U.S. patent application number 14/813987 was filed with the patent office on 2016-02-04 for gas turbine combustor.
The applicant listed for this patent is MITSUBISHI HITACHI POWER SYSTEMS, LTD.. Invention is credited to Satoshi DODO, Mitsuhiro KARISHUKU, Satoshi KUMAGAI, Yoshihide WADAYAMA, Nobuo YAGI.
Application Number | 20160033136 14/813987 |
Document ID | / |
Family ID | 53773318 |
Filed Date | 2016-02-04 |
United States Patent
Application |
20160033136 |
Kind Code |
A1 |
KUMAGAI; Satoshi ; et
al. |
February 4, 2016 |
GAS TURBINE COMBUSTOR
Abstract
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.
Inventors: |
KUMAGAI; Satoshi; (Yokohama,
JP) ; WADAYAMA; Yoshihide; (Yokohama, JP) ;
KARISHUKU; Mitsuhiro; (Yokohama, JP) ; DODO;
Satoshi; (Yokohama, JP) ; YAGI; Nobuo;
(Yokohama, JP) |
|
Applicant: |
Name |
City |
State |
Country |
Type |
MITSUBISHI HITACHI POWER SYSTEMS, LTD. |
Yokohama |
|
JP |
|
|
Family ID: |
53773318 |
Appl. No.: |
14/813987 |
Filed: |
July 30, 2015 |
Current U.S.
Class: |
60/737 |
Current CPC
Class: |
F23R 3/283 20130101;
F23R 2900/00018 20130101; F23R 3/286 20130101 |
International
Class: |
F23R 3/28 20060101
F23R003/28 |
Foreign Application Data
Date |
Code |
Application Number |
Aug 1, 2014 |
JP |
2014-157350 |
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.
Description
CLAIM OF PRIORITY
[0001] 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 FIELD
[0002] The 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 ART
[0003] In 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.
[0004] 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.
[0005] 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.
[0006] 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
[0007] {Patent Literature 1} [0008] Japanese Patent Laid-Open No.
2013-108667
[0009] {Patent Literature 2} [0010] Japanese Patent Laid-open No.
2013-053814
SUMMARY OF INVENTION
Technical Problem
[0011] 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.
[0012] 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.
[0013] 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 Problem
[0014] A 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 Invention
[0015] The 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.
BRIEF DESCRIPTION OF DRAWINGS
[0016] FIG. 1 is a sectional view of a gas turbine combustor
according to Embodiment 1 of the present invention, which shows
outlines of flow of a fuel and air and a combustion process in the
gas turbine combustor.
[0017] FIG. 2 is a partial sectional view showing components of a
burner portion in the gas turbine combustor according to Embodiment
1 of the present invention shown in FIG. 1.
[0018] FIG. 3 is a partial sectional view showing method of
connecting to each other a fuel nozzle and a fuel nozzle plate in
the gas turbine combustor according to Embodiment 1 of the present
invention shown in FIG. 1.
[0019] FIG. 4 is a partial sectional view showing a method of
connecting to each other a fuel nozzle and a fuel nozzle plate
which form a burner portion of a gas turbine combustor according to
conventional example.
[0020] FIG. 5 is a partial sectional view showing a method of
connecting to each other a fuel nozzle and a fuel nozzle plate in a
gas turbine combustor according to Embodiment 2 of the present
invention.
[0021] FIG. 6 is a partial sectional view showing a method of
connecting to each other a fuel nozzle and a fuel nozzle plate in a
gas turbine combustor according to Embodiment 3 of the present
invention.
[0022] FIG. 7 is a partial sectional view showing a method of
connecting to each other a fuel nozzle and a fuel nozzle plate in a
gas turbine combustor according to Embodiment 4 of the present
invention.
[0023] FIG. 8 is a partial sectional view showing a method of
connecting to each other a fuel nozzle and a fuel nozzle plate in a
gas turbine combustor according to Embodiment 5 of the present
invention.
[0024] FIG. 9 is a partial sectional view showing a method of
connecting to each other a fuel nozzle and a fuel nozzle plate in a
gas turbine combustor according to Embodiment 6 of the present
invention.
[0025] FIG. 10 is a partial sectional view showing a method of
connecting to each other a fuel nozzle and a fuel nozzle plate in a
gas turbine combustor according to Embodiment 7 of the present
invention.
DESCRIPTION OF EMBODIMENTS
[0026] Embodiments of a gas turbine combustor according to the
present invention will be described hereinafter with reference to
the accompanying drawings.
Embodiment 1
[0027] The 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 FIG.
1.
