Note: Descriptions are shown in the official language in which they were submitted.
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COMBUSTOR ASSEMBLY AND METHOD
FIELD OF THE INVENTION
[0001] The present invention re1 ates to a gas turbine engine
combustor.
BACKGROUND OF THE INVENTION
[0002] Gas turbine engine comk-)ustors in use in aircraft
engine applications often inc':ude an inner and outer liner
which are joined to enclc:ae a space to provide a
combustion chamber. Typicaliy, little attention is paid
to how the inner and outer ccmbustor liners are attached,
however. Since it is well-known that unnecessary weight
is to be avoided in aircraft. applications, opportunities
for weight reduction should no.: be ignored.
SUNIlMARY OF THE INVENTION
[0003] One object of the preserIt invention is to provide a
low cost combustor burner co-Llar assembly which positions
a fuel burner in a passage opf~ning in an upstream end wall
of a combustor and permits the thermal expansion and
contraction thereof with respect to the upstream end wall
of the combustor.
[0004] Another object of the present invention is to provide
a head part of a gas engine combustor wherein a single
piece fuel burner collar is radial-displaceably secured to
the combustor only by a heat shield attached to the
combustor wall.
[0005] In accordance with one aspect of the present
invention, there is provided a head part of an annular
combustor for a gas turbine engine having an upstream end
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wall with passage openings each of which accommodates a
fuel burner. The head part comprises a heat shield
detachably secured to a downstream side of the upstream
end wall and covering an inner surface thereof, and a
burner collar positioned w=ithin each of the passage
openings and accommodating a corresponding one of the fuel
burners. The burner collar has a radial flange with
opposed first and second annular radial surfaces. The
burner collar is axially restrained directly by the
upstream end wall and the hea'_- shield in a manner wherein
a radial surface of the dowristream side of the upstream
end wall abuts the first annular radial surface of the
flange, and a radial surface of an upstream side of the
heat shield abuts the second annular radial surface of the
flange, such that the b:zrner collar is radially
displaceable with respect to the upstream end wall.
[0006]The burner collar preferably includes an annular
cylinder, and the radial f'-ange extends radially and
outwardly from the external periphery of the annular
cylinder.
[0007] In one embodiment of the present invention the burner
collar includes an annular cylinder and a skirt portion
having an outer diameter sma::ler than a diameter of the
passage opening in the upstream end wall of the combustor.
The flange preferably extends radially and outwardly from
a downstream end of the annular cylinder and has an outer
diameter greater than the dianieter of the passage opening.
The heat shield preferably has threaded studs which are
integrated with the heat shield and extend through
openings in the upstream eiid wall of the combustor.
Self-locking nuts are used to engage the respective
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threaded studs in order to secure the heat shield to the
upstream end wall. The heat shield has a configuration
such that when the heat shield is secured to the upstream
end wall the radial surface of the heat shield is axially
spaced a predetermined distance apart from the radial
surface of the downstream sidE~ of the upstream end wall to
form a gap for fittably and radial-displaceably
accommodating the flange of the burner collar therein.
[0008] In accordance with another aspect of the present
invention, there is provided a method for securing a
burner collar to a gas turbine engine combustor for
accommodating a fuel burner r,adial-displaceably positioned
in a passage opening in an upstream end wall of the
combustor. The method coniprises a step of axially
restraining the burner collar in the passage opening by
using a heat shield which is detachably secured to a
downstream side of the upstream end wall and covering an
inner surface thereof, to directly abut a radial flange of
the burner collar against a radial surface of the upstream
end wall of the combustor suc:~h that the burner collar is
radially displaceable with respect to the upstream end
wall of the combustor.
[0009] In contrast to multi-part assemblies of burner
collars in the prior art, the present invention
advantageously provides a single piece configuration of a
burner collar which needs no additional parts to hold the
burner collar in position. Lnstead, the axial flange of
the burner collar is sirnply clamped between the
conventional heat shield and the upstream end wall of the
combustor. Therefore, the burner collar can be
manufactured economically and. the overall weight of the
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gas turbine engine combustor can be reduced, which is also
a desirable advantage especially when the gas turbine
engine is used in aircraft.
[0010] Other advantages and features of the present
invention will be better understood with reference to a
preferred embodiment of the present invention described
hereinafter.
