U.S. patent application number 15/726447 was filed with the patent office on 2019-04-11 for segmented fuel distributor.
The applicant listed for this patent is PRATT & WHITNEY CANADA CORP.. Invention is credited to Gavin Rohiteshwar KISUN, Aleksandar KOJOVIC, Oleg MORENKO.
Application Number | 20190107285 15/726447 |
Document ID | / |
Family ID | 65992247 |
Filed Date | 2019-04-11 |
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United States Patent
Application |
20190107285 |
Kind Code |
A1 |
MORENKO; Oleg ; et
al. |
April 11, 2019 |
SEGMENTED FUEL DISTRIBUTOR
Abstract
There is provided a segmented fuel distributor for injecting
fuel into a combustion chamber. The segmented fuel distributor
comprises segments serially interconnected in to provide an annular
structure. The segments include a main conduit defining a first
axis along which a main fuel flow path extends. The segments having
two or more secondary conduits extending from the main conduit and
being in fluid flow communication therewith, and fuel injectors
fluidly connected to the secondary conduits at remote ends
thereof.
Inventors: |
MORENKO; Oleg; (Oakville,
CA) ; KOJOVIC; Aleksandar; (Oakville, CA) ;
KISUN; Gavin Rohiteshwar; (Mississauga, CA) |
|
Applicant: |
Name |
City |
State |
Country |
Type |
PRATT & WHITNEY CANADA CORP. |
Longueuil |
|
CA |
|
|
Family ID: |
65992247 |
Appl. No.: |
15/726447 |
Filed: |
October 6, 2017 |
Current U.S.
Class: |
1/1 |
Current CPC
Class: |
F23R 3/283 20130101;
F02C 7/222 20130101; F05D 2240/40 20130101; F23R 3/286 20130101;
F23R 3/002 20130101; F23R 3/50 20130101; F23R 3/34 20130101; F05D
2230/53 20130101 |
International
Class: |
F23R 3/34 20060101
F23R003/34; F23R 3/28 20060101 F23R003/28 |
Claims
1. A segmented fuel distributor for injecting fuel into a
combustion chamber of a gas turbine engine, the segmented fuel
distributor comprising a plurality of segments configured to be
serially interconnected in fuel flow communication to provide an
annular structure, the segmented fuel distributor configured for
mounting to an external casing of the gas turbine engine, the
segments including a main conduit defining a first axis along which
a main fuel flow path extends, the segments having two or more
secondary conduits extending from the main conduit and being in
fluid flow communication therewith, and fuel injectors fluidly
connected to the secondary conduits at remote ends thereof.
2. The segmented fuel distributor of claim 1, wherein the main
conduit of each of the segments is fluidly connected to main
conduits of circumferentially adjacent segments via transfer tubes,
a connection between the transfer tubes and the main conduits being
flexible.
3. The segmented fuel distributor of claim 1, wherein each of the
secondary conduits defines a second axis disposed at an angle
relative to the first axis of the main conduit.
4. The segmented fuel distributor of claim 3, wherein the angle
between the second axis and the main conduit is from 15.degree. to
90.degree..
5. The segmented fuel distributor of claim 1, wherein the main
conduit and the secondary conduits are integrally formed.
6. The segmented fuel distributor of claim 1, wherein the segments
have three of the secondary conduits.
7. The segmented fuel distributor of claim 1, wherein the secondary
conduits extend away from each other from the first axis toward the
remote ends.
8. The segmented fuel distributor of claim 1, further comprising
fuel injector receiving members each affixed to a respective one of
the remote ends of the secondary conduits, the fuel injectors
fluidly connected to the secondary conduits via the fuel injector
receiving members.
9. The segmented fuel distributor of claim 8, wherein the fuel
injectors are slidingly received within cavities of the fuel
injector receiving members.
10. The segmented fuel distributor of claim 8, wherein the fuel
injector receiving members define cooling cavities fluidly
connected to an environment of the segmented fuel distributor.
