U.S. patent application number 14/358413 was filed with the patent office on 2014-10-23 for gas turbine combustor.
This patent application is currently assigned to MITSUBISHI HITACHI POWER SYSTEMS, LTD.. The applicant listed for this patent is MITSUBISHI HITACHI POWER SYSTEMS, LTD.. Invention is credited to Naoki Abe, Shinji Akamatsu, Toshihiko Saito.
Application Number | 20140311151 14/358413 |
Document ID | / |
Family ID | 48429605 |
Filed Date | 2014-10-23 |
United States Patent
Application |
20140311151 |
Kind Code |
A1 |
Saito; Toshihiko ; et
al. |
October 23, 2014 |
GAS TURBINE COMBUSTOR
Abstract
Provided is a gas turbine combustor having improved
maintainability obtained by facilitating the mounting and removal
of a base plate for supporting main burners and a pilot burner. A
gas turbine combustor is provided with: a pilot burner disposed at
the center of a combustor inner tube; main burners provided on the
outside of the pilot burner in the radial direction so as to be
arranged in the circumferential direction of the inner peripheral
surface of the combustor inner tube; a circular disc-shaped base
plate disposed within the combustor inner tube and supporting both
the pilot burner and the main burners; and an engagement section
protruding from the inner peripheral surface toward the inside
thereof in the radial direction and engaging with the base plate.
The base plate, and the engagement section or the inner peripheral
surfaces are affixed by bolts.
Inventors: |
Saito; Toshihiko; (Tokyo,
JP) ; Akamatsu; Shinji; (Tokyo, JP) ; Abe;
Naoki; (Tokyo, JP) |
|
Applicant: |
Name |
City |
State |
Country |
Type |
MITSUBISHI HITACHI POWER SYSTEMS, LTD. |
Yokohama-shi, Kanagawa |
|
JP |
|
|
Assignee: |
MITSUBISHI HITACHI POWER SYSTEMS,
LTD.
Yokohama-shi, Kanagawa
JP
|
Family ID: |
48429605 |
Appl. No.: |
14/358413 |
Filed: |
November 14, 2012 |
PCT Filed: |
November 14, 2012 |
PCT NO: |
PCT/JP2012/079457 |
371 Date: |
May 15, 2014 |
Current U.S.
Class: |
60/737 |
Current CPC
Class: |
F23R 2900/00017
20130101; F23R 3/343 20130101; F23R 3/283 20130101; F23R 3/286
20130101; F23R 3/42 20130101; F23R 3/14 20130101 |
Class at
Publication: |
60/737 |
International
Class: |
F23R 3/28 20060101
F23R003/28 |
Foreign Application Data
Date |
Code |
Application Number |
Nov 16, 2011 |
JP |
2011-250242 |
Claims
1-4. (canceled)
5. A gas turbine combustor, comprising: a pilot burner disposed in
a center of a combustor swirler basket; a plurality of main burners
disposed radially outside the pilot burner along a circumferential
direction of an inner peripheral surface of the combustor swirler
basket; a base plate disposed inside the combustor swirler basket
and supporting the pilot burner and the main burners; and an
engaging portion protruding radially inward from the inner
peripheral surface and engaged with the base plate, wherein the
base plate has an upstream surface disposed upstream in a direction
of flow of compressed air to be supplied in the combustor swirler
basket, and base plate and the engaging portion are fixed to each
other with a bolt inserted from the upstream surface side.
6. The gas turbine combustor according to claim 5, wherein the
engaging portion is a bolt receiving portion having a streamlined
shape along a direction of flow of compressed air to be supplied in
the combustor swirler basket, and the base plate and the bolt
receiving portion are fixed to each other with the bolt.
7. The gas turbine combustor according to claim 5, wherein the
engaging portion is two annular protruding portions formed along
the circumferential direction of the inner peripheral surface and
disposed side by side in an axial direction of the combustor
swirler basket, and the base plate and the annular protruding
portions are fixed to each other with the bolt with the base plate
engaged between the annular protruding portions.
