U.S. patent number 3,620,641 [Application Number 04/865,942] was granted by the patent office on 1971-11-16 for bearing assembly.
This patent grant is currently assigned to Rolls-Royce Limited, Derby, GB2. Invention is credited to Francis Anthony Weston, John Michael Storer Keen, Maurice John Byett.
United States Patent |
3,620,641 |
|
November 16, 1971 |
BEARING ASSEMBLY
Abstract
A gas turbine engine comprises in flow sequence compressor
means, combustion means and turbine means, the compressor means and
the turbine means comprising bladed rotors, a shaft supporting at
least one of said bladed rotors, a bearing in which said shaft is
mounted, a fixed substantially cylindrical engine casing, two
axially spaced apart substantially radially extending annular panel
members, said bearing being supported from the fixed casing by way
of said panel members, at least one of said panel members having a
plurality of angularly spaced-apart dished portions, said portions
being secured to the other of said panel members to brace together
and interconnect the panel members.
Inventors: |
John Michael Storer Keen
(Derby, GB2), Maurice John Byett (Derby, GB2), Francis
Anthony Weston (Derby, GB2) |
Assignee: |
Rolls-Royce Limited, Derby, GB2
(N/A)
|
Family
ID: |
10434648 |
Appl.
No.: |
04/865,942 |
Filed: |
October 13, 1969 |
Foreign Application Priority Data
|
|
|
|
|
Oct 6, 1966 [GB3] |
|
|
44,764/66 |
|
Current U.S.
Class: |
415/229; 415/142;
415/208.2; 415/208.1; 415/220 |
Current CPC
Class: |
F16C
35/00 (20130101); F02C 7/20 (20130101); F01D
25/162 (20130101); F16C 2360/23 (20130101) |
Current International
Class: |
F01D
25/16 (20060101); F16C 35/00 (20060101); F02C
7/20 (20060101); F01d 011/08 (); F01d 001/02 () |
Field of
Search: |
;415/115,170,219,213,180,135,217 |
References Cited
[Referenced By]
U.S. Patent Documents
Foreign Patent Documents
Primary Examiner: Henry F. Raduazo
Attorney, Agent or Firm: Cushman, Darby & Cushman
Parent Case Text
This application is a continuation-in-part of our copending
application Ser. No. 668,387 filed Sept. 18, 1967 and now
abandoned.
Claims
We claim:
1. A gas turbine engine comprising in flow sequence compressor
means, combustion means and turbine means, the compressor means and
the turbine means comprising bladed rotors, a shaft supporting at
least one of said bladed rotors, a bearing in which said shaft is
mounted, a fixed substantially cylindrical engine casing, two
axially spaced-apart substantially radially extending annular panel
members, said bearing being supported from the fixed casing by way
of said panel members, at least one of said panel members having a
plurality of angularly spaced apart dished portions, said at least
one panel member having corrugated portions between said dished
portions, and said dished portions being secured to the other of
said panel members to brace together and interconnect the panel
members.
2. A gas turbine engine as claimed in claim 1 wherein the dished
portions are substantially lozenge shaped, as herein defined.
3. A gas turbine engine as claimed in claim 2 wherein the dished
portions each have major and minor axes, the major axes extending
radially of the shaft.
4. A gas turbine engine as claimed in claim 2 wherein the dished
portions are elliptical.
5. A gas turbine engine as claimed in claim 1 wherein the
corrugated portions are constituted by elongated dished portions,
the major axis of each elongated dished portion extending radially
of the shaft.
6. A gas turbine engine as claimed in claim 1 wherein said dished
portions are of relatively rounded shape, further dished portions
being interposed between the relatively rounded dished portions,
and being of relatively elongated shape, each relatively elongated
dished portion having a major axis which extends radially of the
shaft.
7. A gas turbine engine as claimed in claim 1 comprising in each
dished portion a deeper dished portion which secures the said
dished portion to the other of said panel members.
8. A gas turbine engine as claimed in claim 1 comprising means
defining apertures in regions of at least one panel member which
are not dished, the edges of the apertures being deformed out of
the planes of the apertures, forming stiffened rims therefor.
9. A gas turbine engine as claimed in claim 1 wherein the dished
portions are secured to the other of said panel members by
welding.
10. A gas turbine engine as claimed in claim 1 wherein the said
dished portions are integrally formed in said at least one panel
member.
11. A gas turbine engine as claimed in claim 1 wherein said
angularly spaced-apart dished portions are provided in both panels,
said portions being arranged in pairs, one from each panel, the
portions of each pair having their bases secured together.
12. A gas turbine engine as claimed in claim 11, comprising for
each said pair of dished portions a connecting member extending
between said bases securing them together, said connecting member
being an open-ended tubular member having an internal dividing
wall, each open end being respectively secured in an aperture in
the respective base, forming a deeper dished portion therein.
