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Патент USA US2411271

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Nov. 19, 1946.
Filed Aug. 26, 1945
Patented Nov. 19, 1946
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William I. Jackson, Orange, Calif.’
Application August 26, 1943, Serial No. 500,083
2 Claims.
(Cl. 170-168)
My invention relates to a propeller for aircraft
such as airplanes, helicopters, dirigibles and the
Formed integral with and projecting inwardly
from rim I2, midway between its front and rear
edges, is a web or flange I3 and the outer ends of
blades H are formed integral with this web and
with rim I2 by means of outer walls I14, which
connect the outer ends of said blades with said
rim and inner walls I5 which connect the blades,
like, and the principal object of my invention is,
to provide a propeller which in structure, com
bines fan blades and a ring or rim having air
passageways, in order to develop extremely high
pulling or lifting power when rotated at high
inwardly from walls I4, with the inner portion
A further object of my invention is to provide
of web I3.
These walls I4 and I5 are disposed transverse
a propeller of the character referred to, wherein 10
ly of the blades II and formed through web I3
the blades or vanes, in addition to being inclined
in cross section, are inclined lengthwise so their
between said walls, and beneath the outer end of
each blade is an air passageway such as IS.
inner ends, which are connected to a hub, are
positioned forwardly of the outer ends of said
Formed through Web between the openings Iii
blade and the rim or ring to which said outer ends 15 are similar openings to provide air passageways ‘
I7, and overlying each of said passageways is an
are connected.
integral plate or wall I8, which is inclined length
Further objects of my invention are, to con
struct the propeller in a single piece, by casting
wise to correspond with the transverse inclina
tion of the blades II.
methods or otherwise, and to embed in the
periphery of the rim or ring portion of the pro 20
Connecting the inside edges of the inclined
plates I8 with web I5 along the inner edges of
peller, a member such as a steel cable, in order
the openings I1 are integral walls I9, and the
to counteract and resist bursting strains when
thep-ropeller is rotated at high speeds.‘
outer edges of said inclined plates are integrally
With the foregoing and other objects in View,
connected to the inner face of rim I2 (see Fig. 5).
my invention consists of certain novel features of 25 During operation the propeller is, rotated at
high speed, and those portions of the blades in
construction and arrangement of parts, which
wardly from the rim will function in the usual
will be hereinafter more fully described and
manner and force a heavy column of air rear
claimed and illustrated in the accompanying
drawing, in which;
Fig. 1 is a front elevation of the propeller.
Fig. 2 is a plan view.
~ wardly through the rim or ring. At the same time
30 the outer ends of the blades which are inclined,
Fig. 3 is an enlarged cross section taken on the
line 3-3 of Fig. 1.
Fig. 4 is an enlarged section taken on the line '
and the inclined plates I8, will force air through
openings I5 and I‘! in the rim so as to produce a
tubular column of air surrounding the column
- driven rearwardly by the inner portions of the
4-4 of Fig. 1.
36 blades, thus producing a high degree of pulling or
lifting force upon the aircraft with which the pro
Fig. 5 is an enlarged cross section taken on the
peller is associated.
line 5--5 of Fig. 1.
To reinforce the rim portion of the propeller
Fig. 6 is a cross section of the peripheral rim
and provide resistance to bursting strains de
of the propeller and showing a reinforcement
40 veloped while said propeller is rotated at high
Referring by numerals to the accompanying
speeds, a member, preferably a steel cable such
drawing which illustrates a preferred embodi
ment of my invention, I0 designates a hub, with
which is formed integral, the inner ends of a plu
rality of radial blades II which are correspond
ingly inclined in cross section, also inclined
lengthwise so that their outer ends occupy a plane
rearwardly of their inner ends and the hub.
Thus the propeller is substantially dish shape, ‘
with its convex face or side forwardly presented.
The rim or ring which ‘connects the outer ends of
the blades includes a peripheral rim number I2,
which is substantially lozenge shape in cross sec
tion with smooth convex faces and fairly sharp
front and rear edges, thus providing a stream 55
lined effect.
as C, may be embedded in the rim member I2 (see .
Fig. 6).
Where larger sizes of my improved propeller
are built for use on large helicopters, said pro
pellers may take the shape of an umbrella or par
achute and reinforced by guy rods or wires ex
tending from the hub to the outer portion’ of the
Propellers constructed in accordance with my
invention, and in smaller sizes, may be advan
tageously employed for the propulsion of boats,
also in rotary pumps, compressors, impellers and
the like.
Thus it will be seen that I have provided a pro
peller which is simple in structure, inexpensive of
manufacture and very effective in performing the
functions for which it is intended.
It will be understood that minor changes in
the size, form and. construction of my improved
propeller may be made and substituted for those
herein shown and described without departing
from the spirit of my invention, the scope of
which isset'forth in the appended-claims‘.
I claim as my vinvention:
outer ends of said blades, which ring is lozenge
shape in cross section and being o?set rearward
ly from said hub, a continuous ?ange projecting
inwardly from said ring between its front and
rear ends, the inner edge of which ?ange is se
cured to said blades inwardly from their ends,
and there being spaced openings formed in said
> *2. An airplane propeller as set forth'in claim 1,
1. In an airplane propeller, a hub, a series of 10 with inclined plates integral with said ?ange in
front of the openings therein.
blades are inclined lengthwise and in cross see
blades projecting radially from said hub, which
tion, a peripheral ring integrally connected to the ' '
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