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Патент USA US2411936

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Dec. 3, 1946.
Q_ R_ „TON
y
_ 2,411,936
COOLING „ SYSTEM
Filed Aug. >5, 1945-
3 ‘sheets-smet 1
ßnventor
fc5/@we @afm
_ Dec. 3, 1946.
c`. R. PAToN
_ 2,411,936
COOLING SYSTEM
F'iled Aug. 5, 1945
_5 SheetsœSheet 2
(lttomegs
De’c. 3, 1946.
c. R. PAToN
2,411,936
COOLING SYSTEM
Filed Aug. ~5, 1945
3 *Sheets-Sheet 3
de’ IQ ,0a/1022 »
"542,411,936
PatentiedDec'. 3, v19246
L< 2.411,@
Í >‘oxyde mratò?, yisnim‘mghani.Mien., assignor if@ - f
neuwagen@ ,Si
General
`
`
y Application Augustñ
C
ms.
.'Ilhis invention- relates to *cooling `irre-a
>` '
y.-.forinfof
*fand-:shown--in section; .
A'more :particularlyfto auxiliary coolingf_meansëfor> '
.cooling parts ofV aircraft engines.`
In any internal combustionengme.the‘primary ~
>`object of> cooling is .to conduct the heat away from
»the .cylinder walls ïand head with sufficient ra
Figure-'Z Vis- a sectional viewtakenlonjine
f'
„rflî‘igure 8 is;_a side elevation »cia iurtherrnodiiied
A, ofi-.Figure 5.;
pidity to prevent their being raised abovea criti
.cal temperature. IWith this object most engines
are „provided with a primary cooling systemgto
form of my invention;
f
»~ "
l I Figure „9.is an enlargedsectional view
lines-149 of Figurel8; and _
¿.
`accomplish-this. - There are two. main systems: 10
are sectional
air-cooled,¢which utilizes cooling ñns to dissipate
' coolingchannels in the casings aroundthe com
bustion chamber. There are in eachcase, how
on
,
views vtaken
on rlines lill-l0, H--Il, and |2-.-l2, respectively,
the heat to rair forced thereover; or liquid-cooled,
. in which water or some other liquid iiowsthrough
-Y
:of Figure 9.-; A*
Referring now more particularly to the draw
15 Í ings,¿ there _isshown in dot?and-¿dashfoutline'an
_ engine 2.0i the liquid-cooledty'pe> which-is mount
ever, other parts of the engine and its associated
partsthat it maybe'necessary to cool and which
ed in av1 housing g4 also shown in dot-and-.dash
(outline, which housing may be the front portionof a plane’s fuselage. This housing is roughlyiof
are not satisfactorily cooled by the main or pri
mary cooling system,`especia1ly Where the engine
shape:V The forward portion is__ tapered '
is mounted within a relativelyclose housing and 20.'I .torpedo
and the nose of thegtorpedo section is‘provided by
,any auxiliary heat removal willaid in engine op- f
.-.the *propeller hub also shown` in dot-and-dash
eration. For example, the ¿ pipesy carrying the
~lines.;
@l
r
,.1
n
,r
' ~
exhaust gases to the atmosphere acquire a great
„The forward portion ofthe housing or cowling
dea1 of heat therefrom and no particularcooling
is,~supp0rted»f.1f0m the front ofthe engine. by
Lmeans is .usually provided therefor. Also,_ the 25.¿means-pf a ringlì and wtherefore it must b_e a
temperature in the vicinity of the spark plugs
-_: fairly strong and rigidassembly. The ring 6 _has
may be excessive andthe Aperformance ofthe
its ‘outer peripherytïsecuredto the inner surface
f plugs maybe improved by cooling this area.
»of
the»y cowling >by Yrivets 8 or similar securing
It is ytherefore an object of my invention to pro
means.A
Thetforward portion of theengine pro
30
vide auxiliary cooling means-for an engine. ,
, jects through thev center opening I0 in the ring
It is a further object o_i my inventionfto Vprovide
Y and is. secured thereto yby a plurality of boltsl2
auxiliary cooling means for the exhaust means,
which >extend from the engine housing through
It is a still further object of my invention to
openingshinf'the'ring and are secured thereto'by
, provide auxiliary cooling means for cooling the
Í nuts fui.v The bolts l2 are resiliently Amounted
spark plugs.
'
jwith` respectI to the ring by rubber washers i6 on
It is a still further object of my invention to
provide auxiliary cooling means to lower the op
erating temperature of various parts‘of an en
fgine.
- With these and other
objects
`
in view,»which~will
f
each side of the ring. ‘This will reduce the vibra
_Ã transmitted tothe fuselage from the engine.
.tion
The ring 6‘ acts as a bulkhead in the housing.
