiving hole is formed to have an outer diameter larger than an outer diameter of a downstream portion of the fuel nozzle, and the second stepped portion of the fuel nozzle abuts against the first stepped portion of the fuel nozzle receiving hole.
6. The gas turbine combustor according to claim 3, wherein a first tapered portion in which an upstream portion of the fuel nozzle receiving hole formed in the fuel nozzle plate is formed to have an inner diameter larger than an inner diameter of a downstream portion of the fuel nozzle receiving hole; and
- a second tapered portion in which an upstream portion of the fuel nozzle inserted in the fuel nozzle receiving hole is formed to have an outer diameter larger than an outer diameter of a downstream portion of the fuel nozzle, and
- an outer surface of the second tapered portion of the fuel nozzle abuts against the first tapered portion of the fuel nozzle receiving hole.
7. The gas turbine combustor according to claim 1, wherein a gap is formed between an inner surface of the fuel nozzle receiving hole formed in the fuel nozzle plate to receive the fuel nozzle and an outer surface of the fuel nozzle inserted in the fuel nozzle receiving hole.
8. The gas turbine combustor according to claim 1, wherein a portion of the fuel nozzle projecting to a downstream side from the fuel nozzle receiving hole of the fuel nozzle plate is formed to have an outer diameter being gradually smaller toward a downstream end portion of the fuel nozzle.
9. The gas turbine combustor according to claim 1, wherein the fuel nozzle is provided with an orifice in a fuel passage formed inside the fuel nozzle to narrow the passage.
Type: Application
Filed: Jul 30, 2015
Publication Date: Feb 4, 2016
Inventors: Satoshi KUMAGAI (Yokohama), Yoshihide WADAYAMA (Yokohama), Mitsuhiro KARISHUKU (Yokohama), Satoshi DODO (Yokohama), Nobuo YAGI (Yokohama)
Application Number: 14/813,987
