U.S. patent number 3,630,449 [Application Number 05/036,162] was granted by the patent office on 1971-12-28 for nozzle for rocket engine.
Invention is credited to Stanley D. Butler.
United States Patent |
3,630,449 |
Butler |
December 28, 1971 |
NOZZLE FOR ROCKET ENGINE
Abstract
An improved structure and method of making are provided for
cooling the conical nozzle of a rocket engine. The nozzle is
constituted of a number of curved segments welded together along
their side edges to form the cone member. In order to provide for
cooling the metal of each segment, the latter is laid as a flat
plate on the bed of a planing machine and by means of a
gang-cutting tool, grooves are cut in the plate across its entire
width. Thereafter a flat-facing sheet of metal is diffusion bonded
to the grooved plate to leave closed channels across the plate
composite. The plate is then curved to proper shape and the
abutting edges are welded together so as to leave channels
extending lengthwise of the member. These channels are made to
coincide with similar channels formed along the combustion chamber.
In the event of a jet engine powered by a mixture of gases, an
auxiliary conduit is taken from one of the gas supply lines and
forced through the channels for cooling purposes and finally
returned to the source of the gas.
Inventors: |
Butler; Stanley D. (Woodland
Hills, CA) |
Assignee: |
|
Family
ID: |
21887010 |
Appl.
No.: |
05/036,162 |
Filed: |
May 11, 1970 |
Current U.S.
Class: |
239/127.1;
239/132.3 |
Current CPC
Class: |
F02K
9/64 (20130101) |
Current International
Class: |
F02K
9/64 (20060101); F02K 9/00 (20060101); B64d
033/04 () |
Field of
Search: |
;239/132.3,132.5,127.1,127.3 |
References Cited
[Referenced By]
U.S. Patent Documents
Primary Examiner: King; Lloyd L.
Claims
What is claimed is:
1. An article of manufacture comprising a nozzle adapted to be
secured to the combustion chamber of a thrust propulsion engine
with the combustion chamber having coolant passageways
therethrough; said nozzle constituting a hollow circular member of
large diameter tapering down to a smaller diameter, said nozzle
being constituted of curved segments joined together at their edges
to form a peripherally complete conically shaped wall, said segment
consisting of two plates of metal bonded together along their faces
by diffused heat, with plates forming the outer surface of the
combustion chamber and having grooves extending through the wall
from the large diameter end to the small diameter end of the nozzle
and the other plate serving to form the inner surface of the
combustion chamber and to close the open side of the grooves to
complete the peripheries thereof to form passageways through the
nozzle, said passageways being of a size and are spaced apart to
match the coolant passageways of the combustion chamber at the
position where the nozzle and combustion chamber are secured
together.
Description
BACKGROUND OF THE INVENTION
It is necessary in a rocket engine to provide some form of cooling
means for the thrust chamber assembly. The cooling fluid which is
usually contained in a built-in jacket or a cooling coil
surrounding the wall of the combustion chamber and nozzle, usually
constitutes either the oxidizer or the fuel. The coolant is
returned to its original source so that the heat absorbed by the
coolant is not wasted but augments the initial energy content of
the propellant prior to injection.
Various structures have been proposed to provide the jacket or the
cooling coil. But, such structures are complicated, not only from
the manufacturing standpoint but also in the assembly of the
various parts. Moreover, the cooling means are not altogether
reliable in operation. Rocket engines run for short periods of time
and must develop their full power almost instantaneously so that
any malfunction of the cooling system which must also respond
immediately can be most detrimental, even causing the engine to
destroy itself by the tremendous heat developed within the
combustion chamber. The most vulnerable portion of the engine, from
the cooling standpoint, is the throat section of the nozzle which
is located at the place of the highest heat-transfer energy
intensity and is therefore the most difficult to cool. It is
therefore important that the coolant be given unrestricted access
to the nozzle and particularly to the throat section which
immediately precedes the nozzle.
SUMMARY OF THE INVENTION
An object of the invention is to provide an improved cooling system
for a rocket engine and, in particular, provide an improved nozzle
and its throat section.
Another object is to provide an improved nozzle for an aerospike
engine and in which its construction is such as to facilitate its
integration with the combustion chamber.
Another object is to improve the accessibility of all parts of the
engine, especially the nozzle and throat portions to the
coolant.
Another object is to provide an improved method of fabrication of
the cooling system including the nozzle and throat section of a
rocket engine. These objects are attained in brief, by employing a
cylindrical combustion chamber having channels which extend
longitudinally of the chamber and in employing complementary
segments of a nozzle with integral channels, the latter serving as
extensions of matching channels in the chamber. The channels in the
nozzle segments are obtained by milling out parallel grooves in a
flat sheet of metal and overlying the grooves with a separate metal
sheet. Thereafter, the two sheets of metal are joined by a
diffusion bond and after trimming and bending the metal composite
to shape, welding the edges of a number of the segments together to
form a nozzle in which the longitudinal channels conform precisely
to the longitudinal channels of the combustion chamber.