11. The segmented fuel distributor of claim 8, wherein fuel
cavities are defined between the fuel injectors and the fuel
injector receiving members, the fuel cavities fluidly connected to
the secondary conduits.
12. A combustor for a gas turbine engine, comprising a casing and a
segmented fuel distributor affixed to the casing and configured for
injecting fuel into a combustion chamber of the combustor, the
segmented fuel distributor comprising a plurality of segments
serially interconnected in fuel flow communication, the segments
including a main conduit defining a first axis along which a main
fuel flow path extends, the segments having two or more secondary
conduits extending from the main conduit and being in fluid flow
communication therewith, and fuel injectors fluidly connected to
the secondary conduits at remote ends thereof.
13. The combustor of claim 12, wherein the main conduit of each of
the segments is fluidly connected to main conduits of
circumferentially adjacent segments via transfer tubes, a
connection between the transfer tubes and the main conduits being
flexible.
14. The combustor of claim 12, wherein each of the secondary
conduits defines a second axis disposed at an angle relative to the
first axis of the main conduit.
15. The combustor of claim 14, wherein the angle between the second
axis and the main conduit is from 15.degree. to 90.degree..
16. The combustor of claim 12, wherein the secondary conduits
extend away from each other from the first axis toward the remote
ends thereof.
17. The combustor of claim 12, further comprising fuel injector
receiving members each affixed to a respective one of the remote
ends of the secondary conduits, the fuel injectors fluidly
connected the secondary conduits via the fuel injector receiving
members.
18. The combustor of claim 12, wherein the casing defines apertures
for receiving the fuel injectors therethrough, and wherein the
casing defines cylindrical protrusions each disposed around a
respective one of the apertures, fuel injector receiving members
affixed to the remote ends of the secondary conduits being each
received within a respective one of the cylindrical
protrusions.
19. A method of assembling a combustor of a gas turbine engine,
comprising: disposing fuel distribution segments circumferentially
around a central axis of the combustor, the fuel distribution
segments having two or more fuel injectors; fluidly connecting the
fuel distribution segments with two respectively adjacent ones of
the fuel distribution segments to form a segmented fuel
distributor; and securing the segmented fuel distributor to a
casing of the combustor.
20. The method of claim 19, wherein fluidly connecting the fuel
distribution segments comprises fluidly connecting the fuel
distribution segments with the two respectively adjacent ones of
the fuel distribution segments with transfer tubes, a connection
between the transfer tubes and the fuel distribution segments being
flexible.
Description
TECHNICAL FIELD
[0001] The application relates generally to gas turbine engines
and, more particularly, to systems and methods for injecting fuel
in combustors of such engines.
BACKGROUND
[0002] Existing fuel manifolds for gas turbine engines include
internal fuel manifolds and external fuel manifolds. While internal
fuel manifolds are advantageous in a number of respects (e.g.
weight, cost, etc.), they are not as easily removed and/or
accessible for maintenance purposes as their more
traditionally-used external counterparts. For example, a gas
turbine engine with an internal fuel manifold must be split apart
in order to access the fuel manifold for service and/or
replacement. Consequently, such operations cannot be done in the
field and involve more time, cost and engine downtime.
SUMMARY
[0003] In one aspect, there is provided a segmented fuel
distributor for injecting fuel into a combustion chamber of a gas
turbine engine, the segmented fuel distributor comprising a
plurality of segments serially interconnected in fuel flow
communication to provide an annular structure, the segmented fuel
distributor configured for mounting to an external casing of the
gas turbine engine, the segments including a main conduit defining
a first axis along which a main fuel flow path extends, the
segments having two or more secondary conduits extending from the
main conduit and being in fluid flow communication therewith, and
fuel injectors fluidly connected to the secondary conduits at
remote ends thereof.
