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Патент USA US3034773

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May 15, 1962
R. L. ROWLEY
3,034,763
ROTOR CONSTRUCTION
Filed Aug. 20, 1959
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ROBERT L. POM/LEV
By
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ATTORNEY
United States Patent 0 ” ice
1
3,034,763
ROTOR CONSTRUCTION
Robert L. Rowley, South Glastonbury, Conn., assignor to
United Aircraft Corporation, East Hartford, Conn., a
corporation of Delaware
Filed Aug. 20, 1959, Ser. No. 835,132
2 Claims. ((11. 253-47)
,
3,034,763
Patented May 15, 1962
2
The rib or ?ange 30 is higher than the ?ange 28 be
cause of the greater spacing of the platform 26 from the
disc axis at the ?ange 30‘. The ?anges 28 and 30 are
preferably located in alignment with the opposite end sur
faces 18 and 22 of the disc. Between the ?anges 28 and
30 the peripheral surface 32 of the disc is preferably
parallel to the axis of the disc. This peripheral surface
32 is located as close to the axis as possible and still
This invention relates to a rotor construction for an
axial ?ow compressor or turbine.
One feature of the invention is a mounting for a blade
on a supporting disc by which to minimize any circula
tion ?ow below the blade platform. Another feature is a
blade mounting in which the disc construction serves
provide adequate strength to the disc to support the blade
dovetails. By minimizing the distance from the bottom
surface 34 of each slot 10 to the peripheral surface 32
the rigidity ditferences between the disc section at each
dovetail slot and the disc section between the dovetail
slots are minimized thereby minimizing the stress con
as a retainer for axial blade movement in one direction. 15 centration factor at dovetails during disc vibration. The
Another feature is ‘a Ininimum weight, maximum load
periphery of the ?anges 28 and 30 are arcuate about the
disc and blade assembly where the blade platform makes
axis of the disc and each ?ange de?nes a circle concen
an acute angle with the disc axis.
tric to the axis of the disc.
One particular feature is an arrangement by which
As will be apparent from FIGS. 3 and 4 the slots 10
to minimize the rigidity difference of the disc at the dove 20 and blade roots 12 may not be exactly at right angles
tail and between the dovetail slots that support the blades.
to the plane of the disc but may be positioned at a slight
Other features and advantages will be apparent from
angle thereto. Similarly the opposite side edges 36 of
the ‘following description taken in conjunction with the
the blade platform 26 may extend parallel to the root.
accompanying drawing in which:
It will be understood that the contiguous edges of ad
FIG. 1 is a longitudinal sectional view through a com 25 jacent platforms are substantially in contact with one
pressor disc.
another.
FIG. 2 is a perspective view of a portion of the pe
It is to be understood that the invention is not lim
riphery of the disc with the blade attached thereto.
ited to the speci?c embodiment herein illustrated and de
‘FIG. 3 is a sectional view substantially along the line
of 3-3 of FIG. 1.
FIG. 4 is a sectional view substantially along the line
of 4—4 of FIG. 3.
scribed, but may be used in other ways without departure
30 from its spirit as de?ned by the following claims.
I claim:
1. An axial ?ow turbine or compressor rotor including
The drawing shows in FIG. 1 only a sectional view of
a disc having a row of blades projecting outward from
the disc from the axis of the disc to the periphery. The
its periphery, each blade having an operative blade por
disc 2 is generally ?at being thickened as to 4 adjacent 35 tion, a root portion, and a platform integral therewith
to the center for stress purposes. The disc may also
located between the blade portion and the root portion,
carry projecting ribs 6 on opposite sides for positioning
the underside of the platform extending at an acute an
the disc in a complete rotor assembly. A rotor assem
gle to the axis of the disc in an axial direction such
bly to which this disc is applicable is described in the
that one end of the platform is located at a greater radial
Ledwith Patent 2,639,885.
40 distance from the axis than the other end of the platform,
The periphery 8 of the disc is thickened in an axial
the disc having a series of axially extending peripheral
direction and has a plurality of peripheral axially ex~
slots substantially the same shape as the root portions
tending slots 10 to receive the blade roots 12 on the
to receive said root portions therein, and axially spaced
blades 14. These slots and blade roots may be of any
peripheral ?anges on the disc between adjacent slots for
conventional arrangement; the particular shape is the
engagement with the underside of the platforms, the
usual dovetail root. The root 112 may have at one end
a projecting flange ‘16 to overlie the end surface 18 of
periphery of said ?anges being substantially arcuate about
the axis of the disc, one of the peripheral ?anges having
the disc thereby to prevent axial movement of the blade
a greater radial dimension than the other thereby to lim
in one direction (to the right in FIG. 1). A blade lock
it the axial movement of the blade root in one direction
ing strip 28 overlies the opposite end surface 22 of the
with respect to the disc.
disc and has its opposite end received in a radially ex 50
2. An axial ?ow turbine or compressor rotor including
tending opening 24 in the blade root to limit axial move
a disc having a row of blades projecting outward from
ment in the other direction (to the left, FIG. 1).
its periphery, each blade having an operative blade por
Between the operative air-foil portion of the blade and
tion, a root portion, and a platform integral therewith
the blade root 12 is the blade platform 26 which de?nes
located between the blade portion and the root portion,
the interior wall of the gas path past the blade. This 55 the underside of the platform extending at an acute angle
platform in the arrangement shown extends at an acute
to the axis of the disc in an axial direction such that one
angle to the axis of the disc as viewed in a longitudinal
end of the platform is located at a greater radial dis
axial plane as in FIG. '1. The several platforms 26 for
tance from the axis than the other end of the platform,
the row of blades 14 on the disc 2 thus de?ne substan
the disc having a series of axially extending peripheral
tially a cone concentric to the rotor axis. Thus the 60 slots substantially the same shape as the root portions
spacing of each platform 26 from the axis in a radial
direction increases from one end of the platform to the
other. To prevent the leakage of air past the disc be
tween the periphery of the latter and the platform 26 the
to receive said root portions therein, and axially spaced
peripheral ?anges on the disc between adjacent slots for
engagement with the underside of the platforms, the
periphery of said ?anges being substantially arcuate about
disc has axially spaced ?anges 28 and 30 projecting ra 65 the axis of the disc, one of the peripheral ?anges having
dially from the disc and in engagement with the under
a greater radial dimension than the other thereby to limit
side of the platform as best shown in FIG. 1.
the axial movement of the blade root in one direction
3,034,733
4
with respect to the disc, the periphery of the disc between
the ?anges being cylindrical.
References Cited in the ?le of this patent
UNITED STATES PATENTS
2,656,147
2,683,583
Brownhill ct a1 _________ __ Oct. 20, 1953
Huebner et al. ________ __ July 13, 1954
2,75 1,189
2,807,434
2,910,268
Ledwith ______________ .. June 19, 1956
Zimmerman __________ __ Sept. 24, 1957
Davies et a1. __________ __ Oct. 27, 1959
669,979
1,659,752
Great Britain ________ __ Mar. 12, 1952
France ______________ __ Nov. 18, 1953
FOREIGN PATENTS
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