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Патент USA US3085409

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April 16, `¿£1963
w. T. KlTcHx-:Ns
3,085,399
ROTARY JET ENGINE
Filed May 5, 1961
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April 16, 1963
w. T. KlTcHENs
3,085,399
ROTARY JET ENGINE
Filed May 5, 1961
4 Sheets-Sheetl 2
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INVENTOR.
WML/,4M 7.- e/Tcws/vs,
BY
April 16, 1963
w. T. KITCHENS
3,085,399
ROTARY JET ENGINE
Filed May 5, 1961
4 Sheets-Sheet 3
INVENTOR.
WML/4M 7.’ ,e/ Tof/Ems,
¿Trae/VERS.
_ April 16, 1963
w. T. KlTcHENs
3,085,399
ROTARY JET ENGINE
Filed May 5, 1961
4 Sheets-Sheet 4
Wg
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“Mw/Wm" ‘
BY
A rraeA/Eys
3,085,399
Patented Apr. 16, 1963
2
site end the housing drum 18 is rotatably supported on a
3,085,399
ROTARY JET ENGINE
William T. Kitchens, 1216 Pioneer Road,
‘West Palm Beach, Fla.
Filed May 5, 1961, Ser. No. 108,074
8 Claims. (Cl. dil-39.35)
‘bearing bushing 24 rotatably engaged on the enlarged
top portion 25 of shaft y14 and extending between said
enlarged shaft portion and an integral bearing sleeve
26 formed in the wall 15 of the main housing. The
enlarged upper portion 25 of shaft 14 is formed with
an outwardly extending ñange 27 formed with radial pas
sages 28 communicating with a central bore 29 formed
This invention relates to power plants, and more par
in shaft portion 25, and communicating with a plurality
ticularly to an engine of the rotary jet type.
A main object of the invention is to provide a novel 10 of outlet conduits 30 secured in the outer ends of the
and improved rotary jet engine which is relatively simple
in construction, which provides high output, and which
provides smooth and eñ‘icient operation.
A further object of the invention is to provide an im
passages 28 and connecting said passages to the space
immediately adjacent the periphery of the top portion of
a generally cylindrical rotor member 31 rigidly secured
on shaft 14, for example, by being splined thereto in the
proved rotary jet engine which involves relatively inex 15 manner illustrated in FIGURE 3.
The rotor member "31 is formed at its periphery with a
pensive components, which is rugged in construction, and
which is extremely economical in utilization of fuel.
A still further object of the invention is to provide an
plurality of inclined outwardly projecting radial vanes
32 which are arranged in evently spaced peripheral rows.
Rigidly secured to the inside surface of the drum member
improved rotary jet engine which is relatively compact in
size, which has high capacity, and which is provided with 20 y18 is a generally cylindrical shell member 33 formed
means for efficiently mixing the air and fuel admitted
thereto and for developing a high output pressure in the
resultant mixture for delivery to the firing chambers of
with horizontally extending, inwardly projecting evenly
spaced bañle plates 34 which extend into the spaces de
fined between the rows of peripheral vanes 32, as shown
in FIGURE 3, and which cooperate with the vanes 32 in
the engine.
A still further object of the invention is to provide an 25 a manner presently to be described to thoroughly atomize
and mix liquid fuel with air to provide a homogeneous
mixture thereof at high pressure at the lower portion of
the member 18.
As shown in FIGURE 3, the top Wall 35 of the drum
air admitted thereto to provide the proper combustible 30 member I8 is formed with air admission apertures 36
located over the annular space between the main body
mixture for operating the engine.
portion of rotor member 31 and shell member 33, so that
Further objects and advantages of the invention will
air may be admitted directly into said annular space.
become apparent from the following description and
A liquid fuel supply manifold 37 is secured in the
claims, and from the accompanying drawings, wherein:
improved rotary jet engine which is relatively light in
weight in proportion to the power rating thereof, which
is easy to install, and which is provided with self-contained
means for thoroughly and efficiently mixing the fuel and
FIGURE 1 is a horizontal cross sectional view taken 35 top end portion of the stationary bushing 24, fuel being
admitted into the manifold 37 from a fuel supply line
38, as shown in FIGURE 2. An annular conduit member
69 is threadedly engaged in the top end portion of shaft
FIGURE 2 is a cross sectional view taken substantially
element 25 and extends rotatably through the bottom wall
on the line 2_2 of FIGURE 1.