BRIEF DESCRIPTION OF THE DRAWINGS
[0011] Having thus generally described the nature of the
invention, reference will now be made to the accompanying
drawings, showing a preferred embodiment by way of
illustration, in which:
[0012] Fig. 1 is a partial cross-sectional view of a gas
turbine engine, showing an annular combustor incorporating
an embodiment of the present invention;
[0013] Fig. 2 is a partial cross-sectional view of an
annular combustor in an enlarged scale, illustrating
details of the embodiment shown in Fig. 1;
[0014] Fig. 3 is a front view of a heat shield used in the
embodiment in Fig. 1, showincx the upstream side thereof;
and
[0015] Fig. 4 is a rear view of a burner collar used in the
embodiment of Fig. 1, showing the downstream side thereof.
DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENT
[0016] Referring to the drawings, particularly to Fig. 1, an
annular combustor 10 is shown. The inner casing 12 of the
annular combustor 10 includes radially spaced annular
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inner and outer walls 14 and 16 respectively,
interconnected at their upstream ends by means of an
annular upstream end wall, u:_,ually called a bulkhead 18,
to form an annular combustor cnamber 20.
5 [0017] A plurality of passage openings 22 (only one shown)
are provided in the bulkhead 18, each one receiving the
outlet end of a fuel burner 24 which is suspended from an
outer casing structure 26 for delivery of fuel and air
into the combustion chamber 2~0. The passage openings 22
are equally spaced around the bulkhead 18.
[0018]As more clearly shown in Fig. 2, the bulkhead 18 has
a first annular section 30 which integrally extends
radially and inwardly from the annular outer wall 16 of
the combustor 10, and a secc>nd annular section 32 which
integrally extends radially and outwardly from the annular
inner wall 14 of the combustc:>r 10. The first and second
sections 30, 32 are overlapped in part, adjacent to the
annular inner wall 14, and art:, secured together by locking
means which are described with details hereinafter. The
plurality of passage openings 22 are located in the first
annular section 30 of the bulr":head 18.
[0019]The bulkhead 18 is part_icularly vulnerable to over
heating as a result of the combustion process which takes
place within the combustor chamber 20. In order to
provide thermal shielding of the bulkhead 18, segmented
heat shields 34 are attached to the downstream side of the
first annular section 30 of the bulkhead 18, covering an
inner surface 36 thereof. Heat shields 38, 40 are also
provided to cover the inner surfaces of the respective
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annular inner and outer walls 14, 16 at an area adjacent
to the bulkhead 18.
[0020]As more clearly shown in Fig. 3, each heat shield 34
is of generally truncated sectorial configuration, having
ridges 41, 42, 44 and 46 projecting from the shield
plate 48. The shield plate 48 has a circular opening 50
having a diameter smaller than the passage openings 22 of
the bulkhead 18 and greater than the periphery of the
outlet end of the fuel bur.-ner 24 (see Fig. 2). The
ridge 41 is circular and defines the periphery of the
opening 50, and includes a radial surface 52. The
ridge 42 is also circular, radially spaced apart from the
ridge 41, and as more clearly shown in Fig. 2, the
ridge 42 has a thickness greater than the thickness of
ridge 41. Ridges 44, 46 havf~ the same thickness as that
of ridge 42 so that the ridiges 42, 44 and 46 provide an
equal spacing between the shield plate 48 and the inner
surface 36 of the first section 30 of the bulkhead 18 when
the heat shield 34 is secured to the bulkhead 18.
[0021] As illustrated in Fig. 2, the heat shield 34 includes
a plurality of threaded studs 54 extending from a
thickened portion 56 (see Fiq. 3) of the shield plate 48.
The thickened portion 56 has a thickness equal to or
slightly less than the thickness of the ridges 42, 44
and 48 to maintain the equal and even spacing. Small
holes 58 and 60 in the respective shield 34 and the
bulkhead 18 form cooling air passages to direct
pressurized cool air from outside of the combustor
chamber 20, through the space between the heat shield 34
and the bulkhead 18, entering the combustor chamber 20 to
cool the bulkhead 18 and the heat shield 34. A plurality
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of pins 62 integrally project from the shield plate 48 to
increase air contacting surfaces of the heat shield 34 for
a better cooling result. The heat shield 34 further
includes inner and outer ridgt:--~s 64, 66 extending outwardly
from the shield plate 48 t.owards the inside of the
combustor chamber 20 to form air channels adjacent to the
heat shields 38, 40 for a better cooling result.
