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Патент USA US2137386

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Nov. 22, 1938.
_
K_ CAMPBELL ET AL
2,137,386
CONTROLLABLE ENGINE COWLING
Original Filed Oct. 19, 1955
2 Sheets-Sheet‘ 1
INVENTORS
Kenneth Campbell %,P/IMpBA Téylor:
Nov. 22, 1938,
K. CAMPBELL ET AL
2,137,386
CONTROLLABLE ENGINE COWLING
Original Filed Oct. 19, 1935
2 Sheets-Sheet 2
INVENTORS
Kennel/7 Campbell “#P/YIWPB. Tbylor
Patented Nov. 22, 1938
2,137,386
PATENT OFFICE
_‘ UNITED STATES
2,137,386
CONTROLLABLE ENGINE COWLING
Kenneth Campbell, Radburn, and Philip E. Tay
lor, Upper Montclair, N. J., assignors to Wright
Aeronautical Corporation, a corporation of New
York
Application October 19, 1935,:Serial No. 45,264
Renewed February 19, 1932
"
/
8 Claims.
(Cl. 223-171)
This invention relates to cooling and cowling
means for engines, and in certain respects com
prises improvements on the co-pending applica
tion of Chilton, Serial No. 720,283, ?led April 12,
1934. In that application there is disclosed a disc
placed within the cowl entrance to de?ne a radial
air entrance to conform to the divergent ?ow
existing behind the propeller and to prevent the
recirculation and loss of air found to exist with
10 .conventional open entrance cowls.
Recent improvements in ?nning and in pres
sure-baffles of air-cooled radial aircraft engines.
have greatly reduced the pressure differential
across the bailies needed for adequate cooling.
Previously, when’ this differential got down to a
pressure of 5” H2O, or less, as may happen in slow
\ ‘speed climb, di?culty was encountered with cool;
I ing, but with the cylinder and baffle improvements
now available these low pressure differentials are
20 adequate for cooling, thus permitting full throttle
climb operation at low airplane speed. In high
speed level ?ight, however, the baf?e differentials
will increase to 3 ‘or 4 times the ?gure obtained
buckles for adjustment having universal pivotal
connections 28, 22, with the rim of the disc and
the cylinder heads, respectively. These links 26
are oblique relative to the edge of the disc and
thus guide the disc for coincidental axial and
rotative movement, and the links may generally
be de?ned as lying in a plane which bisects the
angle between the engine axis and a normal
thereto, said plane, in turn, being perpendicular
to that plane which includes the engine axis and 10
the normal.‘ In other words, each link lies in a
plane which makes substantially a 45° angle with
the engine axis.
-
The rim vof the disc 22 is of similar diameter '
to the entrance 32 defined by the usual inturned 25
portion 32 at the front of the engine cowling ring.
The disc 22 is rotated bodily through a link 35
by means of a suitable bellcrank lever ,36 pivoted
to a suitable bracket 38 secured to one of the
cylinder heads 21?, the lever 36 being also pro
a
vided with a suitable control rod 22 running to a
pilot’s control (not shown). On account of the
angular disposition of the links 26, rotation of the
in climb. Such high bai?e pressures are no longer cowling by the control 22, results in the disc being
25 necessary for cooling, and they result in an un
moved fore and aft to positions wherein the disc
necessarily great air ?ow over the cylinders which . edge may be variably spaced from the cowl edge
absorbs an unnecessarily great proportion of the 32 to permit of variation in the amount of air
‘engine power.
entering within the cowling 32 for engine cooling
Accordingly, a prime object of this invention is purposes. The disc 22 is illustrated by full lines,
30 to provide a simple and improved means for ad-.
justing the air ?ow, so that the excess quantity
passing in high speed ?ight, with conventional
cowls, may be reduced so as merely to meet the
cooling requirements; whereby the drag of the
35 entire engine-cowling combination is also re
duced. Associated objects are to provide im
proved and simpli?ed means for effecting the de
sired cowl opening control.