FIGURE 3 is an enlarged vertical cross sectional View 40 40 of the liquid fuel supply manifold 37, the conduit
member 39 being formed with a conical seat 41. A coni
taken substantially on the line 3_3 of FIGURE l.
cal valve element 42 is mounted on a depending valve
FIGURE 4 is a horizontal cross sectional view taken
rod 43 which extends slidably and axially through the
on the line 4_4 of FIGURE 3.
top wall 44 of manifold 37 and which is biased towards
FIGURE 5 is a horizontal cross sectional View taken
45 the valve Seat 41 by a coiled spring 45 surrounding the
on the line 5_5 of FIGURE 3.
stem member 43 and bearing between the conical valve
FIGURE 6 is an enlarged cross sectional view taken
4Z and the wall 44, suitable washers 45 being interposed
substantially on the line 6_6 of FIGURE 2.
through a rotary jet engine constructed in accordance
with the present invention.
between the top end of the spring and wall 44, as shown
FIGURE 7 is a plan view of a fragmentary peripheral
portion of the rotor of the engine of FIGURE l, said view 50 in FIGURE 3. The upstanding rod 43 is formed at its
top end with a ball element 46 which is rotatably received
being taken substantially on the line 7_7 of FIGURE 2.
in a spherical socket 47 carried by a control rod 48 pivoted
FIGURE 8 is a cross sectional View similar to FIGURE
at 49 to an opstanding bracket 50 mounted on the top
6 but showing a modified form of firing chamber which
wall 15 of main housing 12, whereby to regulate the
may be employed in the engine of the present invention.
Referring to the drawings, and more particularly to 55 admission of liquid fuel from the manifold 37 into the
conduit 39, and thence to the annular space defined be
FIGURES l to 7, 11 generally designates an improved
tween the main body of the rotor element 31 and the
rotary jet engine constructed in accordance with the pres
shell member l33.
ent invention. The engine 11 comprises a generally circu
Designated at 51 is a ring gear which is secured on
lar main housing 12 which is secured on a base portion
13 in which is journaled the output shaft 14 of the engine. 60 the bottom wall 19 of the inner housing -18 concen
trically with the shaft 14 and which is gearingly coupled
The wall «15 of housing 1‘2 opposite base portion "13 is
to the gear 22 by a pair of diametrically opposite idler
formed with a plurality of air inlet openings î16 for ad
gears 52, 52 which meshingly engage between the ring
mitting air into the housing for subsequent mixture with
gear 51 and the central gear 22, the idler gears 52 being
liquid fuel in a manner presently to be described. The
housing is provided at its periphery with a plurality of 65 journaled between top and bottom annular plate members
53 and 54 mounted for free rotation around the axis of
exhaust conduits 17 for discharging the gaseous products
shaft 14. Thus, the upper plate member 53 rotatably
of combustion of the engine into the atmosphere.
engages with a bearing ring 56 surrounding the portion
Designated at 13 is a drum-shaped inner housing which
of shaft 14 between rotor member 31 and gear 22, and
is rotatably mounted concentrically with the main hous
ing 12 and which is rotatably supported at its bottom 70 the lower plate member 54 rotatably engages between the
reduced sleeve portion 57 of the bearing bushing 20 and
wall 19 on a bearing bushing 20 provided on the hub 21
the inner circular edge of the annular bottom Wall 119.
of an inner gear 22 splined to the shaft 14. At its oppo
3,085,399
3
d
Thus, rotation of the inner housing y18, produced by com
bustion of the fuel mixture, as will be presently described,
neath the batiie member 73 and in the path of movement.