[0028] In a gas turbine plant 1 to which a gas turbine combustor
according to Embodiment 1 shown in FIG. 1 is applied, a gas turbine
which constitutes a gas turbine plant 1 includes a compressor 3
which takes in air 2 from atmosphere and compresses it, a gas
turbine combustor 7 which burns compressed air 4 compressed by the
compressor 3 and a fuel 5 to generate a high-temperature and
high-pressure combustor exit gas 6, a gas turbine 8 which is driven
by the combustor exit gas 6 generated by the gas turbine combustor
7 and extracts energy from the combustor exit gas 6 as rotational
power, and an electric generator 9 which generates electric power
using the rotational power of the gas turbine 8.
[0029] 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.
[0030] 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.
[0031] 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.
[0032] 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.
[0033] 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.
[0034] 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.
[0035] 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.
[0036] 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.
[0037] FIG. 2 shows the arrangement of the burner 18 of the gas
turbine combustor 7 according to Embodiment 1. As shown in FIG. 2,
the burner 18 in the gas turbine combustor 7 according to
Embodiment 1 includes the swirler 13, the fuel nozzle plate 14, and
the fuel nozzles 15.
[0038] 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.
[0039] 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.
[0040] 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.
[0041] 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 FIGS. 3 and
4.
[0042] The partial enlarged view of FIG. 3 illustrates a method of
connecting together by welding 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.
[0043] 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.
[0044] As shown in the partial enlarged view of FIG. 3, 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, a fuel nozzle receiving hole
44 to receive the fuel nozzle 15 is formed to extend through the
fuel nozzle plate 14, and a connecting portion 45 is formed at an
upstream end portion 40 of the fuel nozzle 15, inserted in the fuel
nozzle receiving hole 44 and an 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.
[0045] FIG. 4 shows 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 conventional Example. With
the connecting method according to conventional example shown in
FIG. 4, a side surface 40b of the fuel nozzle 15 on the upstream
side and a downstream end portion 41b of the fuel nozzle plate 14
are connected to each other by forming a connecting portion 42 on
them from the downstream side of the fuel nozzle plate 14.
[0046] However, the method of connecting the fuel nozzle 15 and the
fuel nozzle plate 14 to each other according to conventional
example shown in FIG. 4 poses the following problem. That is, when
multiple fuel nozzles 15 are densely arranged downstream of the
fuel nozzle plate 14 and a space 43 surrounding the fuel nozzle 15
is narrow, an operation space which is wide enough to connect the
fuel nozzle 15 and the fuel nozzle plate 14 to each other cannot be
ensured on the downstream side of the fuel nozzle plate 14.
[0047] 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 FIG. 4, no operation space for
connecting the fuel nozzle 15 and the fuel nozzle plate 14 to each
other is present on the upstream side of the fuel nozzle plate 14,
as is apparent from the structure shown in FIG. 4.
[0048] In the gas turbine combustor 7 according to Embodiment 1
shown in FIG. 3, 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, even when multiple fuel nozzles
15 are densely arranged, the fuel nozzle receiving hole 44 to
receive the fuel nozzle 15 is formed to extend through the fuel
nozzle plate 14, and the fuel nozzle 15 inserted in the fuel nozzle
receiving hole 44 projects to the downstream side of the fuel
nozzle plate 14.
[0049] 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.
[0050] 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.
[0051] 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.
[0052] 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.
[0053] 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 2
[0054] A 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 FIG. 5.
[0055] The partial enlarged view of FIG. 5 illustrates details of
the structure of the burner 18 in the gas turbine combustor 7
according to Embodiment 2. Since the basic arrangement and 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 2 are similar to those
according to the above-mentioned Embodiment 1 of the present
invention, parts common to both embodiments will not be described
and only different parts will be described below.
[0056] The partial enlarged view of FIG. 5 shows the fuel nozzle 15
connected to an upstream end portion 41 of the fuel nozzle plate 14
at an upstream end portion 40 of the fuel nozzle 15, in the burner
18 of the gas turbine combustor 7 according to Embodiment 2.
[0057] The burner 18 of the gas turbine combustor 7 according to
Embodiment 2 shown in FIG. 5 includes stepped portions 51 and 50.
The stepped portion 51 is formed upstream of the fuel nozzle
receiving hole 44 formed to extend through the fuel nozzle plate 14
and has a diameter larger than that of the downstream portion of
the fuel nozzle receiving hole 44. The stepped portion 50 is formed
at the upstream end portion 40 of the fuel nozzle 15 inserted in
the fuel nozzle receiving hole 44 and has a diameter larger than
that of the downstream portion of the fuel nozzle 15. The stepped
portion 50 formed at the upstream end portion 40 of the fuel nozzle
15 abuts against the stepped portion 51 formed upstream of the fuel
nozzle receiving hole 44.
