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Патент USA US3081028

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March 12, 1963
w. s. CASTLE ETAL
3,081,021
FABRICATED WHEEL AND BLADE ATTACHMENTS
Filed 0012. 14, 1959
5 Sheets-Sheet 1
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ATTORNEY
March 12, 1963
w. s. CASTLE ETAL
3,081,021
FABRICATED WHEEL AND BLADE ATTACHMENTS
Filed Oct. 14, 1959
5 Sheets-Sheet 2
ATTORNEY’
March 12, 1963
W. S. CASTLE ETAL
3,081,021
FABRICATED WHEEL AND BLADE ATTACHMENTS
Filed Oct. 14, 1959
3 Sheets-Sheet 3
Mr
United States PatentO?Fice
3,081,021
Patented Mar. 12, 1963
1
2
The tang portions are further axially spaced with re
3,081,021
spect to each other for cooperation with two axially
FABRICATED WHEEL AND BLADE
spaced parallel annular sheet metal plates 38 and 40 se
ATTACHMENTS
cured together at 42 by suitable means to comprise the
William S. Castle, Speedway, and John B. Minnicli, In
dianapolis, Ind., assignors to General Motors Corpora 5 rot-or wheel 16, each of the tang portions being circum
tion, Detroit, Micl1., a corporation of Delaware
ferentially cut at its inner end to provide a radial slot 42,
Filed Oct. 14, 1959, Ser. No. 846,505
44 for receiving the discs 38 and 40 therein. The tang
2 Claims. (Cl. 230-134)
portions are adapted to be secured to the discs by the in
sertion of rivets 46, 48 in the holes 50, 52 and 54, 56,
This invention relates to a rotor assembly.
10 respectively. It will be seen therefore that the overall
More particularly, it is an object of-this invention to
con?guration of each blade root matches the curvature
provide a low cost‘ fabricated rotor assembly that is easy
of the blade from which the root depends therefore pro
to assemble and disassemble.’ '
viding for a minimum of metal while giving optimum
1 Other objects, features ad advantages will become ap
stress distribution and support to the blade.
. v
parent upon reference to the succeeding detailed descrip 15
Each of the blades or airfoil assemblies is adapted to
tion and to the drawings illustrating the preferred em
be circumferentially spaced from each other by spacer
bodiments of the invention, wherein:
means 18 comprising two axially spaced radial sheet
FIGURE 1 is a front elevational view‘ with parts
metal plates 60 and 62 axially ?anged at 6'4 and 66 for
broken away and in section of one embodiment of the
cooperation with a top sheet metal plate 68 constituting
invention,
FIGURE 2 is an enlarged plan view with parts broken '
away and in section taken on a plane indicated by
and viewed in the direction of the arrows 2—2 of FIG
URE 1,
20 a platform inclined at the same angle as the blade
platform 36 for cooperation therewith. The plates 60
and 62, as well as platform 68, extend circumferentially
for the entire desired spacing between blades so as to not
only constitute a continuous streamlined surface to
FIGURE 3 is a cross-sectional view taken on a plane 25 reduce friction, etc., losses, but also an air or gas seal
indicated by and viewed in__the direction of arrows 3--3
to reduce to a minimum the passage of air or gas be
of FIGURE 1,
tween the blades in any direction or path other than over
FIGURE 4 is a cross-sectional view taken on a plane
the platforms 36 and 68. The leg plates 60 and 62 are
indicated by and viewed in the direction of the arrows
radially spaced for the same purpose as are tang portions
4-4 of FIGURE 1,
30 28, 30, and are axially spaced so as to ?t Within the
FIGURE 5 is an enlarged exploded perspective view
of a detail,
FIGURE 6 is a front elevational view of another em
bodiment of the invention,
opening defined by the axial distance between rotor discs
38 and 40 to which they are adapted to be rive-ted as
shown.
'
.