8. A gas turbine combustor, comprising: a pilot burner disposed in
a center of a combustor swirler basket; a plurality of main burners
disposed radially outside the pilot burner along a circumferential
direction of an inner peripheral surface of the combustor swirler
basket; a base plate disposed inside the combustor swirler basket
and supporting the pilot burner and the main burners; and an
engaging portion protruding radially inward from the inner
peripheral surface and engaged with the base plate, wherein the
engaging portion is an annular step portion formed along the
circumferential direction of the inner peripheral surface, and an
outer peripheral end surface of the base plate and the inner
peripheral surface are fixed to each other with a bolt with the
base plate and the annular step portion engaged with each other,
the bolt being inserted from radially outside the combustor swirler
basket at a position immediately below the annular step portion.
Description
TECHNICAL FIELD
[0001] The present invention relates to a gas turbine combustor in
which a pilot burner and main burners are supported on a combustor
swirler basket by means of a disc-shaped base plate.
BACKGROUND ART
[0002] In recent years, gas turbine combustors employing a premix
combustion method have been increasing in number for reducing NOx
and other purposes. These gas turbine combustors employing a premix
combustion method include main burners (premix burners) configured
to perform premix combustion and also a pilot burner configured to
perform diffusion combustion. In this way, diffusion flame produced
by the pilot burner can be used as pilot flame for the main burners
to produce premix flame. Accordingly, the premix combustion can be
performed stably.
[0003] Thus, as a burner arrangement for the stable premix
combustion, the above-described conventional gas turbine combustors
employ an arrangement in which multiple main burners surround a
pilot burner. Moreover, the pilot burner and the main burners thus
arranged are attached to the inner peripheral surface of a
combustor swirler basket by means of a disc-shaped base plate.
[0004] Moreover, as a structure for attaching the base plate, a
structure in which an outer peripheral portion of the base plate is
welded to the inner peripheral surface of the combustor swirler
basket has conventionally been employed. However, employing this
base-plate attachment structure will require detachment and
attachment of the base plate for repair of the burners and the base
plate when they are damaged by flashback and for modification and
replacement of the burners due to change in combustion
specifications. Hence, the maintainability is lowered. Further, as
the base plate and the combustor swirler basket are welded
repeatedly, the base plate and the combustor swirler basket become
easily strained by the welding. Consequently, the accuracy of
attachment of the burners may possibly be lowered.
[0005] Meanwhile, Patent Document 1 discloses a gas turbine
combustor in which outer peripheral portions of casings are fixed
to each other with bolts.
PRIOR ART DOCUMENT
Patent Document
[0006] Patent Document 1: Japanese Patent Application Publication
No. 2002-98116
SUMMARY OF THE INVENTION
Problem to be Solved by the Invention
[0007] Here, it may be possible to employ a casing attachment
structure like the one of the conventional gas turbine combustor
described above as the base plate attachment structure. However,
the attachment of the base plate is performed, not outside the
casings, but inside the combustor swirler basket, and therefore the
maintainability needs to be considered further.
[0008] Thus, the present invention has been made for solving the
above problem, and an object thereof is to provide a gas turbine
combustor capable of improving its maintainability by enabling easy
attachment and detachment of a base plate that supports a pilot
burner and main burners.
Means for Solving the Problems
[0009] A gas turbine combustor according to a first invention for
solving the above problem is characterized in that
[0010] the gas turbine combustor comprises: [0011] a pilot burner
disposed in a center of a combustor swirler basket; [0012] a
plurality of main burners disposed radially outside the pilot
burner along a circumferential direction of an inner peripheral
surface of the combustor swirler basket; [0013] a base plate
disposed inside the combustor swirler basket and supporting the
pilot burner and the main burners; and [0014] an engaging portion
protruding radially inward from the inner peripheral surface and
engaged with the base plate, and
[0015] the base plate and any one of the engaging portion and the
inner peripheral surface are fixed to each other with a bolt.
