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Патент USA US2407194

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" Sepf. 3,1946.
Filed-‘June a, 1943
, 3 Sheets-Sheet 1
1 Gecz'ZG. VG/PQS
A tiorney
Sept. 3, 1946.
2,“ 7,194
Filed June a, 1943
s Sheets-Sheet 2
Sept. 3,f194s.~
Filed June a, 1945
3 ‘Sheets-Sheet s
' Inventor
' 1j I
Patented Sept. 3. 1946
Cecil Gordo'n Vokes,
Application Ju‘ne‘8, 1943, Serial No. 490,067
In Great Britain June 11, ‘1942
11 Claims. (01. i‘ssésa)‘
This inventionis primarily designed for ?lter
ing air passing to the engine of aircraft, but it
is notnecessarily con?ned thereto,lparts of the
invention being of wide application where condi
tions are appropriate to their use.‘ ‘
rarily. For example, it may be desired to?lter
the air passing to an aircraft ‘engine when‘taking
oif or landing or at low altitudes but to leave the
intake free while actually ?ying or when ?ying
Fig. 3 is a fragmentary section‘on‘ the line
III‘—III of Fig. 1,
Figs. 4 and 5 are corresponding ‘views‘to Figs:
It is'often desirable 'to‘cut out a filter tempo
at higher altitudes.
Fig.2 is‘ a similar ‘view to ‘Fig.’ 1 showing‘the“
parts in an alternative‘position,‘
p _
The present invention provides a method of
?ltering air supplied to the engine ‘of an aircraft
in which the air is ‘drawn to the engine intake
through ?ltering means when the aircraft is on
the ground with the engine running and a pas
sage for its direct entry is ‘opened under prede
termined ?ying conditions, a ?ow through ‘the
1 and 2 of an alternative form,
Fig. 6 is a fragmentary section on line VI-VI
‘of Fig. 4.‘
Fig. 7 is an enlarged detail of a portionof
As shown in Figs. 1, 2 and 3, the ?lter unit‘
lies in a scoop or other entry duct I arranged
to admit air from outside the surface skin‘ of an
’ engine cowling or wing or other suitable part‘of
an aircraft. The ?lter unit may include a?lter
ing element 2 (for ‘example a pleated“ ?ltering
screen) mounted in a frame 3 which normally ex
?ltering‘ meansrbeing simultaneously induced in
tends‘at an incline across the duct ‘I. ‘ The en
the reverse direction so as‘ to dislodge accumu
‘type of‘engine inlet may, for example,
lated particles.
try scoop (where such is used) for an u -draught
have a
baseportion 4 covered by a false bottom 5 which
extends back nearly'to the trailing edge of the
?ltering means including a duct structure and
frame 3 of the unit. The frame is pivotally
a ?ltering screen,‘ an element of the ?ltering
mounted at 6 and when in use lies‘at'an up
means is made movable in door-like fashion, the 25 ward and forward incline as shown at Fig. '1.
said element controlling air entering the struca
An extension ‘I on the frame of the unit can close
ture by causing it when in the one position to"
or nearly close the passage 8 in the base portion
pass through ?ltering means to the air intake ‘
leads to opening‘ 9. A small leakage will:
of the engine and when in another position caus
normally take place past the‘extension ‘I, so that
ing it to pass direct to the said air intake with
a certain amount‘ ‘of dirt from the ?lter collecting
out filtration’ and a small proportion to pass
in front of it can pass through and emerge from‘
through the ?ltering means in reverse direction
the exit 9 into the outer air.
and dislodge accumulated particles.
