close

Вход

Забыли?

вход по аккаунту

?

код для вставки
@cà 8, M46.,
f
R. H. GODDARD
FEEDING DEVICE FOR COMBUSTION CHAMBERS
Filed ' OC‘L.' l2, 1942
2,409,036
2,409,036
Patented Oct. 8, 194i@
UNITED STATES PATENT OFFICE
2,409,036
FEEDING DEVICE FOR COMBUSTION y
CHAMBERS
Robert H. Goddard, Roswell, N. Mex., assignerv of
one-halfA to The.v Daniel andFlorence Guggen
heim Foundation, New York, N. Y., a corpora
tion of NewYork
Application October-:12, 1942, SerialNo. 461,670l
5 Claims. (Cl. 1.58--36)
l
This invention relates to feeding devices par
ticularly adapted for use in rocket motors in
which~ discharge gases are continuously produced
in a combustion chamber and are continuously
ejected through a rearwardly directed nozzle,
lThe operating conditions in such rocket mo
tors are very different from those encountered
in oil-burning or gas-burning furnaces. In such
furnaces, the combustion space is relatively
large and the rate of fuel feed is relatively slow.
In a rocket motor, most commonly used in air
craft, it is necessary to avoid excessive weight
and the motor must be relatively small, with a
combustion chamber of limited capacity and to
2
Fig. 1 is a sectional front elevationcff apre
ferred construction of feedingî mechanism;
_
Fig. 2 is a partial perspective View of» an an
nular stationary member forming- part. of thel
mechanism shown in Fig. l ;
Fig. 3 is a. similar view of an annular rotat
ing member used in the preferred construction.;
Fig. 4 is .a partial perspective View similar to
Fig. 2 but showing a modification- to be> de
scribed; and
Fig. 5 is a diagrammatic view illustratingv the
shiftingl of the locus of impact of the two liq
uids under certain operating conditions’.
In Figs. 1 to 3 I have shown a modified con
struction in which concentric and stationary
annular' casing members 60- and 8! are fixed in
rapid rate.
.
the upper end portion 62A of the combustion
In order to secure a large power output from
chamber of a rocket motor. A» feed pipe 63» for
such a, relatively small power unit, it is desir
liquid- oxygen is connected to the fixed outer
able to use a mixture of. gasoline or other liquid
fuel and a liquid oxidizing agent such, as liquid 20 casing 68, and a feed pipe 84 for liquid `fuel is
connected to the fixed inner casing lil. At their
oxygen, but a mixture of such liquids is very
which fuel and an oxidizing agent> are fed at a
explosive, and the ignition of any considerable
amount of such a mixture produces violent and
dangerous combustion.
It is the general object of my present inven
tion to provide effective combustion for such a
mixture of gasoline and liquid oxygen and also
lower-ends, theîcasings 68 and 8l are-beveled at
their inner and outer edges, as> indicated at 85.
and. Bßin Fig. 2 and at 6l and 88 in Fig. l.
The beveledÍ inner surface 85> of the fixed outer
casing 68 is provided with a series of elongated
circumferential slots 18, preferably arranged in
staggered relation as best shown in Fig. 2. The
to reduce the violence of the combustion reac-A
beveled outer surface 88 of the fixed inner
tion Without reducing the power output of the
apparatus. I also maintain substantially con 30 casing 6| is provided with aV similar series of
slots 'Il (Fig. l).
tinuous. discharge of combustion gases from the
A rotating annular member 'l5 is mounted
discharge nozzle.
within the outer fixed annular casing 64), anda
To the accomplishment of these objects, I
corresponding. rotating annular member 16- is
provide means for rapidly and periodically vary
ing the feed of one or both liquids to they com 35 mounted within the inner fixed annular cas
ingßl.
bustion chamber, so that combustion takes place
The rotating annular member 'l5 is mounted
in a rapid succession of relatively small explo
at
its upper end on balls 'i8 on a fixed ball race'y
sions, with the combustion gases produced in
7.9,/ and at its lower end said member is pro
a series of closely successive waves. These waves
follow each other so rapidly that they inter 40 vided with beveled inner and outerv edge sur
faces 88 and 8| (Fig. 3), slidably engaging the
mingle in the combustion chamber and produce
corresponding.. surfacesl 65- and 66 of the associ
a substantially continuous and uniform flow of
ated fixed annular casing 88. The inner surface
combustion gases through the discharge nozzle.
80 is provided with` a series of staggered slots
A more specific object of my inventionl is to
provide means for periodically interrupting. the 45 82, arranged to coact with the slots 18.
The rotating annular member 15 is of similar
flow of each liquid and for more effectively mix
construction and, is similarly mounted on balls
ing the gasoline and liquid oxygen. I also pro
8% on a fixed ball race 85 in the fixed casingiil.
vide means for independently varying the inter
Similar beveled surfaces are provided at the
vals between feeding occurrences for each liquid.
My invention further relates to arrangements 50 lower end of the rotating member 16, and one
of these surfaces has staggered slots 88. It will
and combinations of parts which will be herein
be noted that the slots 10 and 82 of the coact
after described and more particularly pointed
ing annular members 80 and 15 are directed in
out in the appended claims.
ward, While the slots 1l and 88 of the coact
Preferred forms of the invention are shown
ing members 6l and 16 are directed outward.
in the drawing, in which
2,409,036
4
The rotating annular member 15 has a rotor
ring 90 (Fig. 1) of copper or aluminum, coact
ing with a. stator 9| to form an induction motor,
and the inner rotating annular member 16 has
Y, but the net open slot area will remain approxi
mately the same and the flow through the pipes
63 and 64 will be substantially uniform.
It is desirable that the frequency of the m0