[0016] A gas turbine combustor according to a second invention for
solving the above problem is characterized in that
[0017] the engaging portion is a bolt receiving portion having a
streamlined shape along a direction of flow of compressed air to be
supplied in the combustor swirler basket, and
[0018] the base plate and the bolt receiving portion are fixed to
each other with the bolt.
[0019] A gas turbine combustor according to a third invention for
solving the above problem is characterized in that
[0020] the engaging portion is two annular protruding portions
formed along the circumferential direction of the inner peripheral
surface and disposed side by side in an axial direction of the
combustor swirler basket, and
[0021] the base plate and the annular protruding portions are fixed
to each other with the bolt with the base plate engaged between the
annular protruding portions.
[0022] A gas turbine combustor according to a fourth invention for
solving the above problem is characterized in that
[0023] the engaging portion is an annular step portion formed along
the circumferential direction of the inner peripheral surface,
and
[0024] the base plate and the inner peripheral surface are fixed to
each other with the bolt with the base plate and the annular
protruding portion engaged with each other.
Effect of the Invention
[0025] Thus, in the gas turbine combustor according to the present
invention, the base plate is engaged with the engaging portion
protruding from the inner peripheral surface of the combustor
swirler basket, and the base plate and any one of the engaging
portion and the inner peripheral surface are fixed to each other
with the bolt. This enables easy attachment and detachment of the
base plate that supports the pilot burner and the main burners.
Accordingly, the maintainability can be improved.
BRIEF DESCRIPTION OF THE DRAWINGS
[0026] FIG. 1 is a schematic structure diagram of a gas turbine
combustor according to one embodiment of the present invention.
[0027] FIG. 2 is a front view of a base plate.
[0028] FIG. 3 Part (a) of FIG. 3 is a view showing the structure of
attachment of a base plate in a gas turbine combustor according to
a first embodiment of the present invention. Part (b) of FIG. 3 is
a cross-sectional view taken along III-III line in Part (a) and
seen in the direction of arrows III in Part (a).
[0029] FIG. 4 is a view showing the structure of attachment of a
base plate in a gas turbine combustor according to a second
embodiment of the present invention.
[0030] FIG. 5 is a view showing the structure of attachment of a
base plate in a gas turbine combustor according to a third
embodiment of the present invention.
[0031] FIG. 6 is a view showing the structure of attachment of a
base plate in a gas turbine combustor according to a fourth
embodiment of the present invention.
[0032] FIG. 7 is a view showing the structure of attachment of a
base plate in a gas turbine combustor according to a fifth
embodiment of the present invention.
[0033] FIG. 8 is a view showing the structure of attachment of a
base plate in a gas turbine combustor according to a sixth
embodiment of the present invention.
[0034] FIG. 9 is a view showing the structure of attachment of a
base plate in a gas turbine combustor according to a seventh
embodiment of the present invention.
MODES FOR CARRYING OUT THE INVENTION
[0035] Hereinbelow, a gas turbine combustor according to the
present invention will be described in detail with reference to the
drawings.
EMBODIMENTS
[0036] First, a gas turbine combustor according to a first
embodiment of the present invention will be described in detail
with reference to FIGS. 1 to 3.
[0037] As shown in FIG. 1, a combustor 1 for a gas turbine is one
employing a premix combustion method, and includes a combustor
swirler basket 11 in which fuel F and compressed air A for
combustion are mixed and a combustor tail tube 12 in which the
mixture of the fuel F and the compressed air A is combusted.
Specifically, the combustor 1 is formed by connecting a downstream
opening end portion of the combustor swirler basket 11 and an
upstream opening end portion of the combustor tail tube 12. Note
that the terms upstream and downstream represent directions based
on the flow of the fuel F and the compressed air A.
[0038] Further, a pilot burner 13 and multiple main burners (premix
burners) 14 are provided inside the combustor swirler basket 11.