Distance pieces or studs I!) are formed under
In a typical form a ?ltering unit is so mounted
the frame 3 and when the unit is moved down to
at an incline in the ?lter casing or duct that it
occupy the top of the base portion, the false bot
will normally be largely self-cleaning and so that
tom 5 moves down‘ beneath it, as shown in‘ Fig. 2.
it can be moved out of the path of the incoming
The exit 9 into the outer air is arranged to help
air either at will or ‘automatically under prede
induce air ?ow through the element-from the
termined conditions. Its control could, for ex
clean side (which now faces the interior of the
ample, be linked with that of a supercharger or 40 duct I) ‘so as to remove adherent dust and grit
that of‘ a retractable under carriage. The pres_
from the dirty side and discharge it. Air stream
ent invention has as one important part the fact
separating vanesll or air straightening means
may be permanently ?xed in the duct. The false
that the arrangement is such as to take advan
bottom will again rise into position and give- a
tage of the movement of the ?lter unit to produce
a reverse flow through the material of the ?lter 45 smooth path to‘ the air ?ow when the unit is re
turned to working position. It might be merely
screen when the ?lter is‘ cut out vand to discharge
spring loadedas by springs l2 to allow‘ of its
the particles or dirt thereby removed.
movement‘into the base portion and automatic
Other parts of the invention "are embodied in
return; or it could be mechanically moved to con
typical forms ‘shown upon the accompanying
to the‘ movement'of the unit. As shown,‘
drawings, the parts for which a monopoly is de
operating means l3 (which may be electric,‘lhy-'
sired being those "delimited'by the’ claims.
draulic or ‘pneumatic of conventional form) on
In the drawings:
erates a lever I 4 pivoted at l5.
- Fig.‘ 1 is a sectional elevation of an‘ intake ar- ‘ _ ates a bell-crank lever l1 pivoted
Accordingly, in ‘an aircraft having an engine
55 ‘the false bottom; link l9‘ and arm ZIJ‘attached
to the ?lter unit operate the latter; and a link
2| operates a ?ap 22 in the upper wall of the
duct I, enabling the full area of the front of the
?ltering element to be used in the position of
Fig. l.
of air tends to clean the ?lter.
2. A construction as de?ned in claim 1, where
in the ?lter cleaning air is directed for discharge
The back of the frame is closed at 23 to
seal off the aperture when the ?ap 22 is in the
position shown in that ?gure.
It will be noticed that the dirty side will not
be able to contaminate the clean air side and 10
that the forward speed of the machinev will
create a pressure at the mouth of the air scoop
or duct and air will be able to blow through the.
element in the reverse direction and thereby
automatically clean it.
rection of the air therethrough during its ?ltering
function, whereby such reversely directed current
fully beyond the stream of air passing through
the duct to the engine.
3. In an aircraft having an engine, a ?ltering
assembly including a duct and a ?ltering screen,
means for causing the flow of air through the
duct to selectively and at will, pass through the
?ltering screen for ?ltering or, in main part, to
pass through the duct free of the in?uence of the
?ltering screen, the ?ltering screen when in non
Back ?re sometimes damages the elements and 15 ?ltering position with respect to the duct caus
ing a portion of the air passing through the duct,
arrangements could be made, therefore, for the
unit or some part of it to depress in‘ case of a
‘ to be directed through the ?ltering screen in a
direction reverse to the ?ow of air through that
bad back ?re, against a spring'loading or other
screen during the ?ltering function, whereby the
means, so as to give free exitto the back ?re
gases. This is shown as illustrated by the pivot 20 ?ltering screen is cleaned.
4. A construction as de?ned in claim 3 where
ing of both the frame 3 and arms 29 on the axis
in a discharge passage is provided for the clean
6 and the'use of springs 24 tohold the frame nor
ing air passing in a reverse direction through the
mally against the abutment on the arm.
?ltering screen to avoid in?uencing the stream
Such arrangements are further examples of a
of air passing through the duct to the engine.
door-like use of an element carryingv the filter
ing screen, and any suitable pivoted, sliding or
5. In an aircraft having an engine, a duct for
supplying air under pressure to the engine, a ?l
tering element mounted fOr movement with re
spect to the duct, said element in one position
Turning now to Figs. 4 to 6, the intake duct i
has panels including ?ltering screens 2. In this 30 traversing the duct to ?lter the air passing there
through and in another position being free of ?l
case there are alternative intakes to the duct,
tering influence on the air passing through the
namely through the ?ltering screens 2 and by the
rotating single or multiple door-like movement
can be equally readily applied to such an element.
front or scoop entry controlled byrthe movable
element 30. This element takes the form of a
flap with an arm 3| connected to conventional
control means by link 32.