of the intake ends 64 of the venturi members 63 mounteddrives the housing A18 in a clockwise direction, as viewed
in the forward ends of the combustion chambers. It will>
in FIGURE 1, transmitting torque through the planetary
be noted that the forward portions of the venturi memgears 52, S2 and the gear 22 to the shaft `14, causing the
bers 63 are formed with slots '77 to admit air into thev
shaft 14to be driven in a counterclockwise direction.
fuel supply spaces 62 so that this air may be mixed with‘
_ It will be noted that the vanes 34 move in a clockwise
the fuel mixture in the supply spaces and may be fur-~
direction with the drum member 18, whereas the vanes
nished to the rear portions of the venturi members 63l
30 move in a counterclockwise direction with the rotor
through the discharge openings 66, creating a further'
member 31 so that the elements 34) and 34 move past 10 mixture of air and atomized liquid fuel and aiding in the
each other at a relatively high speed, traveling in oppo
Complete diffusion of the atomized liquid fuel with the
site directions. The liquid fuel admitted into the an
air admitted into the firing portions I69 of the combustion
nular space containing the elements 30 and 34 is thus
chambers.
engaged by and completely atomized by the rapidly mov
The ignition device 70 may be timed in any suitable
ing vanes 32 and baffle elements 34, and the inclined vane 15 manner and may be operated in conjunction with any
elements 32 build up a substantial pressure in the mixture
conventional distributor arranged to provide proper tim
of air and fuel thus produced, which is relatively high
ing of the spark provided by the member 7€)` with the
at the lower end of the member 1S. The difference in
power strokes of the engine. Thus, as shown in FIG
pressure thus causes air to be drawn into the top end of
URE 2, the associated distributor system may be con
the housing 18 through the air admission aperture 36 by 20 trolled by a photo cell `80 -arranged to receive a light
suction and to be aspirated into the annular space bebeam from a light source 81, the light source y81 being
tween the rotor member 31 and the shell 33 to be ‘homo-v
mounted on the base element 13 and the photo cell 80
gencously mixed therein with the atomized fuel.
being mounted on the top wall 15 of the main housing,
Secured to the lower end portion of the inner housing
the beam of light being interrupted intermittently by the
1S are a plurality of evenly spaced arcuate rigid conduits
arcuate conduit element 6i) as housing 1S rotates. Thus,
60 which are secured at their outer ends to respective
the timing of ignition will depend upon the positions of
combustion chambers 61 (FIGURE 6) the conduits 60
the combustion chambers 61 around the axis of the en
communicating with annular fuel admission spaces `62 de
gine, and the devices ’70 will fire each time the firing
ñned within the combustion chamber 61 by the annular
chambers 61 are in predetermined positions relative to
venturi conduits 63 secured in the -forward ends of the 30 the main housing ì12.
chambers, as shown in ‘FIGURE V6.
In operation, when the combustible fuel mixture is
The chambers 61 comprise air scoop intake portions
ignited in the firing spaces 69, the rapid combustion of
64 at their forward ends communicating with the in
the fuel mixture produces a reaction tending to propel
wardly convergent forward end portions of the venturi
the firing chambers 61 forwardly, namely, to the right,
with apertures 66 through which the liquid fuel and air
on the housing 18, rotating said housing and developing
conduits 63. The venturi conduit members 63 are formed 35 as viewed in FIGURE 6, producing a clockwise torque
mixture from the space 62 is admitted into the venturi
member 63 from the associated supply conduit 60, a check
valve 67 being provided between the end of each supply
conduit 69 and its associated fuel mixture admission
space 62, as shown in FIGURE 6. r1`he check valve 67
is of the spring-operated type and is arranged so that it
will not open unless a predetermined minimum pressure
exists in the associated supply tube 60, whereby the sup
ply of air and fuel will be cut olf when the pressure
thereof drops below a minimum limiting value. Further
more, since the chamber 62 is subjected to the pressure
developed in the communicating portions of the venturi
a counterclockwise torque on the output shaft 14, as
viewed in FIGURE 1. The air and fuel is continuously
supplied through the annular space between shell 33 and
rotor member 3l, being atomized and mixed in said space,
as above described, and. being delivered to »the combustion chambers 61 under substantial pressure. The
atomized fuel and air is further mixed with air and dif
fused as above described in the forward end portions
of the combustion chambers and is admitted into the
firing portions 69 to be ignited by the ignition devices 7G.