Moreover, the pilot burner 13 and the main burners 14 are supported
on an inner peripheral surface 11a of the combustor swirler basket
11 by means of a disc-shaped base plate 15.
[0039] The pilot burner 13 is disposed in the center of the
combustor swirler basket 11 and includes a pilot cone 21, a pilot
nozzle 22, and a pilot swirler 23. The pilot nozzle 22 is inserted
in the pilot cone 21 in such a way as to be coaxial with the pilot
cone 21. Moreover, the pilot swirler 23 is interposed between the
inner peripheral surface of the pilot cone 21 and the outer
peripheral surface of the pilot nozzle 22.
[0040] Meanwhile, there are eight main burners 14 provided radially
outside the pilot burner 13 at an equal angular interval along the
circumferential direction of the inner peripheral surface 11a of
the combustor swirler basket 11. Each main burner 14 includes a
swirler tube 31, an extension pipe 32, a main nozzle (premix
nozzle) 33, and a main swirler 34. The main nozzle 33 is inserted
in the swirler tube 31 and the extension pipe 32 in such a way as
to be coaxial with the swirler tube 31 and the extension pipe 32.
Moreover, the main swirler 34 is interposed between the inner
peripheral surface of the swirler tube 31 and the outer peripheral
surface of the main nozzle 33.
[0041] Thus, during operation of the combustor 1, the compressed
air A at high temperature and high pressure flows into the upstream
opening end portion of the combustor swirler basket 11, and is then
supplied into and around the pilot burner 13 and also into and
around the main burners 14. At the same time, the fuel F is also
supplied into the pilot nozzle 22 of the pilot burner 13 and the
main nozzles 33 of the main burners 14.
[0042] As a result, in the pilot burner 13, first, the supplied
compressed air A is swirled by the pilot swirler 23 to be mixed to
the fuel F injected from the pilot nozzle 22. Thereafter, the
fuel-air mixture obtained by the mixing is ignited, so that
diffusion combustion is performed inside the pilot cone 21 and the
downstream side (inside the combustor tail tube 12). Then, the
combusted gas produced by the diffusion combustion is supplied
downstream inside the combustor tail tube 12.
[0043] Moreover, in each main burner 14, first, the supplied
compressed air A is swirled by the main swirler 34 to be mixed to
the fuel F injected from the main nozzle 33. Thereafter, the
premixed fuel-air mixture obtained by the mixing is caused to swirl
and flow toward the inside of the combustor tail tube 12 from the
extension pipe 32. As a result, flame of the premixed fuel-air
mixture is stabilized by the diffusion flame produced by the pilot
burner 13, so that the premix combustion is performed stably. Then,
the combusted gas produced by this premix combustion is supplied
downstream inside the combustor tail tube 12.
[0044] Meanwhile, as shown in FIG. 2, a support hole 51 for the
pilot burner 13 and support holes 52 for the main burners 14 are
formed in the base plate 15. Specifically, the support hole 51 is
bored in the center of the base plate 15, and the pilot cone 21 of
the pilot burner 13 penetrates through and is supported on the
support hole 51. Moreover, the support holes 52 are bored around
the support hole 51, and the extension pipes 32 of the main burners
14 penetrate through and are supported on the support holes 52.
[0045] Further, as shown in FIG. 2 and Part (a) of FIG. 3, multiple
bolt holes 53 are formed in an outer peripheral portion of the base
plate 15 (radially outside the support holes 52). These bolt holes
53 are through-holes penetrating the base plate 15 between its
upstream surface 15a and downstream surface 15b in the thickness
direction, and are disposed at an equal angular interval along the
circumferential direction of the base plate 15. Note that, of the
multiple bolt holes 53, two bolt holes 53 are representatively
illustrated in FIG. 2.
[0046] On the other hand, as shown in Parts (a) and (b) of FIG. 3,
multiple bolt receiving members (engaging portion) 41A are provided
on the inner peripheral surface 11a of the combustor swirler basket
11 at the same interval as the interval of the bolt holes 53 along
the circumferential direction of the inner peripheral surface 11a.