[0004] In another aspect, there is provided a combustor for a gas
turbine engine, comprising a casing and a segmented fuel
distributor affixed to the casing and configured for injecting fuel
into a combustion chamber of the combustor, the segmented fuel
distributor comprising a plurality of segments serially
interconnected in fuel flow communication, the segments including a
main conduit defining a first axis along which a main fuel flow
path extends, the segments having two or more secondary conduits
extending from the main conduit and being in fluid flow
communication therewith, and fuel injectors fluidly connected to
the secondary conduits at remote ends thereof.
[0005] In yet another aspect, there is provided a method of
assembling a combustor of a gas turbine engine, comprising:
disposing fuel distribution segments circumferentially around a
central axis of the combustor, the fuel distribution segments
having two or more fuel injectors; fluidly connecting the fuel
distribution segments with two respectively adjacent ones of the
fuel distribution segments to form a segmented fuel distributor;
and securing the segmented fuel distributor to a casing of the
combustor.
BRIEF DESCRIPTION OF THE DRAWINGS
[0006] Reference is now made to the accompanying figures in
which:
[0007] FIG. 1 is a schematic cross-sectional view of a gas turbine
engine;
[0008] FIG. 2 is a schematic tridimensional view of a segmented
fuel distributor in accordance with one embodiment;
[0009] FIG. 3 is a schematic front view of a fuel carrying segment
of the segmented fuel distributor of FIG. 2;
[0010] FIG. 3a is a schematic top view of a segmented fuel
distributor comprising fuel carrying segments in accordance with
another embodiment;
[0011] FIG. 4 is a schematic cross-sectional view of a portion of
the segmented fuel distributor of FIG. 2;
[0012] FIG. 5 is a schematic tridimensional cross-sectional view of
a portion of the segmented fuel distributor of FIG. 2;
[0013] FIG. 6 is a schematic tridimensional view of the segmented
fuel distributor of FIG. 3a; and
[0014] FIG. 7 is a schematic top cross-sectional view of the
segmented fuel distributor of FIG. 6.
DETAILED DESCRIPTION
[0015] FIG. 1 illustrates a gas turbine engine 10 of a type
preferably provided for use in subsonic flight, generally
comprising in serial flow communication a fan 12 through which
ambient air is propelled, a compressor section 14 for pressurizing
the air, a combustor 16 in which the compressed air is mixed with
fuel and ignited for generating an annular stream of hot combustion
gases, and a turbine section 18 for extracting energy from the
combustion gases. The compressor section 14, the fan 12, and the
turbine section 18 rotate about a central axis 11 of the gas
turbine engine 10. In the embodiment shown, the combustor 16 is
surrounded by a casing 20 disposed around the central axis 11.
[0016] Referring now to FIG. 2, a portion of the casing 20 and a
segmented fuel distributor 22 affixed thereto are shown. The
segmented fuel distributor 22 comprises individual fuel carrying
segments 24 serially interconnected in fuel flow communication to
form an annular structure 26. In the embodiment shown, the
individual fuel carrying segments 24 are interconnected with each
other with transfer tube assemblies 28. The transfer tube
assemblies 28 are configured to allow a flexibility of the
segmented fuel distributor 22. A combustion chamber 30 is located
radially inward to the casing 20 relative to the central axis 11.
Using such transfer tube assemblies 28 might offer certain
advantages. In a particular embodiment, the segmented fuel
distributer 22 allows for the reduction of weight, components
count, installation and service time, possible leak locations, and
allows for movement resulting from radial thermal growth. In the
embodiment shown, each of the fuel carrying segments 24 acts as a
single fuel nozzle having several fuel injection points 32. In one
particular embodiment, the fuel carrying segments 24 are made of
AMS 5401/INCONEL 625 or other suitable metal.