. As shown in FIGURE 2, the annular cover plate 73
is secured to a ring member 82 forming part of an an
member 63, the pressure in the space 62 will aid the 50 nular framework comprising a cooperating ring member
83 and connecting rod 84. The combustion chambers 61
spring, and the check valve will close unless the fuel
are rigidly secured, as by welding, or the like, to the in
supply pressure is sufficient to overcome the combined
termediate portions of the transverse connecting rods 84.
effects of the spring and the pressure in the space 62.
In the modified form of the invention illustrated in
Each tiring chamber y61 is formed with a relatively en
FIGURE 8, the ñring chambers are somewhat diüerent
larged intermediate main combustion chamber portion
in construction from those previously described, each
69 in which is mounted a suitable ignition device, such
firing chamber comprising a generally cylindrical main
as a spark plug 70 for igniting the fuel >and air mixture
body 90 secured to the connecting rods 84, said main
introduced into the combustion chamber. It will be
body being provided at its forward portion with an an~
noted that the fuel and air mixture furnished from the
associated supply space 62 is further mixed with air ad 60 nular venturi-forming member 91 provided with an axialV
stem member 92 secured to a cruciform supporting
mitted into the combustion chamber through the venturi
bracket 93 fastened in the forward end portion of the
member 63. The resultant products of combustion are
cylindrical member 90 and likewise in the forward porexhausted from »the combustion chamber through «the
tion of the venturi member 91. The stern member 92
outlet opening 71 provided at the end of the combustion
integrally formed at its rear end with a concave rear
chamber opposite the air intake scoop portion -64 and 65 is
wardly
facing cup-like head element 95 defining an an~
subsequently are discharged through the exhaust conduits
nular
venturi
space 96 with respect to the rear portion
17.
.
of the main venturi member 91. Said main venturi mem
As shown in FIGURE 7, an annular baffle plate 73 is
ber 91 is formed at its peripheral portion with an annular
secured over the combustion chambers y61, the bañle plate
fuel receiving cavity 97 communicating with the mid
73 being formed with a plurality of evenly spaced arcuate 70 portion of the venturi member 91 through radial passages
openings 74 deñned beneath upwardly struck arcuate
98.
louvers 75 which act as air scoop elements. The louvers
75 are inclined upwardly and forwardly in the direction
of rotation of the combustion chambers 61 so that they
serve as air scoop elements to drive air downwardly be
The cylindrical body members 9€) are secured on
bracket members 99, which are in turn rigidly secured on
the ends of the conduits 60, the members 99 being formed
Ywith cavities 100 and being provided with inwardly open`
3,085,399
5
5
by jet reaction, means gearingly coupling said inner hous
ing flap valves 101, serving the same function as the check
valves `67 previously described, the flap valves 101 open
ing in response to a predetermined pressure of the fuel
mixture in the conduits 60 and allowing said fuel mixture
ing to said output shaft, and means to admit liquid fuel
into the space between the inner housing and said rotor.
to be `admitted into the spaces 100. The spaces 10i) com
having air inlet and outlet passages, an output shaft jour
naled in said main housing, a rot-or secured on said
municate with the annular fuel supply spaces 97 of the
venturi members 91, as is clearly shown in FIGURE 8.