40
become apparent as the speciñcatlon proceeds,>
the embodiments of my invention will be best un
-,An. annular toroidal member. I8 is secured to
Vvthe~ ring 6 andl forms therewith a circular hollow
chamber. One side 200i _the member I8 is paral
l‘ leljw' h_the cowling and-iis’secured thereto by the
rivetsv 8; a second side 22 extends radially inward;
derstood by reference to the‘following speciñca
"tion and claims and the illustrations in the ac
`
companying drawings, in which;
'
_
45
'
,Y
,
' "
‘
‘
Figure 3 is a sectional view takenon Allin-.eïS--vf'il .
`
» openings through wh1ch project ears or scoops 26
' ` _
¿integral _with the annular torus which face for
Figure 2 is a sectional view taken on line 2-2
of Figure 1;
secured to the ringä.
l . The cowling is provided with a pair of spaced
Figure 1 is a perspective view of my construc
tion as applied to an aircraft engine;v
and thefthird side 24 extends axially back and is
50
,ward' and force air intor the chamber when the
„plane moves through the air ori-the propeller ro
_ tates. . Along ythe sides and top kof theengine are
La rpluralityof longitudinally extending exhaust
Figure 4 is a sectional view taken online 4-4
lines 28 which conduct the hot gases ~from the
„of Figurel;
cylinders vto ,the discharge` point at; the rear.;„ Of
55
I" , ¿Figure ‘5 >is >a top planview showingy a modified
of Figure 1;
y
.
v
`
.
.
2,411,936
3
necessity these lines operate at very high tem
peratures and it is desirable to eliminate this
heat from the engine area. A collector shrowd
30 is therefore mounted around,'but spaced a
short distance from, each exhaust line to enclose
the same for its length along the engine, but
permit Acoolant. leakage at points where the mani
fold is connectedjt‘othecylindergblock. The for
opening 33’ and enclose the exhaust pipe 66 re
spectively. In this manner air flowing in through
opening 33’ will wipe over the» whole of the ex
haust manifold up to within a short distance of
the engine and pass out over the exhaust pipe
to cool the same.
,
The modification shown in_Figures 8-12 inc.
has the same annular ‘collectionf'chainber formed
o'f‘annular plate'ß’ and angular ring 52, the scoops
juxtaposition with the toroidal chamber and are 10 26 not showing in this vertical section. Air is
connected into the same by flexible tubing >32'
therefore collected and introduced into this
fitted to openings 33. Thus air scooped vYintothe
chamber for the distribution to the Various parts
chamber may flow back through the shrowds 30
as
before, The >-enclosing chamber for the ex
and cool the exhaust lines.
‘
` `
~
haust manifold however in this instance has two
There are also located in a‘ïseries of longitu-f l U'separatechamb‘ers, one chamber enclosing di
dìnal rows on the engine a lset of spark plugs to
rectly'the exhaust manifold and the second being
ignite the gasoline mixture Ainïa series of,v cylin-.
. in-_the nature of a bypass for introducing cool
ward ends'of the shro'wds 30 are brought into
ders. These are shown at 34 and are located ad
air to those parts which tend to run hottest.
jacent the exhaust lines. A hollow tube 36 yis
Thisl enclosure consists of one stamping ‘I0
mounted adjacent each row of spark plugs which 20 adapted to be secured to the engine block at the
Óhasa series off'openings 38. therein adjacent >each
>plug so that air will blow’on the plug to ‘cool it
manifold and .having'o-penings 'l2therein through
off. As in the previous case, »the forward end of
the tube 36 is connected to the annular air cham
tion is stamped to conform to theshape ofthe
ber by-fleXi-bletubing 46 fitted to openings 4|.
There are as many exhaust shrowd tubes -and
f-»spar'k‘plug tubes as there are exhaust lines and
rows of spark plugs.
ï“ ' Therefore, with air entering the ears or scoops
26 to provide a certain air pressure'within the"
-"annular chamber, air is provided to flow back
which AAthefmanifold stacks may pass. ` This'por
manifold ina vertical plane as best shown in
Figurey 1l and extends up over the same to con
duct air into proximity with the exhaust mani
fold but let it circulate past.
A vsecond half 14
completes the enclosure, -the two halves being
held together vby cap screws 'I6 spaced along the
'seams and by spacer bolts 18 through the center
portion. Within the top of theenclosure formed
*thro-ugh‘the tubes 3S and 36 to cool the exhaust
lines and the spark plugs and therefore permit
the engine to operate at a cooler temperature and
by these two- halves there are provided at suita
ble points resilient spacers 80 adapted to press
*lengthen the life of the parts. Since the annular
chamber is substantially of square cross section,
the enclosure.
as shown f in Figure 2, it is strong mechanically
and assists considerably in strengthening the
fuselage or cowling.
against the exhaust manifold and the inside of
f
The hottest points in the exhaust manifold are
of course the points where the hot gases are in
troduced from the combustion chambers or that
>point ladjacent openings 72 calledl the stacks.