[0017] Referring now to FIG. 3, one of the individual fuel carrying
segments 24 is shown. In the embodiment shown, the fuel carrying
segment 24 includes a main conduit 34 extending along a
longitudinal axis L along which a primary fuel flow path 36
extends. The fuel carrying segment 24 further includes two or more
secondary conduits 38, which may also be referred to as stems,
extending away from the main conduit 34 and which each define a
secondary fuel flow path. In the depicted embodiment, the fuel
carrying segment 24 includes three secondary conduits 38, however
it is to be understood that in alternate embodiments there may be
only two secondary conduits 38 or there may be more than three
secondary conduits 38. In one particular embodiment, the main
conduit 34 and the secondary conduits 38 are integrally formed with
each other to define a monolithic component. In the depicted
embodiment, the secondary conduits 38 are disposed at respective
angles .alpha. relative to the main conduit 34 along respective
longitudinal axes L'. Secondary fuel flow paths 40 extend through
the secondary conduits 38 and are fluidly connected with the main
flow path 36 of the main conduit 34. The fuel carrying segment 24
may comprise from two to five, or more, secondary conduits 38. The
segmented fuel distributor 22 may comprise simultaneously
individual fuel carrying segments 24 having different numbers of
secondary conduits 38. The angles between the longitudinal axes L
and L' may range from 15.degree. to 90.degree.. The secondary
conduits 38 extend away from each other from the longitudinal axis
toward remote ends 38a of the secondary conduits 38 relative to a
radial distance from the longitudinal axis L. In other words, an
axial distance between two of the secondary conduits 38 relative to
the longitudinal axis L increases with a radial distance from said
longitudinal axis L.
[0018] The main conduit 34 defines two opposed ends 42 and 44
spaced apart from each other along the longitudinal axis L. The two
opposed ends 42 and 44 circumscribe openings 46 for receiving a
fuel flow to be injected into the combustion chamber 30. In the
embodiment shown, the two opposed ends 42, 44 of the main conduit
34 are configured to be fluidly connected with circumferentially
adjacent ones of the individual fuel carrying segments 24 via the
transfer tube assemblies 28. For that purpose, the fuel carrying
segment 24 defines coupling portions 34a adjacent the opposed ends
42, 44 and formed integrally with the main conduit 34.
[0019] The coupling portions 34a are configured for being sealingly
connected to the transfer tube assemblies 28. In the embodiment
shown, a diameter of the coupling portions 34a is greater than a
diameter of the main conduit 34. Each of the coupling portions 34a
defines a first annular groove 34b. One of the coupling portions
34a defines a second annular groove 34c of a depth less than that
of the other annular grooves 34b and disposed beyond the first
annular groove 34b relative to a distance from end 42. In a
particular embodiment, the second annular groove 34c is configured
for receiving external snap ring or circlip 45 (FIG. 3a) to limit
movement of an outer sleeve 68 (FIG. 5). In the embodiment shown,
the first annular grooves 34b are configured for receiving O-rings
(not shown) for creating a sealing engagement between the coupling
portions 34a and the outer sleeve 68. The outer sleeve 68 may then
be able to contain a fuel leak. The leaked fuel may be able to
drain through drain passages 34e (FIG. 5) defined in the fuel
carrying segments 24.
[0020] The fuel carrying segment 24 further includes fuel injector
receiving members 50 disposed at the remote, or distal ends 38a of
the secondary conduits 38. The fuel carrying segment 24 further
includes fuel injectors 52 (FIGS. 4-5) configured for being
received by the fuel injector receiving members 50. The assembly of
the fuel injectors 52 within the fuel injector receiving members 50
is described herein below.
[0021] In the embodiment shown, the main conduit 34, the secondary
conduits 38, and the fuel injector receiving members 50 are
integrally formed by suitable manufacturing processes. In the
embodiment shown, the fuel carrying segment 24 is integrally formed
and fuel passages are formed by manufacturing along the
longitudinal axes L and L' of the main and secondary conduits 34
and 38. Manufactured holes 54 are shown for illustration purposes.