a. similar rotor ring 92 coacting with a stator 93.
tors be such as to produce periodic waves corre
sponding to'the dimensions of the combustion
chamber. These waves may travel either longi
As the movable slots are rotated and inter
mittently brought into alignment; with the fixed
. slots, jets or slugs of liquid fuel and liquid oxy
gen will be fed to the combustion chamber
along intersecting paths as indicated in Fig. 1, 10
so that an intimate mixture of the two liquids
is quickly attained. This construction has the
advantage of delivering both liquids from ex
tudinally of the chamber or may expand toward
the cylindrical chamber wall.
It will be understood that my improved feed
ing mechanism, while particularly designed for
use with liquids, also possesses similar utility when
used with gases.
Having thus described my invention and the ad
site directions, thus providing a very thoroughly 15 vantages thereof, I do not wish to .be limited to
intermingled combustion mixture.
the details herein disclosed, otherwise than as
Different explosive effects may be obtained by
set forth in the claims, but what I claim is:
varying the relative speed of the rotating an
l. .Feeding mechanism for a combustion cham
nular members 'l5 and 16, which varying speeds
ber in a rocket motor comprising separate means
may be attained by varying the frequencies of
to feed liquid fuel and a liquid oxidizing agent
the induction motors.
to said chamber, and means to quickly and suc
In Fig. 4 I have shown a portion of an annu
cessively interrupt the feed of :both of said liq
lar casing lill*i having slots 'l0a arranged in a
uids as they enter said chamber and to simulta
somewhat different and less staggered rela
neously shift the locus of delivery of said liquids.
tion. With this construction and with a similar
2. Feeding mechanism for a `combustion cham
arrangement of slots in the associated rotating
ber in a rocket motor comprising concentric fixed
member, the feed will be more definitely inter
annular casings mounted on said combustion
tended coaxial annular passages and in oppo
mittent while the arrangement previously de
chamber and projecting therein and having slots
scribed shifts the admission area up and down
in their lower end portions, means to feed fluid
between the upper and lower rows of slots.
30 fuel and a fluid oxidizing agent to said concentric
All forms of my invention as above described
fixed casings, rotatable annular members mount
thus provide very simple and effective means for
ed within said fixed casings and having slots in
periodically feeding liquids to a combustion
their lower end portions coacting with said first
chamber in separated portions, so that the com
named slots to provide fluid passages when
bustion, while substantially continuous, neverthe 35 aligned therewith, and means to rotate said annu
less takes place at slightly spaced intervals. The
intervals are, however, too short to completely
extinguish the flame. Dangerous explosions of
large amounts of the combustion mixture are thus
lar members.
.
3. The combination in a feeding mechanism as
set forth in claim 2, in which the fluid passages
of the outer pair of ñxed and rotating annular
avoided.
40 members are directed toward the axis of said ro
By changing the relative locations of the ad
tating members and the fluid passages in the in
mission slots in the construction shown in Fig. 1
ner pair of fixed and rotating annular members
and as illustrated in Figs. 2 and 4, both the ad
are directed away from said axis.
mission timing and the admission locus may be
4. Feeding mechanism for a combustion cham
varied. By varying the frequencies, further var
ber in a rocket motor comprising concentric fixed
iations in feed and proportionate mixture may
annular casings mounted on said combustion
be obtained.
chamber and projecting therein and having slots
'I'he change in locus of admission and impact
in their lower end portions, means to feed fluid
of the two liquids, when using the stationary an
fuel and a fluid oxidizing agent to said concentric
nular casing (il)a (Fig. 4) with the rotating mem 50 fixed casings, rotatable annular members mount
ber l5 and a corresponding stationary casing 6|a
ed within said fixed casings and having slots in
with the inner rotating member 16, is illustrated
their lower end portions coacting with said first
diagrammatically in Fig. 5.
named slots to provide fluid passages when
It is assumed that the stationary casings and
aligned therewith, and each rotatable member
rotating members are so disposed angularly that
having a ring of conductive metal and constitut
a lower slot 'llla in the casing Sl'la will be opened
ing the rotor of an induction motor by which said
simultaneously with an upper slot 1 Ib in the cas
member is rotated.
.
ing Sla, and that an upper slot 10b in the casing
5. Feeding mechanism for a combustion cham
60a will :be opened simultaneously with a lower
ber in a rocket motor comprising separate means
slot 'Ha in the casing 6in.
60 to feed liquid fuel and a liquid oxidizing agent
With the slot ‘Illa and ‘Ilb open, the impact of
to said chamber, and rapidly rotated valve ele
the jets or sprays will occur at the locus X, while
ments effective to shift the locus of delivery of
with the slots 10b and 'Ha open, the impact will
both of said liquids to said chamber and of im
occur at the locus Y. As one pair of slots is
pact of said liquids Within said chamber succes
gradually closed and the other pair of slots is
sively and repeatedly during each rotation of
simultaneously and gradually opened, the locus
said elements.
of impact will shift back and forth between X and
ROBERT H. GODDARD.
Документ
Категория
Без категории
Просмотров
0
Размер файла
351 Кб
Теги
1/--страниц
Пожаловаться на содержимое документа