As in the previously described form of the invention, the
fuel mixture is admitted into the intermediate portions
of the venturi members 91, being mixed with air enter
ing the forward end portions of the members 9i) through
the forward ends of the venturi members 91, being fur
ther mixed with the air and being discharged through the
annular venturi-shaped spaces 96 into the interior of the
combustion chambers, to be there ignited by the ignition
devices 70 in the same manner as previously described.
Annular exhaust venturi members 106 are provided in
the rear end portions of the cylindrical bodies 90, to pro
vide for the discharge of the products of combustion from
2. A rotary jet engine comprising a main housing
output shaft and having outwardly projecting compressor
vanes, an inner housing rotatably mounted on said shaft
and having air inlet means opening into said main hous
ing adjacent said air inlet passages, a space lbeing pro
vided between said inner housing and said rotor, in~
wardly projecting baille elements on said inner housing
extending adjacent said vanes, outwardly projecting rigid
conduits secured to said inner housing and communica-t
ing with the space between said inner housing and said
rotor, respective jet combustion chambers mounted on
the ends of said conduits, said chambers having venturi
air intake elements, fuel ignition means in said jet com
bustion chambers, said jet combustion chambers having
the combustion chambers 90 in a manner to develop a 20 exhaust conduits at their rear ends adjacent said outlet
substantial amount of thrust. As in the previously de
scribed form of the invention, the reaction developed by
the discharge of the combustion gases produces the driv
passages, said chambers being positioned substantially
ing torque to rotate the housing 18 in a clockwise direc
ingly coupling said inner housing to said output shaft and
normal t-o radii of said output shaft, whereby to effect
rotation of the chambers by jet reaction, means .gear
tion, as viewed in FIGURE l, the torque being ulti 25 being constructed and arranged to rotate the output shaft
mately applied to the output shaft 14 to drive same in a
in a direction opposite to the direction o-f rota-tion of
counterclockwise direction.
the inner housing, and means to admit liquid fuel into
As shown in FIGURE 3, a conductive slip ring 111
the space -between the inner housing and said rotor.
is mounted on the top wall 3S of housing 1S, being suit
3. A rotary jet engine comprising a main housing
ably insulated therefrom by means of an annular insulat 30 having air inlet and -outlet passages, an output shaft jour
ing member 112 secured to the top wall 35 and formed
naled in said main housing, a rotor secured on said
with a seat in which the slip ring 111 is secured. A
output shaf-t and having outwardly projecting compressor
suitable brush 113 is provided, said brush being mounted
vanes, a generally cylindrical inner housing rotatably
in the wall 15 of the main housing 12 and engaging the
mounted on said shaft and having air inlet means open
slip ring 111. The brush 113 is suitably insulated from 35 ing into said main housing adjacent said air inlet passages,
wall 15, for example, by the use of a suitable insulating
a space being provided between said inner housing and
bushing. The brush 113 is electrically connected to the
said rotor, inwardly projecting baflle elements on said
output of the ignition system associated with the engine.
inner housing extending adjacent said vanes, outwardly
Respective ignition wires 114 connect the slip ring 111
projecting rigid conduits secured »to said inner housing
to the ignition devices '70, the ignition wires 114 being 40 and communicating with the space ‘between said inner
suitably insulated and being mounted on the respective
housing and said rotor, respective jet combustion charn
outwardly extending conduits 60.
bers mounted on the ends of said conduits, said chambers
The speed of the engine may be controlled by varying
having venturi air intake elements communicating with
the supply of fuel admitted to the engine between Ithe
said conduits and having air scoop por-tions at their for
valve element 4Z and the annular valve seat member 39, 45 Ward ends communicating with said venturi elements,
namely, by varying the angle of rotation of the control
fuel ignition means in said jet combustion chambers,
lever 4S.