It is understood that the manufactured holes 54 are suitably
clogged to preclude fluid flow communication between the main and
secondary flow paths 36 and 40 and an environment E (FIG. 2) of the
segmented fuel distributor 22. The fuel carrying segments 24 may be
manufactured using metal injection molding (MIM) or additive
manufacturing (AM), or other technologies to create complex shapes
which might be optimized for weight. In a particular embodiment,
the MIM/AM manufacturing is unable to create the fuel passages
within the conduits. Said passages may then be manufactured and
plug welded at any location where they interface with the
environment E. As discussed below, the shape of the fuel carrying
segments 24 might improve cooling with ambient air.
[0022] Referring now to FIG. 3A, another embodiment of a fuel
carrying segment 24' is illustrated. For the sake of clarity, only
the elements that are different than the fuel carrying segment 24
of FIG. 3 are described herein below. In the embodiment shown, the
secondary conduits 38' of the fuel carrying segment 24' have an
L-shape and extend from the main conduit 34'. An angle .beta.
between the main conduit 34' and the secondary conduits 38' may, in
one particular embodiment, range from about 5 degrees to about 175
degrees. The secondary conduits 38' each define an angle .theta.
such that the secondary conduits 38' curve radially inwardly to
reach the fuel injector receiving members 50. In one particular
embodiment, the angle .theta. may range from about 60 degrees to
about 130 degrees, and an angle between said members 50 and the
secondary conduits 38' may be about 90 degrees. However, it is to
be understood that other configurations and other ranges for both
angle .beta. and angle .theta. can also be used, and will depend
upon the specific configuration required, engine architecture,
design requirements and parameters, etc.
[0023] Referring now also to FIG. 4, each of the fuel injector
receiving members 50 has a cylindrical shape extending
perpendicularly to a respective one of the secondary conduits 38.
In the embodiment shown, each of the fuel injector receiving
members 50 defines two cavities 50a and 50b separated by a wall
50c. The two cavities 50a and 50b overlap each other along a given
length relative to a central axis L'' of the fuel injector
receiving member 50. In the embodiment shown, the two cavities 50a
and 50b decrease in height, or diameter, toward a center of the
fuel injector receiving member 50 relative to its central axis
L''.
[0024] One of the two cavities 50b is shaped for slidingly and
sealingly receiving one of the fuel injectors 52 therein. In the
embodiment shown, the other of the two cavities 50a faces away from
the casing 20 and is also referred to as a first cooling cavity 50a
configured for receiving air from the environment E of the
segmented fuel distributor 22. The air circulating in the first
cooling cavity 50a might reduce a temperature of the fuel carrying
segment 24. In the depicted embodiment, the fuel injector receiving
member 50 further defines a second cooling cavity 50d configured
for receiving a flow of air from the environment E and is fluidly
connected with the first cooling cavity 50a.
[0025] The secondary flow paths 40 extend through the fuel injector
receiving members 50 such that the fuel injectors 52 are in fluid
flow communication with the one of the two cavities 50b. Fuel
cavities 56 are defined between the fuel injectors 52 and
cylindrical walls of the fuel injector receiving members 50. The
fuel cavities 56 are fluidly connected with the one of the two
cavities 50b and with the main conduit 34 via the secondary
conduits 38. Stated otherwise, the fuel cavities 56 are fluidly
connected with the main flow path 36 via the secondary flow paths
40.
[0026] Still referring to FIG. 4, the fuel injectors 52 define
outlets 58 fluidly connected to the main conduit 34 via the
secondary conduits 38, along the main and secondary flow paths 36
and 40, and via the fuel cavities 56, for injecting fuel in the
combustion chamber 30. Any suitable fuel injector may be used. The
fuel injectors 52 may be integrally formed with the fuel carrying
segments 24 or separated as shown.