[0022] When the heat shielk:i 34 is mounted to the
bulkhead 18, the threaded studs 54 positioned close to the
annular outer wall 16 extend through mounting holes in the
first annular section 30 and engage with self-locking
nuts 68 and washers 70 to secure the heat shield 34 to the
downstream side of the bulkhead 18. The threaded studs 54
positioned close to the arinular inner wall 14 extend
through mounting holes in the first and second annular
sections 30, 32 to engage with self-locking nuts 68
washers 70 to not only secure the heat shield 34 to the
downstream side of the bulkhead 18, but also to securely
join together the overlappec3 portions of the first and
second annular sections 30, 32 to form the assembled
bulkhead 18.
[0023] The annular radial surface 52 of the annular ridge 41
is spaced apart from the inner surface 36 of the first
annular section 30 of the bulkhead 18 because the
thickness of the ridge 41 is less than the thickness of
the spacing ridges 42, 44 arid 46, forming a gap between
the radial surface 52 of the heat shield 34 and the inner
surface 36 of the bulkhead 18, to fittably accommodate a
radial flange 72 of a burner collar 74.
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[0024] The burner collar 74 includes an annular cylinder 76.
The annular radial flange 72 extends radially and
outwardly from a downstream erid of the annular cylinder 76
and has an outer diameter greater than the passage
opening 22 of the bulkhead 18. A skirt portion 78 extends
radially, axially and outwardly from an upstream end of
the annular cylinder 76 and has an outer diameter smaller
than a diameter of the passage opening 22 of the
bulkhead 18. Thus the buriier collar 74 is positioned
within the passage opening 22 of the bulkhead 18 to
accommodate the fuel burner 4, the inner surface of the
annular cylinder 76 sealir:3ly contacting the outer
periphery of the burner 24 to inhibit pressurized air
outside the combustor chamber 20 from uncontrollable
admission into the combustor chamber 20.
[0025] The distance between the annular radial surface 52 of
the heat shield 34 and the inner surface 36 of the
bulkhead 18 can be predetermined to a high degree of
accuracy during the machinin(.j process. Thus, the radial
inner surface 36 of the bulkhead 18 closely abuts the
radial surface of the annular flange 72 at the upstream
side thereof and the radial surface 52 of the heat
shield 34 closely abuts the radial surface of the annular
flange 32 at the downstream side thereof. Such a
configuration axially restra-ins the position of the burner
collar 74 with respect to t:ie bulkhead 18 and minimizes
air leakage between the burner collar 74 and the
respective heat shield 34 and the bulkhead 18, while
permitting radial displacement of the burner collar 74
with respect to the bulkhead 18 and the heat shield 34.
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[0026] As more clearly shown in Figs. 3 and 4, the radial
flange 72 of the burner collar 74 further includes a
tab 80 projecting radially and outwardly with a pair of
side surfaces 82. The tab 80 fits into an axial recess 84
in ridge 42 with a pair of side walls 86. Thus, the
interfaces 82 and 86 between the tab 80 and the recess 86
inhibit rotational movement of the burner collar 74 with
respect to the bulkhead 18.
[0027] In a disassembly process, the self-locking nuts 68
and washers 70 positioned close to the annular inner
wall 14 are disengaged frorr the threaded studs 54 to
permit removal of the annular inner wall 14 of the
combustor 10. The self-locking nuts 68 and washers 70
positioned close to the annular outer wall 16 of the
combustor 10 are then disengaged from the studs 54
permitting detachment of tkie heat shield 34 from the
downstream side of the first annular section 16 of the
bulkhead 18. Finally, the burner collar 74 can be
withdrawn from the passage opening 22 of the bulkhead 18
towards the inside of the combustor chamber 20. The
process is reversed in the assembly process thereof.
[0028] Modifications and improvements to the above described
embodiment of the present invention may become apparent to
those skilled in the art. The forgoing description is
intended to be exemplary rather than limiting. The scope
of the invention is therefore intended to be limited
solely by the scope of the appended claims.