[0058] 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.
[0059] In the burner 18 of the gas turbine combustor 7 according to
Embodiment 2 shown in FIG. 5, the stepped portion 50 formed at the
upstream end portion 40 of the fuel nozzle 15 has an outer diameter
larger than that of the downstream portion of the fuel nozzle 15,
and the stepped portion 51 formed in the upstream portion of the
fuel nozzle receiving hole 44 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 lower
surface of the large-diameter stepped portion 50 formed on the fuel
nozzle 15 to abut against the lower surface of the large-diameter
stepped portion 51 formed in 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.
[0060] 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.
[0061] Also, the use of the stepped portions 50 and 51 allows the
fuel nozzle 15 to be positioned in its axial direction 52.
[0062] 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 3
[0063] A 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 FIG. 6.
[0064] The partial enlarged view of FIG. 6 illustrates details of
the structure of the burner 18 in the gas turbine combustor 7
according to Embodiment 3. Since the basic arrangement and the
method of connecting to each other upstream end portion 40 of the
fuel nozzle 15 and upstream end portion 41 of the fuel nozzle plate
14, respectively, which form the burner 18 of the gas turbine
combustor 7 according to Embodiment 3 are similar to those
according to the above-mentioned Embodiment 1 of the present
invention, parts common to both embodiments will not be described
and only different parts will be described below.
[0065] FIG. 6 shows details of the structure of the burner 18 in
the gas turbine combustor 7 according to Embodiment 3.
[0066] In the burner 18 of the gas turbine combustor 7 according to
Embodiment 3 shown in FIG. 6, a connecting portion 45 is formed at
the upstream end portion 40 of the fuel nozzle 15, inserted in a
fuel nozzle receiving hole 44 formed to extend through the fuel
nozzle plate 14, 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.
[0067] 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.
[0068] 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.
[0069] 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 4
[0070] A 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 FIG. 7.
[0071] The partial enlarged view of FIG. 7 illustrates details of
the structure of the burner 18 in the gas turbine combustor 7
according to Embodiment 4. Since the basic arrangement and the
method of connecting to each other upstream end portion 40 of the
fuel nozzle 15 and upstream end portion 41 of the fuel nozzle plate
14, respectively, which form the burner 18 of the gas turbine
combustor 7 according to Embodiment 4 are similar to those
according to the above-mentioned Embodiment 2 of the present
invention, parts common to both embodiments will not be described
and only different parts will be described below.
[0072] In the burner 18 of the gas turbine combustor 7 according to
Embodiment 4 shown in FIG. 7, a stepped portion 50 formed at the
upstream end portion of the fuel nozzle 15 has an outer diameter
larger than that of the downstream portion of the fuel nozzle 15,
and a stepped portion 51 formed in the upstream portion of the fuel
nozzle receiving hole 44 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 lower surface
of the large-diameter stepped portion 50 formed on the fuel nozzle
15 to abut against the lower surface of the large-diameter stepped
portion 51, formed in 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.
[0073] 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.
[0074] 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.
[0075] 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.
[0076] In the burner 18 of the gas turbine combustor 7 according to
Embodiment 4 shown in FIG. 7, the fuel nozzle 15 is relatively
lightweight while keeping a sufficient strength. It is, therefore,
possible to reduce the load acting upon combustion oscillation on
the connecting portion 45 that connects the fuel nozzle 15 to the
fuel nozzle plate 14.
[0077] 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 5
[0078] A 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 FIG. 8.
[0079] The partial enlarged view of FIG. 8 illustrates details of
the structure of the burner 18 in the gas turbine combustor 7
according to Embodiment 5. Since the basic arrangement and the
method of connecting to each other upstream end portion 40 of the
fuel nozzle 15 and upstream end portion 41 of the fuel nozzle plate
14, respectively, which form the burner 18 of the gas turbine
combustor 7 according to Embodiment 5 are similar to those
according to the above-mentioned Embodiment 1 of the present
invention, parts common to both embodiments will not be described
and only different parts will be described below.
[0080] In the burner 18 of the gas turbine combustor 7 according to
Embodiment 5 shown in FIG. 8, a fuel nozzle receiving hole 44
formed to extend through the fuel nozzle plate 14 has an inner wall
surface defining a tapered portion 70 in which the fuel nozzle
receiving hole 44 has its outer diameter being gradually larger
from its intermediate portion to the upstream side. The fuel nozzle
15 inserted in the fuel nozzle receiving hole 44 has an outer wall
surface defining a tapered portion 72 in which the fuel nozzle 15
has its outer diameter being gradually larger from its intermediate
portion to the upstream side, in correspondence with the shape of
the inner wall surface defining the tapered portion 70 of the fuel
nozzle receiving hole 44.