These bolt receiving members 41A protrude radially inward from the
inner peripheral surface 11a, and a bolt hole 41b is bored in an
end surface 41a of each bolt receiving member 41A.
[0047] Moreover, the upstream surface 15a of the base plate 15 is
engaged with the end surfaces 41a of the bolt receiving members 41A
such that the bolt holes 41b and the bolt holes 53 communicate with
each other. The base plate 15 and the bolt receiving members 41A in
this engaged state are fixed to each other in the thickness
direction of the base plate 15 with bolts 60.
[0048] Specifically, the base plate 15 can be fixed to the bolt
receiving members 41A by engaging the upstream surface 15a of the
base plate 15 with the end surfaces 41a of the bolt receiving
members 41A and inserting the bolts 60 into the bolt holes 41b and
53 from the downstream surface 15b side.
[0049] Thus, the base plate 15 can be easily attached and detached
by providing the bolt receiving members 41A on the inner peripheral
surface 11a of the combustor swirler basket 11 and fixing the bolt
receiving members 41A and the base plate 15 with the bolts 60.
Accordingly, the maintainability of the pilot burner 13, the main
burners 14, and the base plate 15 can be improved.
[0050] Moreover, since the upstream surface 15a of the base plate
15 is engaged with the end surfaces 41a of the bolt receiving
members 41A, and the bolts 60 are made attachable and detachable
from the downstream surface 15b side of the base plate 15, the
attachment and detachment of the bolts 60 can be easily done via
the downstream opening end portion of the combustor swirler basket
11.
[0051] Next, a gas turbine combustor according to a second
embodiment of the present invention will be described in detail
with reference to FIG. 4.
[0052] As shown in FIG. 4, each bolt receiving member 41B protrudes
radially inward from an inner peripheral surface 11a, and its
upstream end portion has a cross section curving in such a
streamlined shape as to gradually narrow as extending in a
longitudinal direction (upstream in the flow direction).
[0053] Thus, by making each bolt receiving member 41B in the
streamlined shape, compressed air A supplied in a combustor swirler
basket 11 can flow without being disturbed. Accordingly, the
generation of the wake (low flow speed region) of the compressed
air A by the bolt receiving member 41B can be reduced.
[0054] Next, a gas turbine combustor according to a third
embodiment of the present invention will be described in detail
with reference to FIG. 5.
[0055] As shown in FIG. 5, a downstream surface 15b of a base plate
15 is engaged with end surfaces 41a of bolt receiving members 41A
such that bolt holes 41b and bolt holes 53 communicate with each
other. Moreover, the base plate 15 and the bolt receiving members
41A in this engaged state are fixed to each other in the thickness
direction of the base plate 15 with bolts 60.
[0056] Specifically, the base plate 15 can be fixed to the bolt
receiving members 41A by engaging the downstream surface 15b of the
base plate 15 with the end surfaces 41a of the bolt receiving
members 41A and inserting the bolts 60 into the bolt holes 41b and
53 from the upstream surface 15a side.
[0057] Thus, the base plate 15 can be easily attached and detached.
Accordingly, the maintainability of a pilot burner 13, main burners
14, and the base plate 15 can be improved.
[0058] Moreover, the downstream surface 15b of the base plate 15 is
engaged with the end surfaces 41a of the bolt receiving members
41A, and the bolts 60 are made attachable and detachable from the
upstream surface 15a side of the base plate 15. In this way, even
if bolts 60 come off from their bolt holes 41b and 53, it is
possible to prevent these bolts 60 that have come off from entering
the combustion region and to prevent the base plate 15 from tilting
toward the combustion region.
[0059] Next, a gas turbine combustor according to a fourth
embodiment of the present invention will be described in detail
with reference to FIG. 6.