said jet combustion chambers having exhaust conduits
While a specific embodiment of an improved rotary
at their rear ends adjacent said outlet passages, said
jet engine has been disclosed in the foregoing description,
chambers being positioned substantially normal to radii
it will be understood that various modifications within
of sai-d output shaft, whereby to effect rotation of the
the spirit of the invention may occur to those skilled in
chambers by jet reaction, a ring gear mounted on said
the art. Therefore, it is intended that no limitations be
inner housing coaxially therewith, a driven gear mounted
placed on the invention except `as defined by the scope
on said shaft concentrically with said ring gear, means
of the appended claims.
gearingly coupling said ring gear «to said driven gear and
What is claimed is:
1. A rotary jet engine comprising a main housing hav 55 being constructed and arranged to rotate the output shaft
ing air inlet and outlet passages, an output shaft journaled
in said main housing, a rotor secured on said output shaft
in a direction opposite to the direction o-f rotation of the
inner housing, and means to admit liquid fuel into the
space between the inner housing and said rotor.
and having outwardly projecting compressor vanes, an
4. A rotary jet engine comprising a main housing
inner housing rotatably mounted on said shaft and hav*
ing air inlet means opening into said main housing ad 60 having air inlet and outlet passages, an output shaft jour
naled in said main housing, a rotor secured on said output
jacent said air inlet passages, a space being provided be
shaft and having outwardly projecting compressor vanes, a
tween said inner housing and said rotor, outwardly pro
jecting rigid conduits secured to said inner housing
and communicating with the space between said inner
housing and said rotor, respective jet combustion cham
generally cylindrical inner housing rotatably mounted
on said shaft and having air inlet means opening into said
main housing adjacent said air inlet passages, a space
being provided between said inner housing and said
rotor, inwardly projecting baffle elements on said inner
bers having venturi air intake elements communicating
housing extending adjacent said vanes, outwardly project
with said conduits and having air scoop portions at their
forward ends communicating with said venturi elements, 70 ing rigid `conduits secured to .said inner housing and com
municating with the space between said inner housing
fuel ignition means in said jet combustion chambers, said
and said rotor, respective jet combustion chambers mount
jet combustion chambers having exhaust conduits at their
ed `on the ends of said conduits, said chambers having
rear ends adjacent said outlet passages, said chambers
venturi air intake elements communicating with said
being positioned substantially normal to radii of said
output shaft, whereby to effect rotation of the chambers 75 conduits and having air scoop portions at their for
bers mounted on the ends of said conduits, said cham
3,085,399
7
8
ward ends communicating with said venturi elements,
fuel ignition means in said jet combustion chambers,
said jet combustion chambers having exhaust conduits at
member having air inlet means at one end portion thereof
»their rear ends adjacent said -outlet passages, said cham
bers being positioned substantially normal to radii of
said output shaft, whereby to effect rotation of the cham
tending between said peripheral rows of vanes, outwardly
projecting rigid conduits secured to and communicating
with the other end portion of the housing member, re
bers by jet reaction, a ring gear mounted on said inner
housing coaxially therewith, a driven gear mounted on
said shaft concentrically with said ring gear, a plurality
spective jet combustion chambers mounted on the outer
ends of said conduits, said chambers having venturi air
for admitting air into said one end portion, inwardly
projecting baffle elements on said housing member ex
intake elements communicating with said conduits and
having air scoop portions at their forward ends com
municating with said venturi elements, fuel ignition means
of planetary gears disposed between and «gearingly con
necting said ring gear to said driven gear, whereby to
lrotate the output shaft in a direction opposite to the
direction of rotation of the inner housing, and means to
admit liquid `fuel into the space between the inner hous
ing and said rotor.
5. A rotary jet engine comprising a support, an output
in said jet combustion chambers, said jet combustion
chambers having exhaust conduits at their rear ends, said
chambers being positioned substantially normal to radii
of said output shaft, whereby to effect rotation of the
chambers by jet reaction, means gearingly coupling said
housing member to said output shaftfand being con
shaft journaled on said support, a rotor secured on said
output shaft and having outwardly projecting radial in
structed and arranged to rotate the output shaft in a di
rection opposite to the direction of rotation of the hous
ing member, and means to admit liquid fuel into said
one end portion of the housing member.