13. A gas turbine engine as claimed in claim 1 including an axially
extending bearing support ring, said bearing being supported by
said ring and said panel members being connected to said ring, a
further bearing also being supported by the ring.
14. A gas turbine engine as claimed in claim 1 including a
plurality of angularly spaced-apart struts secured to said engine
casing, said panel members being secured to said struts, a
plurality of hollow nozzle guide vanes, each of said struts
extending through one of said guide vanes.
15. A gas turbine engine comprising in flow sequence compressor
means, combustion means, and turbine means, a shaft supporting at
least one of said compressor means and said turbine means, a
bearing in which said shaft is mounted, a fixed cylindrical engine
casing, two axially spaced substantially radially extending annular
panel members, said bearing being supported from the fixed casing
by way of said panel members, at least one of said panel members
having a plurality of angularly spaced-apart dished portions each
of which is secured to the other of said panel members to brace
together and interconnect the same, said dished portions being
elliptical in shape, said at least one panel member having
corrugated portions between the dished portions thereof.
16. A gas turbine engine as claimed in claim 15 wherein the said
dished portions are integrally formed in said at least one panel
member.
17. A gas turbine engine as claimed in claim 15 wherein said
angularly spaced-apart dished portions are provided in both panels,
said portions being arranged in pairs, one from each panel, the
portions of each pair having their bases secured together.
18. A gas turbine engine as claimed in claim 15 including an
axially extending bearing support ring, said bearings being
supported by said ring and said panel members being connected to
said ring, a further bearing also being supported by the ring.
19. A gas turbine engine as claimed in claim 15 including a
plurality of angularly spaced-apart struts secured to said engine
casing, said panel members being secured to said struts, a
plurality of hollow nozzle guide vanes, each of said struts
extending through one of said guide vanes.
20. A gas turbine engine comprising in flow sequence compressor
means, combustion means and turbine means, the compressor means and
the turbine means comprising bladed rotors, a shaft supporting at
least one of said bladed rotors, a bearing in which said shaft is
mounted, a fixed substantially cylindrical engine casing, two
axially spaced-apart substantially radially extending annular panel
members, said bearing being supported from the fixed casing by way
of said panel members, at least one of said panel members having a
plurality of angularly spaced-apart dished portions, said dished
portions being secured to the other of said panel members to brace
together and interconnect the panel members, said dished portions
being of relatively rounded shape, and further dished portions
being interposed between the relatively rounded dished portions and
being of relatively elongated shape, each relatively elongated
dished portion having a major axis which extends radially of the
shaft.
21. A gas turbine engine as claimed in claim 20 comprising in each
dished portion a deeper dished portion which secures the said
dished portion to the other of said panel members.
22. A gas turbine engine as claimed in claim 20 comprising means
defining apertures in regions of the said at least one panel member
which are not dished, the edges of the apertures being deformed out
of the planes of the apertures, forming stiffened rims
therefor.
23. A gas turbine engine comprising in flow sequence compressor
means, combustion means and turbine means, the compressor means and
the turbine means comprising bladed rotors, a shaft supporting at
least one of said bladed rotors, a bearing in which said shaft is
mounted, a fixed substantially cylindrical engine casing, two
axially spaced-apart substantially radially extending annular panel
members, said bearing being supported from the fixed casing by way
of said panel members, both panel members having a plurality of
angularly spaced-apart dished portions, said dished portions being
arranged in pairs, one from each panel member, and a connecting
member for each said pair of dished portions extending between the
bases of said dished portions and securing them together, each said
connecting member being an open-ended tubular member having an
internal dividing wall, each open end being respectively secured in
an aperture in the respective base, forming a deeper dished portion
therein.
Description
This invention concerns a bearing assembly of a gas turbine
engine.
In aircraft gas turbine engines there is a continuous conflict
between the weight and the necessary structural strength of parts
of the engine. This conflict is particularly marked in the large
structures that are employed to support the central shaft or shafts
of the engine, that is to say the shafts each of which carry at
least one bladed rotor of the engine.
Therefore, it is an object of the present invention to provide a
bearing support structure having a high degree of stiffness in both
the axial and radial directions, and also a high degree of
stiffness against rocking motion of a shaft supported therein,
while the weight of the structure is kept to an acceptable
value.
Accordingly, the invention provides a gas turbine engine comprising
in flow sequence compressor means, combustion means and turbine
means, the compressor means and the turbine means comprising bladed
rotors, a shaft supporting at least one of said bladed rotors, a
bearing in which said shaft is mounted, a fixed substantially
cylindrical engine casing, two axially spaced-apart substantially
radially extending annular panel members, said bearing being
supported from the fixed casing by way of said panel members, at
least one of said panel members having a plurality of angularly
spaced-apart dished portions, said portions being secured to the
other of said panel members to brace together and interconnect the
panel members.