1 '~ -Referring now to the form of invention shown 40
»Thereforeit would be -advantageous to introduce
in Figures 5, 6 and 7, there is providedy as before
y‘the enginef located within the housing 4, the
latter in this instance terminating in a plane ap
l-proximatelyat‘the forward'end of the engine.
»An annular plate 6’ secured to and supported by
additional `cooling fluid atthese points. Also, as
the air or other coolingffluid flows back'within
the enclosure, it is heated so that by the time it
reaches the rear it does not have thesame heat
the engine isfianged over at its outer periphery
and secured'to the inner surface of the housing 4
>g by rivets’S. An annular tor'oidal member 52 simi
f' absorbing ability that it had farther to the front.
lar to‘imember i3 is secured> around the outer
baflie t2` which encloses a> bypass chamber 84 to
one side of the exhaust manifold. This is held
vedge of plate S’ by the same rivets 8. The an
~; gular member 52 is secured to the plate 5' and
A‘has a» cylindrical portion which extends out ax
f ially--of thefengine and then parallel to the plate
" 6’ until its diameter is approximately that of the
housing. The outer periphery extends back to
ward the outer edge of plate 6’ and forms with
the plate 6’ an annular air intake chamber.
Scoops 26’ are supported outside the housing as
before to force air into `the chamber.
’
’ The plate 5’ ‘has openings 4i’ therein for the
connection of tubes 35 to cool the spark plugs
>3ft and also larger openings 33' to provide air
v for cooling the' exhaust lines. In this modifica
- tion the enclosure conducting the air around the
- exhaust lines is'formed of two- halves- 54 and 5S
which are so stamped as to conform to an upper
ï and lower half around the exhaust manifold.
AThey are so stamped that they may be secured
‘ together between pairs of exhaust lines by bolts
58 and sho-rt brackets Eil extending out from the
face of the motor block are connected. thereto
»- by the same bolts to support the assemblyon the
side-of the engine. The front and rear portions
_ of the-enclosure -are drawninto cylindrical >shape
It would therefore be advantageous to introduce
more air toward the rear. y'I'hese advantages are
provided in the present design by including a
in-place by the spacer bolts 'i8 which carry clamp
ing spacer portions 86 and 88 to clamp the baf
ile.
v
'
'
Cut into'the baille 82 at points lying opposite
f' the exhaust manifold stacks are slots 93 so -that
air in the bypass may flow- through the slots di
rectly onto the -stacks and of course at the rear
end the bafiie wallceases and the air may ñow
over the whole exhaust manifold. In this, man
.ner cool .air is bypassed from the intake and
passed along the side of the enclosure to be in
troduced at those points of highest temperature.
The_air flowing through the remainder of the
-enclosure cools as it »flows'over the exhaust mani
fold.
,
.
,
It will thus beobvious Afrom the foregoing that
I have provided a chamber for collecting fluid
under pressure for cooling that also serves as
a support for the cowling or housing and that in
cooling the manifold I have also provided addi
tional`r supplementary cooling for the hottest
points,
I claim:
'
'
»
e
l. In auxiliary cooling means for alsubm‘erged
‘such as 62 and-64 tok be secured to the flangedi ,75. liquid cooled .internal combustion engîne'mounted
2,411,936
within a housing having a hollow member con
reservoir.
lar hollow chamber secured between the engine
front and the housing, air scoops connected to
the chamber to conduct air thereinto, a plurality
of longitudinally extending ducts which extend
'
»
3. In auxiliary cooling means for a submerged
liquid cooled internal combustion engine mounted
within a circular housing and having exhaust lines
and spark plugs, and an annular hollow chamber
mounted between the engine‘front and the hous
ing iiuid and a support for the housing.
y
2. In auxiliary cooling means for a submerged
within a circular housing, and having an annu
,
the support for the housingr and acts as an air
nected to both the housing and the engine, means
for introducing air into the chamber and ducts
connected to the member and extending back over
the engine to cool certain desired points where
by the member acts as both a distributor of cool
liquid cooled internal combustion engine mounted
6
engine, whereby the annular chamber reinforces
ing, means to conduct air Vinto the chamber, a
10
plurality of longitudinally extending cooling ducts
adjacent the exhaust lines and spark` plugs and
means for connecting the same to the chamber
whereby the annular chamber reinforces the
means to support the circular housing and also
acts as an air reservoir for cooling.
back over the engine connected to the chamber 15
CLYDE R. PATON.
to conduct air for cooling to various parts of the
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