'
'
The assembly of this embodiment of the invention is
FIGURE 7 is a cross-sectional view taken on a plane 35 believed to be clear from the drawings; however, a brief
indicated by and viewed in the direction of arrows 7—7
resume will be given. The tang portions 28 and 30 of
of FIGURE 6, and
FIGURE 8 is a cross-sectional view taken on a plane
the airfoils are dropped into place over the rotor discs
38 and 40 so as to straddle the same with the holes 50,
indicated and viewed in the direction of arrows 8-8 of
52 and 54,- 56 therein being aligned, and the rivets 44,
FIGURE 6.
40 46 are inserted therein. The spacer means 58 which has
Referring to the drawings and more particularly to
FIGURE 1, there is shown therein an arcuate portion
of an axial flow type rotor assembly 12 incorporating
one embodiment of this invention, the assembly includ
been preassembled by riveting the leg plates 60 and 62 to
the platform 68‘ at 69 and 70, is then dropped in place
between the discs 38 and 40 with the holes 71 and 72
therein aligned with the holes 74 and 76 in the discs, and
ing a number of blades 14 adapted to be secured to a 45 the edge of the platform 68 abutting the adjacent edge
rotor 16 and spaced equally circumferentially therearound
of the platform 36, and the rivets 78 are then inserted
by a number of spacers 18.
Referring more particularly to the details, each of the
blades 14 is preferably machined from bar stock in the
therein. The next circumferentially adjacent blade and
root is then riveted to the rotor wheel, with the connec
tion of the spacer means following, etc., until the entire
shape of an airfoil as shown so as to provide an enlarged 50
rotor is assembled.
inclined root or base portion 20 integral therewith at the
radially inner end 22 thereof.
As seen more clearly in FIGURES 2 and 5, each of
the root portions 20 is undercut or recessed at opposite
Thus, a low weight, high strength,
economically fabricated rotor assembly is provided. The
assembly may be disassembled by a shearing oif of the
rivet heads and a reversal of the assembly procedure.
FIGURES 6 to 8 illustrate another embodiment of the
sides 24 and 26 by suitable milling operations to provide 55
invention, this embodiment differing from the FIGURES
l to 5 embodiment primarily in the construction of the
tions 28 and 30 depending from the blade. The milling
blade root to accommodate connection thereof to two
operations and spacing also provide on opposite sides of
non-parallel axially spaced sheet metal annular plates or
the root of shelf portion 32 (FIGURE 1), 34 at one
edge formed integral with the upper edge of the tang 60 discs 80 and 82 comprising the rotor wheel.
In this embodiment, the converging discs 80 and 82 are
portion 28 or 39 to together constitute a blade platform
each provided at their peripheries with radially extend-.
36 inclined with respect to the axis so as to direct the
ing axially spaced portions 84 and 86 parallel to each
how of air thereover in the most ‘advantageous and
other and adapted to be received within two axially
ve?icient direction.
_
a
The radial spacing of the tang portions provides a line 65 spaced radial slots 88 and 90 circumferentially cut in
the depending tank 92 of the root or base 94 of a blade
radially, axially and circumferentially spaced tang por
of connection and support of the blades to the rotor at
the same inclination as the blade platform and the air
?owing thereover thus providing a more durable con
96.
The blade or airfoil 96 is constructed in a manner
similar to that of FIGURES 1 to 5 embodiment, i.e., ma
chined from bar stock in the shape of an airfoil while
nection. The tang portions are also circumferentially
providing an enlarged root portion. The root portion is
spaced from each other so as to be positioned directly 70 milled or recessed both at the upstream and the down
below the adjacent curved portion of the airfoil, which is
supported thereby, to give the best distribution of stress.
stream sides of the assembly to provide circumferentially
spaced struts 98 and 100, respectively, for distributing the
spar-p21
4
3
stress from the blades to the connection to the discs. The I
trimming away of the metal between strutsreducing'the
weight of the root to a low value.