The dished portions may be substantially lozenge shaped. By
"lozenge shaped" we mean generally rounded in outline, but not
necessarily symmetrical, and this term is intended to include
shapes ranging from circular, through oval to markedly elongated or
boat shaped.
Thus, the dished portions each may have major and minor axes, the
major axis extending radially on the shaft.
Thus, the dished portions may be elliptical.
At least one panel member may have corrugated portions between the
dished portions.
The corrugated portions may be constituted by elongated dished
portions, the major axis of each elongated dished portion extending
radially of the shaft.
Said dished portions may be of relatively rounded shape, further
dished portions being interposed between the relatively rounded
dished portions, and being of relatively elongated shape, each
relatively elongated dished portion having a major axis which
extends radially of the shaft.
There may be provided in each dished portion a deeper dished
portion which secures the said dished portion to the other of said
panel members.
There may be means defining apertures in regions of the at least
one panel member which are not dished, the edges of the apertures
being deformed out of the planes of the apertures, forming
stiffened rims therefor.
The dished portions may be secured to the other offset panel
members by welding.
The said dished portions may be integrally formed in said at least
one panel member.
Said angularly spaced apart dished portions may be provided in both
panels, said portions being arranged in pairs, one from each panel,
the portions of each panel having their bases secured together.
There may be for each said pair of dished portions a connecting
member extending between said bases securing them together, said
connecting member being an open-ended tubular member having an
internal dividing wall, each open end being respectively secured in
an aperture in the respective base, forming a deeper dished portion
therein.
There may be an axially extending bearing support ring, said
bearing being supported by said ring and said panel members being
connected to said ring, a further bearing also being supported by
the ring.
There may be a plurality of angularly spaced-apart struts secured
to said engine casing, said panel members being secured to said
struts, a plurality of hollow nozzle guide vanes, each of said
struts extending through one of said guide vanes.
FIG. 1 is a diagrammatic view of a gas turbine engine provided with
a bearing assembly according to the present invention,
FIG. 2 is a broken away sectional view of a larger scale of part of
the structure of the engine of FIG. 1,
FIG. 3 is a broken-away sectional view of a modification,
FIG. 4 is an axially facing view of another modification,
FIG. 5 is a section on line 5--5 of FIG. 4,
FIG. 6 is a section on line 6--6 of FIG. 4,
FIG. 7 is an axially facing view of another modification, and
FIG. 8 is a section on line 8--8 of FIG. 7.
In FIG. 1 there is shown a gas turbine jet propulsion engine 10
having an engine casing 11 within which are mounted in flow series
a low-pressure compressor 12, a high-pressure compressor 13,
combustion equipment 14, a high-pressure turbine 15, a plurality of
angularly spaced-apart hollow nozzle guide vanes 16, a low-pressure
turbine 17 and an exhaust duct 18.
The high-pressure turbine 15 drives the high-pressure compressor 13
by way of a shaft 21 (FIG. 2), while the low-pressure turbine 17
drives the low-pressure compressor 12 by way of shaft 22, a portion
of the shaft 21 being mounted concentrically within a portion of
the shaft 22.
The portion of the shafts 21, 22 are mounted respectively within
roller bearings 24, 25 respectively. The bearings 24, 25 are
mounted within and supported by a common axially extending bearing
support ring 26.
The bearing support ring 26 is supported from the fixed cylindrical
structure constituted by the engine casing 11, by way of two
axially spaced substantially radially extending annular panel
members 30, 31 which are welded to the bearing support ring 26 at
32, 33 respectively. The panel members 30, 31 are welded at 34, 35
to a plurality of angularly spaced-apart common struts 36 each of
which passes through a respective hollow nozzle guide vane 16 and
is bolted to the engine casing 11. Alternatively, fastenings such
as nuts and bolts may be used to fasten the struts 36 to the panel
members 30, 31.
The panel members 30, 31 are respectively provided with a number of
angularly spaced-apart holes 40, 41 into which are welded circular
or elliptical dished portions or members 42, 43 respectively. The
base 44 of each dished member 42 is welded to a base 45 of a
corresponding dished member 43. The dished members 42, 43 thus
interconnect the panel members 30, 31 and also brace the panel
members 30, 31 together.
Alternatively, only one of the panel members 30, 31 need be
provided with angularly spaced-apart holes 40, 41, the dished
members 42 then having their edges welded to the holes 40 and
having their bases welded to the opposite panel member 31.
In another alternative, each panel member 30, 31 may have angularly
spaced-apart holes 40, 41, the holes in one panel member being
staggered relative to the holes in the other panel member so that
the dished members 42, 43 have their bases welded to one panel
member while their edge portions are welded to the other panel
member. Thus with this arrangement the dished members 42, 43 are
arranged so that they face alternately in the opposite directions
with their bases and edge portions respectively fastened to
alternate panel members 30, 31.