[0060] As shown in FIG. 6, each bolt receiving member 41B protrudes
radially inward from an inner peripheral surface 11a, and its
downstream end portion has a cross section curving in such a
streamlined shape as to gradually narrow as extending in a
longitudinal direction (downstream in the flow direction).
[0061] Thus, by making each bolt receiving member 41B in the
streamlined shape, compressed air A supplied in a combustor swirler
basket 11 can flow without being disturbed. Accordingly, the
generation of the wake (low flow speed region) of the compressed
air A by the bolt receiving member 41B can be reduced.
[0062] Next, a gas turbine combustor according to a fifth
embodiment of the present invention will be described in detail
with reference to FIG. 7.
[0063] As shown in FIG. 7, a combustor swirler basket 11 includes
an upstream inner tube 42 and a downstream inner tube 43.
Specifically, the combustor swirler basket 11 is formed by
connecting a downstream opening end portion of the upstream inner
tube 42 and an upstream opening end portion of the downstream inner
tube 43.
[0064] An annular protruding portion (engaging portion) 42b of an
annular shape is formed on an inner peripheral surface 42a of the
upstream inner tube 42. This annular protruding portion 42b
protrudes radially inward from the inner peripheral surface 42a and
is formed along the circumferential direction of the inner
peripheral surface 42a. Moreover, multiple bolt holes 42c are
formed in the annular protruding portion 42b at the same interval
as the interval of bolt holes 53 along the circumferential
direction.
[0065] On the other hand, an annular protruding portion (engaging
portion) 43b of an annular shape is formed on an inner peripheral
surface 43a of the downstream inner tube 43. This annular
protruding portion 43b protrudes radially inward from the inner
peripheral surface 43a and is formed along the circumferential
direction of the inner peripheral surface 43a. Moreover, multiple
bolt holes 43c are formed in the annular protruding portion 43b at
the same interval as the interval of the bolt holes 53 along the
circumferential direction.
[0066] Specifically, the combustor swirler basket 11 is such that
the annular protruding portions 42b and 43b are disposed side by
side in the axial direction of the combustor swirler basket 11 and
the bolt holes 42c and 43c are disposed coaxially with each other
by bringing the downstream opening end portion of the upstream
inner tube 42 and the upstream opening end portion of the
downstream inner tube 43 into contact with each other. Here, a gap
equivalent to the thickness of a base plate 15 is formed between
the annular protruding portions 42b and 43b.
[0067] Moreover, the base plate 15 is engaged between the annular
protruding portions 42b and 43b such that the bolt holes 42c and
43c and the bolt holes 53 communicate with each other. The base
plate 15 and the annular protruding portions 42b and 43b in this
engaged state are fixed to each other in the thickness direction of
the base plate 15 with bolts 60.
[0068] In other words, the base plate 15 is held between the
annular protruding portions 42b and 43b when the upstream inner
tube 42 and the downstream inner tube 43 are brought into contact
with each other, and the bolts 60 are inserted into the bolt holes
42c, 43c, and 53 from a downstream surface 15b side. In this way,
the base plate 15 can be fixed to the annular protruding portions
42b and 43b at the same time as when the upstream inner tube 42 and
the downstream inner tube 43 are connected.
[0069] Thus, to form the combustor swirler basket 11 by bringing
the upstream inner tube 42 and the downstream inner tube 43 into
contact with each other, the base plate 15 is engaged between the
annular protruding portions 42b and 43b formed on the inner
peripheral surfaces 42a and 43a, and the base plate 15 and the
annular protruding portions 42b and 43b in this state are fixed to
each other with the bolts 60. In this way, the base plate 15 can be
easily attached and detached. Accordingly, the maintainability of a
pilot burner 13, main burners 14, and the base plate 15 can be
improved.
[0070] Moreover, since the base plate 15 is engaged between the
annular protruding portions 42b and 43b, and the bolts 60 are made
attachable and detachable from the downstream surface 15b side of
the base plate 15, the attachment and detachment of the bolts 60
can be easily done via a downstream opening end portion of the
combustor swirler basket 11.