The milling thus
provides a root having a centrally depending slotted
radial tank portion 92 with substantially axially extend
ing shelf portions 102 and 104 together constituting a
blade platform 1% inclined as shown in the same direc
tion and for the same purpose as the FIGURES 1 to 5
embodiment.
We claim:
‘1. A lightweight rotor blade assembly comprising a
rotor, a plurality of thin arcuately curved airfoil type
blades adapted to be secured to said rotor at the periph
ery thereof, spacer means for circumferentially spacing
said blades and spanning the gap therebetween, and means
for securing said blades and spacer means and said rotor
rigidly together, said rotor comprising a number of
annular axially spaced plates, each of said blades having
The spacer means 108 is substantially the same as that 10 an enlarged root integral with and beneath said blade and
of FIGURE 4, comprising two sheet metal radial plates
110 and 112 axially spaced by a spacer 113, ?anged at
114 and 116 and riveted to an inclined platform 113 at
129 and 122, the axial spacing of the plates being such
as to permit straddling of the two discs 80 and 82 by the
plates, and riveting them together.
The assembly of this embodiment is substantially the
same as the FIGURES 1-5 embodiments, i.e., the blade
and tang 92 are dropped into place over the discs 80' and
82 and riveted thereto by the insertion of the rivets
124 into the holes provided in the tank and discs. The
preassembled spacer means 108 is then placed over the
having an overall con?guration substantially matching
the curvature of said blade, each of said roots having
axially and circumferentially spaced tang portions depend
ing radially beneath and being substantially aligned with
the leading and trailing edges of said blade, each of said
tang portions being slotted to receive a rotor plate therein,
said root having other portions extending between and
connecting said tang portions to support all portions of
said blade.
'
2. A rotor blade assembly as in claim 1, wherein said
other portions extend from each of said tang portions
each in a different direction, said other portions being
recessed, said recesses being axially and circumferentially
two discs as shown in FIGURE 8, and riveted thereto by
spaced from each other and each forming a shelf por
rivets 126 being inserted in the holes provided in the
with each other and said tang portions, said
discs, a spacer member 113 being positioned therebe 25 tion-integral
tang portions and shelf portions together constituting a
tween. The next circumferentially adjacent blade as
platform for said blade, said tang portions depending
sembly is then inserted in place and riveted, followed by
beneath diametrically opposite edge portions of said
a spacer means, and so on around the circumference of
the rotor wheel until the entire rotor is assembled. The
assembly may be also easily disassembled by shearing 30
off the rivets, and reversing the assembly operation.
Thus, a rotor assembly of very light weight and great
strength is provided for easy and economical fabrica
tion.
While the preferred embodiments of the invention have
been illustrated in FIGURES 1 to 8, it will be clear that
many modi?cations can be made thereto by those skilled
in the art to which this invention pertains without de
parting from the scope of the invention.
platform.
‘
'
References Cited in the ?le of this patent
FOREIGN PATENTS
528,031
France _______________ __ Oct. 6, 1921
652,099
718,139
Great
Great
Great
Great
724,281
742,194
Britain _________ __ Apr. 18, 1951
Britain _________ __ Nov. 10, 195!
Britain _________ __ Feb. 16, 1955
Britain ________ __ Dec. 21, 1955
$p-
UNITED STATES PATENT OFFICE
CERTIFICATE OF CORRECTION
Patent No“ 3,081,021
March 12, 1963
William 5. Castle et al.
- It is hereby certified that error appears in the above numbered pat
ent requiring correction and that the said Letters Patent should read as
corrected
below.
Column lI
for
—-~
"of"
tang
read
'
'
line 14,
~—
—>—=
a
—~;
for "ad" read —— and ——
; line 59,
column 3, line 21, ‘ for "tank" read
Signed and sealed this 8th day of October 1963.,
(SEAL)
Attest:
ERNEST w. SWIDER
Attesting Officer
.
'
EDWI
Ac t i ng
>
N'L
I
REYNOLDS
Commissioner of Patents
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