[0027] Referring now also to FIG. 5, apertures 20a are defined
through the casing 20 for allowing the fuel injectors 52 to extend
therethrough. Each of the apertures 20a is surrounded by a
respective one of cylindrical protrusions 20b, also referred to as
slotted bosses, that are hollow for slidingly receiving the fuel
injector receiving members 50 therein. In the embodiment shown, a
diameter of the apertures 20a is less than that of an inner
diameter of the cylindrical protrusions 20b to define annular tabs
20c. The fuel injector receiving members 50, once disposed within
the cylindrical protrusions 20b may abut against the annular tab
20c.
[0028] The cylindrical protrusions 20b are hollow and are each
shaped for receiving therein a respective one of the fuel injector
receiving members 50 of the fuel carrying segments 24. Each of the
cylindrical protrusions 50 defines a slot 20d for allowing the
secondary conduits 38 to extend through the cylindrical protrusions
20b. In the embodiment shown, inner surfaces of the cylindrical
protrusions 20b are threaded for receiving nuts 64 to be screwed
therein to limit movements of the fuel injector receiving members
50 when they are received within the cylindrical protrusions 20b.
In the depicted embodiment, the nuts 64 are hollow for allowing
fluid flow communication between the first cooling cavity 50a and
the environment E.
[0029] In the embodiment shown, gaskets 62 are disposed between the
fuel injector receiving members 50 and the cylindrical protrusions
20b for providing a sealing engagement therebetween. In the
depicted embodiment, the gaskets 62 are annular and disposed
adjacent to the annular tabs 20c to be sandwiched between said tabs
20c and the fuel injector receiving members 50. More specifically,
air that has been compressed through its passage in the compressor
section 14 is injected in the combustor chamber 30 for being mixed
with fuel. The gaskets 62 are configured to preclude the compressed
air to escape the combustion chamber 30 via an intersection between
the cylindrical protrusions 20b and the fuel injector receiving
members 50.
[0030] Still referring to FIG. 5, the transfer tube assemblies 28
are illustrated. The transfer tube assemblies 28 each include two
transfer tubes 66 that are disposed within an outer sleeve 68
configured for maintaining a position of the transfer tubes 66
therein. In the embodiment shown, the main conduits 34 define two
inlets 34d each receiving a respective one of the transfer tubes
66. It is understood that the transfer tube assemblies 28 may
comprise less, or more, than two of the transfer tubes 66.
Similarly, the main conduits 34 may comprise less, or more, than
two of the inlets 34d. In the embodiment shown, the transfer tubes
66 are made of AMS 5648/SS 316 stainless steel or other suitable
metal.
[0031] In the embodiment shown, the secondary conduits 38 define
each two fuel passages (not shown) each fluidly connected to a
respective one of the two transfer tubes 66. Therefore, the main
flow path 36 defines two main sub-flow paths 36a and 36b and each
of the secondary conduits 38 defines two secondary sub-flow paths
40a and 40b. The two main sub-flow paths 36a and 36b are in fluid
flow communication with a respective one of the two secondary
sub-flow paths 40a and 40b. In the embodiment shown, the fuel
injectors 52 have each two of the fuel outlets 58 each fluidly
connected to a respective one of the two secondary sub-flow paths
40a and 40b.
[0032] A connection C between the transfer tube assemblies 28 and
the segments 24 offers a flexibility that allows some displacement
of the segments 24 relative to the assemblies 28. Such displacement
might be the result of thermal expansion during use. More
specifically, the flexibility is provided by the interaction
between the transfer tubes 66 and the inlets 34d of the main
conduit 34. In the embodiment shown, the connection C is flexible
and allows variations of about .+-.3 degrees between a longitudinal
axis of each of the transfer tubes 66 and the main conduit 34 of
the segments 24.
[0033] Referring now to FIGS. 3a, 6, and 7, the outer sleeve 68 has
a cylindrical shape and defines two ends 68a and 68b that have a
diameter greater than that of a central section 68c disposed
between the two ends 68a, 68b. In the embodiment shown, two ends
68a, 68b are each configured for receiving therein the coupling
portions 34a' of the segments 24'. O-rings (not shown) may be
disposed within the annular grooves 34b' to create a sealing
engagement between the coupling portions 34a and the outer sleeve
ends 68a, 68b.