[0081] 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.
[0082] 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.
[0083] 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.
[0084] 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.
[0085] 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 6
[0086] A 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 FIG. 9.
[0087] The partial enlarged view of FIG. 9 illustrates details of
the structure of the burner 18 in the gas turbine combustor 7
according to Embodiment 6. Since the basic arrangement and 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 6 are similar to those
according to the above-mentioned Embodiment 1 of the present
invention, parts common to both embodiments will not be described
and only different parts will be described below.
[0088] The burner 18 in the gas turbine combustor 7 according to
Embodiment 6 shown in FIG. 9 includes flanged portions 80. The
flanged portion 80 is formed at an upstream end portion 40 of the
fuel nozzle 15 inserted in a fuel nozzle receiving hole 44 formed
to extend through the fuel nozzle plate 14, and has a diameter
larger than the outer diameter of the downstream portion of the
fuel nozzle 15.
[0089] 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.
[0090] 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.
[0091] 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.
[0092] 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 7
[0093] A 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 FIG. 10.
[0094] The partial enlarged view of FIG. 10 illustrates details of
the structure of the burner 18 in the gas turbine combustor 7
according to Embodiment 7. Since the basic arrangement and the
method of connecting to each other upstream end portion 40 of the
fuel nozzle 15 and upstream end portion 41 of the fuel nozzle plate
14, respectively, which form the burner 18 of the gas turbine
combustor 7 according to Embodiment 7 are similar to those
according to the above-mentioned Embodiment 2 of the present
invention, parts common to both embodiments will not be described
and only different parts will be described below.
[0095] The burner 18 in the gas turbine combustor 7 according to
Embodiment 7 shown in FIG. 10 includes an orifice portion 90 formed
in the intermediate portion of the fuel passage of the fuel nozzle
15. A connecting portion 45 is formed at an upstream end portion 40
of a large-diameter stepped portion 50 of the fuel nozzle 15 and an
upstream end portion 41 of the fuel nozzle plate 14, provided
upstream of a large-diameter stepped portion 51 of a fuel nozzle
receiving hole 44 formed in 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.
[0096] In the method of connecting the fuel nozzle 15 and the fuel
nozzle plate 14 to each other according to conventional structure
shown in FIG. 4, thermal deformation occurs due to factors
associated with welding and the inner diameter of the orifice
portion 90 formed in the intermediate portion of the fuel passage
of the fuel nozzle 15 changes. In contrast to this, with the
structure of the burner 18 in the gas turbine combustor 7 according
to Embodiment 7, the direction of thermal deformation caused by
welding is not a radial direction 71 of the fuel nozzle 15 but an
axial direction 52 of the fuel nozzle 15. This keeps deformation,
occurring in the orifice portion 90 of any fuel nozzle 15, small to
accurately control the fuel flow rate.
[0097] 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
[0098] 1: gas turbine plant [0099] 2: air [0100] 3: compressor
[0101] 4: compressed air [0102] 5: fuel [0103] 6: combustor exit
gas [0104] 7: gas turbine combustor [0105] 8: gas turbine [0106] 9:
electric generator [0107] 10: end cover [0108] 11: front outer
sleeve [0109] 12: rear outer sleeve [0110] 13: swirler [0111] 14:
fuel nozzle plate [0112] 15: fuel nozzle [0113] 16: liner [0114]
17: passage between rear outer sleeve and liner [0115] 18: burner
[0116] 19: cooling air for cooling [0117] 20: fuel supply pipe
[0118] 21: air hole in swirler [0119] 22: air-fuel mixture
containing fuel and compressed air [0120] 23: combustion chamber
[0121] 24: flame [0122] 30: downstream end portion of fuel nozzle
[0123] 40: upstream end portion of fuel nozzle [0124] 40b: side
surface of fuel nozzle on upstream side [0125] 41: upstream end
portion of fuel nozzle plate [0126] 41b: downstream end portion of
fuel nozzle plate [0127] 43: space surrounding fuel nozzle [0128]
44: fuel nozzle receiving hole [0129] 42, 45: connecting portion
[0130] 50: stepped portion of fuel nozzle [0131] 51: stepped
portion of fuel nozzle receiving hole [0132] 52: axial direction of
fuel nozzle [0133] 60: tapered outer shape portion [0134] 70, 71:
tapered portion [0135] 71: radial direction of fuel nozzle [0136]
80: flanged portion of upstream end portion of fuel nozzle [0137]
81: contact portion between flanged portion of fuel nozzle and fuel
nozzle plate [0138] 90: orifice portion
* * * * *