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Патент USA US2128789

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Àug» 30, 1938.
R. ANxloNNAz
2,12817‘89 `
AIRCRAFT MACHINERY
Filed Feb. 8, 1936
/ A/ veA/ȇr
`
>Patented Aug. so, 193s . „
, 2,128,789
.UNITED/STATES PATENT OFFICE ,
,i 2,128,789
KAIRCRAFT MACHINERY
l,llene Anxionnaz,- . Paris, France
Appucauonrebruary s, 193s, serial No. 63,000
_
In France February 16, 1935
y -
4 Claims.
The present invention relates to a turbo-com
pressor for aircraft engines, the'exhaust gases
of which are utilized, in the turbine, in order` to.
increase theengine output, and especially to re
(Cl. 244-59)
stream that has flown past the engine cylinders
ensures its energetic cooling-_a useful feature in ‘
view of_ the high temperature of the exhaust
gases fed to said turbine.- In passing over-“the
engine, the air is_ heated only to such a slight
establish the normal output when the engine is
run at high altitudes.
extent that it is still capable of emcient action on
Hitherto this has- been done chiefly in connec- _ the turbine b.
`
tion with vwater-cooled aircraft engines, and the
The arrangement may also be carried out with
position of the turbo-compressor or compressors different engines and a' different number of «
io 4has been determined solely by the space available _' turbo-compressors.
for mounting, or by considerations of general
eiliciency.
What I claim is:
-
'.
l. In an aircraft, the combination of a fuse
The object of the present invention is to adapt ~ lage, an air-cooled engine carried by said fuse
a turbo-compressor to an air-cooled radial en
lage having at least one row of cylinders project
15 gine, under `satisfactory conditions, and to this
ing radially from said fuselage so as to be cooled
end the turbo-compressor is located in rear of by the relative wind produced along said fuselage »
the cylinders and the axis of the turbine is at vby the movement of said aircraft, and a turbo
right angles to the axis of the radial engine, so rcompressor carried by said fuselage behind ysaid
that the head resistance due to the presence of row of cylinders, said turbo-compressor including
20 the turbine „is reduced to the minimum, efñcient
a turbine having itsaxis atright angles to the
cooling of the engine cylinders by the air is main
engine axis and a compressor coupled directly
tained, and powerful cooling of the hot member with said turbine coaxially therewith,"said tur
of the _turbo-compressor-that is to say, the
bine being located substantially in a cylindrical Y y
turbine-is, ensured. '
'
26
In the accompanying diagrammatic drawing
which illustrates, by way of example, an embodi
ment of the arrangement; Figure l represents a
side elevation of the engine and turbo-com
pressor, in vpartial section,_ and Figure 2 is a
30 rear view, from right to >left of the arrangement
shown in Figure 1.
'
In this example, a radial engine with two rows
of cylinders a ai has'been selected.- One of the
cylinders, a_ or ai of each row, is shown in side
35 elevation (ai beingr partly broken away), the
other cylinders being indicated by their position
in the housing g. 'I'hese cylinders are connected,
>~ by means of exhaust pipes d, with two turbo
compressors, each comprising an exhaust-gas
'I'he _exhaust
manifold is in the form of a ring e constituting
a silencer and :is streamlined to ofl’er the mini
mum resistance to the air. 'I'he turbine b is '
40 turbine b and a compressor c.
, ‘located within said ring e and behind the cylin
45 ders a, ai, its axis being at right angles to the
axis oi’ the radial engine. The- compressor c is
situated inside the casing f, extending from the
housing g, the whole being also streamlined.
y 'I'he turbine b, being located behind the cylin-l
der a, does not increase appreciably the head
resistance, which is also reduced >by the stream
surface coaxial with said engine and passing,
through the outer endsof said cylinders, and
said compressor being located between said tur
bine and the axis of said row ofv cylinders.
,
2. In an aircraft, the combination of a fuse
lage, an air-cooled engine carried by said fuse
lage having at least one circular row of cylin
ders projecting radially from said fuselage so
as to be cooled by the relative wind produced
along said fuselage by the movement of said air
craft, and a turbo-compressor carried lby said
fuselage behind said row of cylinders, said turbo
compressor including a turbine having its axis
at right _angles to the engine axis and a' com-,
pressor coupled directly with said turbine co
axially therewith, said turbine being located'
substantially in a cylindrical surface coaxial with
said engine and passing through the outer ends
of said cylinders, and said compressor being
located at least partly in said fuselage.
l
' 3. In an aircraft, -the combination of a fuse
lage, an air-cooled engine carried by said fuse
lage having at least one circular row of .cylinders
projecting radially >from said fuselage lso as to
be cooled by the relative wind produced along
said fuselage by the movement of. seid aircraft,
a turbo~compressor carried by said'fuselag'e be
hind saidJ row of cylinders, said turbo-com-4
pressor including a turbine having its exisat
lining of the turbine and casing, whilst the pres
ence of the turbo-compressor .does not impair' ' right angles to the engine axis and a compressor .
appreciably the cooling of any ofthe engine
cylinders. The location of turbine b inthe air
coupled directly with said turbine coaxially ,
therewith, said turbine being located substan
2,128,789
2
tially ln a cylindrical surface coaxial with said
engine and passing through the outer ends of
said cylinders, and said compressor being located
at least partly in said fuselage, and an annular
manifold for said engine coaxial therewith so as
to surround said fuselage at a distance therefrom,
arranged to form a casing for said turbine, said
manifold being of streamlined'axial section.
wind produced along said aircraft element by
the movement of said aircraft, and a turbo
compressor carried by said aircraft element be
hind said row of cylinders, said turbo-compressor
including a turbine having its axis at right angles
to the engine axis and a compressor coupled
directly with said turbine coaxially therewith,
said turbine being located substantially in a.
cylindrical surface coaxial with said engine and
passing through the outer ends of said cylinders, 10.
10 lined aircraft element, an air-cooled engine car- - and'said compressor being located between said
ried by said aircraft element having at least one
ro_W of cylinders._
row of cylinders projecting radially from said turbine and the axis 0f said
RENE ANEHONNAZ.
4. In an air craft, the combination of a stream
aircraft element so as to be cooled _by the relative
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