In the drawings:
40
‘
Fig. l is a fragmentary axial section of the
cowling of the invention, with the engine and
propeller indicated in dotted lines;
Fig. 2 is a fragmentaryend view; and
Fig. 3 is a fragmentary plan view illustrating
45 the control mechanism.
In these drawings, l0 designates a conventional
propeller hub having conventional blades I2. A
conventional engine nose l4 and cylinders it are
indicated in dotted lines. To the engine nose M
there is secured a ?xed circular mounting drum
l8, provided with (preferably non-metallic) wear
ing strips 20 on which a cylindrical hub 22 of a
large, slightly coned disc. 24 is free for limited
rotation and sliding. The rim of the disc is
guided by a plurality of links 26 comprising turn
in a forward position giving minimum opening, 30
while the dotted‘ lines 22 of Fig. 1 illustrate the
open position to be used in slow' speed ?ight. In -~
operation the pilot will take 011' and climb with
the cowl in its most open position and will adjust
it towards the closed position for level ?ight, 35
giving reduced air flow with correspondingly re
duced power absorption for cooling. The usual
cylinder head temperature indication may be
used as a guide in adjusting the cowl. The disc
is formed to take advantage of the radial air ?ow 40
behind the propeller as taught in said copending
application.
While we have described our invention in de- ,
tail in its present preferred embodiment, it will 45
be obvious to those skilled in the art, after un
derstanding our invention, that various changes
and modi?cations may be made therein without
departing from the spirit or scope thereof. We
aim in the appended claims to cover all such 50
modi?cations and changes.
’
What is claimed is:
1. The combination with an engine cowl hav- .
ing a front entrance opening, of a disc disposed
therein, swinging links guiding the rim of said
2
2,137,386
disc for approximately helical movement, and coaxial with said engine, the other ends of said
- links being pivoted to the disc edge, means for
control means for e?ecting said movement.
swinging said disc, on said links, with respect to
2. The combination with an engine, of an em
the engine cylinders, and guide means for the
bracing cowl having an air‘ entrance, a disc de
fining an annular passage within said entrance, central portion of said disc.
7. The combination with a radial cylinder en
and links pivotably connecting said disc to said
engine for variation in the area of said entrance. gine, of angularly disposed links pivoted to the
3. The combination with an engine cowl, of an ends of certain cylinders, a disc ahead of and
adjustable air entrance disc therein, and sup
porting and controlling means therefor compris
ing swinging links pivotably connected to said
coaxial with'said engine, the other ends of said
links being pivoted to the disc edge, means for
swinging said disc,‘ on said links, with respect to
disc and engine.
4. The combination with an engine having a
portion of said disc, and a ring cowl encircling
nose, of cylindrical supporting drum thereon, a
ll disc having a hub engaging said drum for rota
tional and sliding movement thereon, a cowl em
bracing said disc for de?ning an adjustable an
nular air entrance opening between said cowl
and disc, manual means for rotating said disc,
20 and means responsive to disc rotation for axially
moving said disc.
5. The combination with a radial cylinder en
gine, of angularly disposed links pivoted to the
ends of certain cylinders, a disc ahead of and
25 coaxial with said engine, the other ends of said
links being pivoted to the disc edge, and means
for swinging said disc, on said links, with respect
to the engine cylinders.
6. The combination with a radial cylinder en
gine, oi angularly disposed links pivoted to the
ends of certain cylinders, a disc ahead of and
the engine cylinders, guide means for the central
said disc with the leading edge of which said disc
is adapted to form a variable area air entrance
opening.
8. In aircraft engine cowling an annular mem
her, a disc member movable relative thereto to
adjust the area for air?ow between the members,
a plurality of circumferentially spaced links each
attached. at one end to the aircraft and at its
other end to one of said members, said links re
spectively lying in planes each of which sub
stantially bisects the right angle between the en
gine axis and a normal to the engine axis, and
control means for moving said disc member, said
links imparting both axial and circumferential
movement to said disc members upon controlled
movement thereof.
PHILIP B. TAYLOR. '
KENNETH CAMPBELL.
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