8. A rotary jet engine comprising a support, an output
clined compressor vanes, a generally cylindrical housing
member rotatably mounted on said shaft and having air
inlet means at one end portion Ifor admitting air into said
one end portion, inwardly projecting baille elements on
said housing member extending adjacent said vanes, out
wardly projecting rigid -conduits secured to and com
shaft journaled on said support, a rotor secured on said
output shaft and having a plurality of peripheral rows of
municating with the other end portion of the housing 25 outwardly projecting radial inclined compressor vanes,
member, respective jet combustion chambers mounted
Y a generally cylindrical housing member rotatably mount
ed on said shaft and surrounding said rotor, said housing
on the outer ends of said conduits, said chambers having
venturi air intake elements, fuel ignition means in said
member having air inlet means at one end portion thereof
.for admitting air into said one end portion, inwardly pro
jet combustion chambers, said jet combustion chambers
having exhaust conduit-s at their rear ends, said cham 30 jecting baiile elements on said housing member extending
between said peripheral rows of fvanes, outwardly project
bers being positioned substantially normal to radii of said
ing rigid conduits secured to and communicating with the
output shaft, whereby to effect rotation of the chambers
by jet reaction, means gearingly coupling said housing
’ other end portion of thehousing member, respective jet
member -to said output shaft, and means to admit liquid
combustion chambers mounted on the outer ends of said
3.5 conduits, said chambers having venturi air intake ele
ments communicating with said conduits and having air
6. A rotary jet engine comprising a support, an output
fuel into said one end portion of »the housing member. f
scoop portions at their forward ends communicating with
shaft journaled on said support, a rotor secured on said
said venturi elements, fuel ignition means -in said jet com
output shaft and having a plurality of peripheral rows of
bustion chambers, said jet combustion chambers having
outwardly projecting radial inclined compressor vanes,
a generally cylindrical housing member rotatably mount 40 exhaust conduits at their rear ends, said chambers being
ed on said shaft and having air inlet means at one end
portion for admitting air into said one end portion, in
wardly projecting baille elements on said housing mem~
positioned substantially normal to radii of said output
shaft, whereby to effect rotation of the chambers by jet
reaction, a driven gear mounted on the output shaft, a
ring gear mounted on the housing member concentrically
wardly projecting rigid -conduits secured to and communi 45 with said driven gear, a plurality of planetary gears dis
posed between and gearingly coupling the ring gear to
eating with the other end portion of the housing member,
the driven gear, whereby to rotate the output shaft in a
respective jet combustion chambers mounted on the outer
direction opposite to the direction of rotation of the hous
ends of said conduits, `said chambers hafving venturi air
ing member, and means to admit liquid fuel into said one
intake elements, fuel ignition means in said jet combus
tion chambers, said jet combustion chambers having ex~ 50 end portion ofthe housing member.
haust conduits at their rear ends, said chambers being
positioned substantially normal to radii of said output
References Cited in the file of this patent
shaft, whereby to effect rotation of the chambers by jet
UNITED STATES ~PATENTS
reaction, means gearingly coupling said housing member 55
to said output shaft, and means lto admit liquid fuel into
1,408,753
Long ________________ _.. Mar. 7, 1922
said one end portion of the housing member.
1,934,237
Russell ______________ _i- Nov. 7, 1933
l7. A rotary jet engine comprising a support, an out
2,680,949
IButler _______________ __ June 15, 1954
ber extending between the peripheral rows of vanes, out
put shaft journaled on said support, a rotor secured on
2,709,889
Mount ______________ __'- June 7, 1955
366,450
440,500
Great Britain _________ __ Mar. 3, 1932
Great Britain _________ __»- Jan. l, 1936
`said output shaft and having a plurality of peripheral rows
of outwardly projecting radial inclined compressor vanes, 60
a generally cylindrical housing member rotatably mount
ed on said shaft and surrounding said rotor, said housing
FOREIGN PATENTS
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