In FIG. 3 there is shown a modification in which a bearing support
ring 26a is employed, which houses roller bearings 24a, 25a and
whose upstream end is supported from a strut 36a by way of two
axially spaced substantially radially extending annular panel
members 30a, 31a which are welded to the bearing support ring 26a
at 32a,33arespectively and to the strut 36a at 34 Ia, 35a
respectively. The strut 36a extends through hollow nozzle guide
vanes as in the FIG. 2 construction.
The panel members 30a, 31a are respectively provided with a
plurality of angularly spaced-apart lozenge-shaped (preferably
substantially elliptically shaped) dished portions 42a, 43a whose
bases 44a, 45a are respectively welded to each other, whereby to
interconnect and brace the panel members 30a, 31a together. Each of
the panel members 30a, 31a is provided, between its adjacent dished
portions, with corrugated portions 46 to take radial loads from the
bearings 24a, 25a. The dished portions 42a, 43a create an axially
stiff structure to take axial gas loads.
A further possibility is for one only of the panel members 30a, 31a
to have a plurality of angularly spaced-apart dished portions whose
bases are welded to the other panel member.
The structure shown in FIGS. 2 and 3 is stiff both axially,
radially and about a diametrical axis, and is relatively simple and
inexpensive to manufacture. Moreover, it enables the bearings to be
supported by structure extending through the nozzle guide vanes and
thus without increasing the length of the engine. By reason of its
said stiffness, the structure is such as to make it easy to provide
passages (not shown) for cooling air and thereby to afford
protection for oil pipes (not shown) in what is normally a very hot
region.
The structures hereinafter described with reference to FIGS. 4 to 7
have similar advantages.
In FIG. 4, the panel members 30b, 31b (only one shown) have a
number of angularly spaced-apart lozenge-shaped dished portions 42b
of relatively rounded shape, further shallow dished portions 48
being interposed between the relatively rounded dished portions
42b. The dished portions 48 are of markedly elongated form, and
have their major axes 49 extending radially of the shaft 22 of the
engine. As can be seen from FIG. 5, the relatively rounded dished
portions 42b, 43b are welded together, but the shallow elongated
dished portions 48, which are provided in both the panel members
30, 31, are not joined together and constitute corrugated portions
between the relatively rounded dished portions 42b, 43b.
FIG. 4 also illustrates how pipes such as 50 may conveniently be
routed through the panel members 30b, 31b.
Holes 54, 56 are provided in regions of the panel members which are
not dished. As can be seen from FIG. 6, the edges of the holes 54,
56 are deformed out of the planes of the holes to form stiffened
rims 58 therefor. By providing holes with stiffened rims, the
weight of the structure is reduced, but the stiffness is not
undesirably reduced.
In the embodiment of FIG. 7, panel members 30c, 31c have dished
portions of different shapes. The panel member 30c (shown in full
lines) has lozenge-shaped dished portions which are generally pear
shaped as shown at 42c, 42d, it will be noted that the dished
portions at 42d have small reentrant curves on their flanks to
clear holes 60 in undished portions of the panel member 30c. The
edges of the holes 60 are deformed in the same way as described
with reference to FIG. 6, and may be arranged to permit the passage
of, and support by means of webs 61, pipes or cooling air
ducts.
Although the lozenge-shaped dished portions 42c, 42d are shown as
having their larger ends radially inward, they may be reversed, so
that the larger end is radially outward.
An undished region of the panel member 30c is provided with holes
62 having deformed edges as in FIG. 6.
The other panel member 31c is disposed behind the panel member 30c,
when viewed as in FIG. 7, and has dished portions 42e of a
generally rounded lozenge shape which are shown dotted in FIG, 7.
The shape of these dished portions 42e is very similar to the
dished portions 42b of FIG 4. Holes 64 (shown dotted) having rims
as shown in FIG. 6, are provided in the undished regions of the
panel member 31d.
Referring to FIG. 8, it will be seen that the pairs of dished
portions 42c, 42d, 42e have their bases secured together by a
connecting member 67 of open-ended tubular form, the connecting
member 67 having an internal dividing wall 68. Each open end of the
connecting member is respectively secured e.g. by welding or
brazing in an aperture in the base of a respective dished portion
42c, 42d or 42e, thus forming a deeper dished portion 69 therein.
Each tubular connecting member 67 may if desired be made in two
cup-shaped parts joined at their bases to form the internal wall
68. Of course, if desired, the deeper dished portion 69 can be
provided in the other types of dished portions 42 described
previously Also, a single cup-shaped member may be employed to
provide a dished portion 42 with a deeper dished portion 68 and to
join it directly to the other panel member, instead of to the base
of another cup-shaped member.
* * * * *