It will be clear that with the ?ap 3%! closed as
shown in Fig. 4, the air to be supplied to the en
gine is drawn through side and bottom openings
immediately beyond the ?lters 2, see Fig. 6, and
through the ?lters and aligned openings in the
wall of the duct l for delivery of ?ltered air to
the engine. When the ?ap 36 is open, as shown
in Fig. 5, the intake of the duct I initially receives
the air under the pressure incident to the for
ward travel of the aeroplane. Therefore, this
air stream is fed directly through the duct i, free
of any direct in?uence of the ?ltering elements
2. The air passing through the duct l under these
conditions will in part ?nd its way laterally
through the ?lters 2' incident to the eduction ef
fect of the air ?owing longitudinally of the skin
beyond the ?lters relative to the duct. This will
cause a small portion of the airfrom the duct
to be de?ected laterally of the ?lters, to pass
duct, the ?ltering element in the latter position
presenting its reverse ?ltering side to the air
35 passing through the ductand a discharge chan
nel below and open to the ?ltering element when
in non-?ltering position, whereby when the ?lter
ing element isvin non-?ltering position a portion
of the air ?owing through the duct is moved in
40 reverse ?ltering direction through the ?ltering
element to the discharge channel.
6. A construction as de?ned in claim 5, where
in the duct wall is formed with an opening to
receive the ?ltering element in non-?ltering posi
tion and wherein a member displaceable by the
?ltering element when moved to non-?ltering
position‘ will establish communication between
the duct and the discharge channel through the
?ltering element.
'7. A construction as de?ned in claim 5. where
in means are provided to normally close the duct
against the discharge element and wherein the
?ltering element when moved to non-?ltering
position, displaces said closing means.
through the ?lters in a direction the reverse of
the air movement when passing through said ?l
ters for ?ltering, as when the duct intake ?ap 39
8. A construction as de?ned in claim 5, where
in the ?ltering element is provided with an ex
tension to partly bridge the discharge channel
when the ?ltering element is in ?ltering position.
9. In an aircraft having an engine, a duct hav
is closed. This reverse flow of air and pressure
through the ?lters tends to clean them for the 60 ing an intake opening facing in the direction of
aeroplane travel to direct air to the engine, man
purpose more particularly described in connec
ually operable means for closing the intake open
tion with Fig. 1.
ing of the duct, ?ltering elements ‘arranged im
mediately beyond the Walls of the duct, the duct
1. In an aircraft having an engine, a duct for
delivering air to the engine, ?ltering means se 65 being open to the air passing through the ?lter
lectively functioning at will to ?lter the air pass
ing elements, and means beyond the ?ltering ele
ing through said duct to the engine or to permit
ments forming ?lter inlets for air. to be passed
the air passing through the duct to the engine to
through the ?ltering elements and to the ‘duct,
be free of ?ltration, manually controlled mech
whereby when the means controlling the intake
anism for said ?ltering means to cause the air
of the duct is closed, the air passing through the
passing through the duct to the engine to remain
duct is delivered through the ?ltering inlets and
un?ltered, and means to utilize a portion of the
when the intake controlling means is open, the
air ?owing through the duct in'un?ltered condi
air passing through the duct is admitted through
tion as a pressure medium to pass through‘ the
such intake and passes through the duct substan~
?ltering means in a direction reverse; to ‘the di 75
tially free of ?ltering in?uence from the ?ltering
ing an intake opening facing in the direction of
the travel of the aeroplane, a skin section con
forming in part to the walls ‘of the duct and
10. A construction as de?ned in claim 9, where
by when the intake controlling means is open,
the air passing longitudinally of the ?lter inlets
incident to the travel of the aeroplane will present
an eduction effect through the ?lter elements to
cause a portion of the air passing through the
duct to ?ow in reverse direction through the ?l
tering elements to clean the same.
11. In an aircraft having an engine, a duct hav
, spaced from said walls, ?ltering elements ar
ranged 'between the skin section and adjacent
wall of the duct, the skin section and adjacent
wall of the duct being formed with openings to
permit air to ?ow through the ?ltering elements
and into the duct, and a manually operable flap
10 for closing the intake opening of the duct at will.
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