[0071] Next, a gas turbine combustor according to a sixth
embodiment of the present invention will be described in detail
with reference to FIG. 8.
[0072] As shown in FIG. 8, a base plate 15 is engaged between
annular protruding portions 42 and 43 such that bolt holes 42c and
43c and bolt holes 53 communicate with each other. Moreover, the
base plate 15 and the annular protruding portions 42 and 43 in this
engaged state are fixed to each other in the thickness direction of
the base plate 15 with bolts 60.
[0073] In other words, the base plate 15 is held between annular
protruding portions 42b and 43b when the upstream inner tube 42 and
the downstream inner tube 43 are brought into contact with each
other, and the bolts 60 are inserted into the bolt holes 42c, 43c,
and 53 from an upstream surface 15a side. In this way, the base
plate 15 can be fixed to the annular protruding portions 42b and
43b at the same time as when the upstream inner tube 42 and the
downstream inner tube 43 are connected.
[0074] Thus, the base plate 15 can be easily attached and detached.
Accordingly, the maintainability of a pilot burner 13, main burners
14, and the base plate 15 can be improved.
[0075] Next, a gas turbine combustor according to a seventh
embodiment of the present invention will be described in detail
with reference to FIG. 9.
[0076] As shown in FIGS. 2 and 9, multiple bolt holes 54 are formed
in an outer peripheral portion of a base plate 15 (radially outside
support holes 52). These bolt holes 54 are blind holes radially
penetrating the base plate 15 from its outer peripheral end surface
15c, and are disposed at an equal angular interval along the
circumferential direction of the base plate 15. Note that, of the
multiple bolt holes 54, two bolt holes 54 are representatively
illustrated in FIG. 2.
[0077] On the other hand, as shown in FIG. 9, an annular step
portion (engaging portion) 44 of an annular shape is formed on an
inner peripheral surface 11a of a combustor swirler basket 11. This
annular step portion 44 protrudes radially inward from the inner
peripheral surface 11a, and is formed along the circumferential
direction of the inner peripheral surface 11a.
[0078] Further, multiple bolt holes 45 are formed in the inner
peripheral surface 11a immediately below the annular step portion
44. These bolt holes 45 are through-holes radially penetrating
through the combustor swirler basket 11 and are formed at the same
interval as the interval of the bolt holes 54.
[0079] Moreover, the base plate 15 is engaged with the annular step
portion 44 such that the bolt holes 45 and the bolt holes 54
communicate with each other. The combustor swirler basket 11 and
the base plate 15 in this engaged state are fixed to each other in
the radial direction with bolts 60.
[0080] Specifically, the base plate 15 can be fixed to the inner
peripheral surface 11a of the combustor swirler basket 11 by
engaging the base plate 15 with the annular step portion 44 and
inserting the bolts 60 into the bolt holes 45 and 54 from radially
outside the combustor swirler basket 11.
[0081] Thus, the base plate 15 can be easily attached and detached
by forming the annular step portion 44 on the inner peripheral
surface 11a of the combustor swirler basket 11, engaging the
annular step portion 44 and the base plate 15 with each other, and
fixing the inner peripheral surface 11a of the combustor swirler
basket 11 and the outer peripheral end surface 15c of the base
plate 15 to each other. Accordingly, the maintainability of a pilot
burner 13, main burners 14, and the base plate 15 can be
improved.
[0082] Moreover, since the inner peripheral surface 11a of the
combustor swirler basket 11 and the outer peripheral end surface
15c of the base plate 15 are fixed with the bolts 60, the bolts 60
are not disposed inside the combustor swirler basket 11.
Accordingly, compressed air A supplied in the combustor swirler
basket 11 can flow without being disturbed.
INDUSTRIAL APPLICABILITY
[0083] The present invention is applicable to gas turbine
combustors in which a pilot burner and main burners can be attached
accurately.
* * * * *