[0034] The outer sleeve 68 further includes two tabs 68d each
defining an aperture. In the embodiment shown, the two tabs are
diametrically opposed relative to a longitudinal axis of the outer
sleeve 68. The tabs 68d are configured for manipulating the outer
sleeve 68, and thus any transfer tube assemblies 28 mounted
thereto, in order to position and move the transfer tube assemblies
28 and/or the outer sleeve 68 into or out of a desired position.
Thus, the tabs 68d can be used to push or pull and simultaneously
engage or disengage the transfer tubes and the outer sleeve with a
corresponding fuel carrying segment 24 or fuel nozzle.
[0035] Referring more particularly to FIG. 7, the outer sleeve 68
encloses a support member 68e defining two apertures for receiving
therein, and for supporting, the transfer tubes 66. In the
embodiment shown, the support member 68e limits radial and/or axial
movements of the tubes 66 relative to the outer sleeve 68. In the
embodiment shown, each of the two transfer tubes 66 have two
sections 66a, 66b that are jointed together at a location of the
support member 68e. Each of the two sections 66a, 66b defines
abutment portions 66c configured for abutting against the support
member 68e. The abutment portions 66c are configured to limit axial
movement of each of the two sections 66a, 66b toward each
other.
[0036] Referring to FIGS. 1 to 7, to assemble the combustor 16 of
the gas turbine engine 10 the fuel distribution segments 24 are
first circumferentially distributed around the central axis of the
combustor 11. Then, the fuel distribution segments 24 are each
fluidly connected with two respectively adjacent ones of the fuel
distribution segments 24 with the transfer tubes 66 of the transfer
tube assemblies 28 to form the segmented fuel distributor 22. Then,
the segmented fuel distributor 22 is secured to the casing 20.
[0037] More specifically, the fuel injector receiving members 50
are each secured to the casing 20, within a respective one of the
cylindrical protrusions 20b, with the nuts 64 screwed in the
cylindrical protrusions 20b.
[0038] Referring more particularly to FIG. 5, the two transfer
tubes 66 are coupled with the inlets 34d defined by the main
conduits 34 of the fuel carrying segments 24. Therefore, the fuel
injectors 52 are each fluidly connected to both of the transfer
tubes 66 via the connections C.
[0039] In the depicted embodiment, the fuel injector receiving
members 50 are pushed in a sealing engagement against the gaskets
62 that abut against the annular tabs 20c defined by the casing 20.
The nut 64 may be used for that purpose.
[0040] In the embodiment shown, the fuel injector receiving members
50, which are disposed at the remote ends 38a (FIG. 3) of the
secondary conduits 38 are disposed in the cylindrical protrusions
20b extending from the casing 20. In the depicted embodiment, the
fuel injectors 52 are fluidly connected to the fuel injector
receiving members 50 of the fuel distribution segments 24 during
the assembly.
[0041] Referring more particularly to FIG. 6, following
installation of the fuel injector receiving members 50 within the
cylindrical protrusions 20b, the transfer tube assemblies 28 are
each slid and locked into position. More specifically, the outer
sleeve ends 68a are slid over first coupling portions 34a of the
main conduit 34. Then, the transfer tube assemblies 28 are each
slid toward second coupling portions 34a of an adjacent one of the
segments 24. Then, the circlips 45 (FIG. 3a) are each disposed
within the second annular grooves 34c (FIG. 3) of the first
coupling portions 34a to limit a sliding movement between the outer
sleeves 68 and the coupling portions 34a.
[0042] The above description is meant to be exemplary only, and one
skilled in the art will recognize that changes may be made to the
embodiments described without departing from the scope of the
invention disclosed. Still other modifications which fall within
the scope of the present invention will be apparent to those
skilled in the art, in light of a review of this disclosure, and
such modifications are intended to fall within the appended
claims.
* * * * *