Other objects and features will be apparent as the specification is
perused in connection with the accompanying drawings, in which:
FIG. 1 represents a vertical section of an "aerospike" jet engine
provided with the improved nozzle but showing the parts of the fuel
supply and the cooling system in schematic form.
FIGS. 2, 3, and 4 are cross-sectional views taken through the
nozzle at the positions marked by section lines 2, 3, and 4
respectively in FIG. 1.
FIG. 5 represents a perspective view of the improved nozzle
attached at one end to a typical combustion chamber.
FIG. 6 shows the use of a gang-cutter milling machine for cutting
the initial grooves in the metal plate, which, when formed, become
a nozzle segment.
FIGS. 7, 8, 9 and 10 are views in perspective of the additional
operations performed to obtain the improved nozzle and parts
thereof.
FIG. 1 represents a longitudinal section but partly schematic of a
rocket engine, and in which the combustion chamber is designated
generally by the reference character "1." The nozzle is designated
by the general reference character "2." The chamber and nozzle are
joined by the inwardly curved throat section 3. The chamber
constitutes the combustion portion of the engine and is fed by the
combination of an oxidant e.g. liquid oxygen) and a fuel e.g.
hydrogen) in proper proportion, fed through the conduits 4, 5,
respectively. As seen in FIG. 5, the chamber is preferably
constructed of a number of elongated rectangularly shaped conduits
or hollow rods 6 (FIG. 2) made of relatively thin metal, the
conduits being pressed inwardly to a curvilinear "S" shape as
indicated at 3 to form a throat section. The conduits are
preferably formed by extrusion having a square configuration so as
to provide complete peripheral continuity, and can be bent to the
proper curvature in a forming machine without severe deformation of
the opening in each conduit. However, the latter could also be made
of a standard round-tubing e.g. of stainless steel formed to a
square shape. The upper ends of the conduits 6 are held in place by
a relatively thick end plate 7 and communicate with an enclosed
compartment 8 which extends around the plate. The pipes 4, 5 extend
through the plate 7 and, at one end, communicate with the interior
of the combustion chamber and, at the other end, make connection
respectively to a liquid oxidant and a source of fuel under
pressure. There is also a pipe or conduit 9 which is connected to
the pipe 5 at one end and at the other end communicates with the
annular compartment 8. The purpose of this conduit and the
compartment 8 will be explained hereinafter. The lower ends of the
parallel-arranged conduits 6, as indicated at 10, are held in
position by being received by certain matching channels formed
within the nozzle section 3.
CONSTRUCTION OF THE NOZZLE
The present invention pertains more especially to the construction
and method of making the improved nozzle with adequate provision
for cooling that particular structure. As shown in FIGS. 1 and 5,
the nozzle takes the form of a frustrum of a cone diverging
outwardly from the throat section 3 and terminating at the lower
end in a hollow circular enclosure 11. The complete structure is
made up of a plurality of segments as illustrated in FIG. 10 and
secured together at their edges. The nozzle is provided with a
series of equidistantly spaced channels extending lengthwise of the
segments for receiving the coolant. It will be noted that the
outward taper of the cone is straight throughout its length (except
for the presence of the circular enclosure 11) and such
construction lends itself to procuring passageways 12 within
straight paths over the entire length of the cone. These
passageways or channels are formed in the manner described
presently.
Referring to FIG. 6, the material of each segment 13 in flat form
is secured to the reciprocatory bed of a mill, generally indicated
at 14. A gang tool 15 with cutting edges set apart the distance
between the passageways is employed. The gang tool is carried by a
head 16 supported on the crossbeam 17 and can be moved across the
material by the handle 18. An electrical motor and the necessary
gearing and levers all of which are well known and not shown, are
contained in the base 19 to drive the bed 20 of the mill along its
roller bearing 21 in the cutting and return directions as indicated
by the double-headed arrow 22. The grooves 23, which eventually
constitute the channels or passageways 12, extend the full length
of the metal plate 13, which becomes a segment of the nozzle as
pointed out hereinafter. The latter is made of heavy machinable
metal such as stainless steel, capable of withstanding extremely
high temperature. The next step is to lay over the grooved surface
of the material 13 a flat metal plate 24, and then to secure the
facing plate to the grooved member by a well-known operation termed
"diffusion bond." Thus, the facing plate causes the grooves to be
closed along their length and the latter then becomes passageways
or channels for receiving a coolant, as will be described
hereinafter. The next step in the process of making the nozzle is
to trim the edges 25 of the composite member to conform to a
template by a suitable and well-known cutting machine. The plate is
then given the requisite curvilinear shape to constitute a nozzle
segment by being placed in a forming machine (not shown) of any
suitable and well-known type. Six, or any other desired number, of
these segments are fitted together at their longitudinal edges and
the abutting elements are welded to complete the nozzle.
Thereafter, the circular enclosure 11 is attached to the lower or
wide open end of the nozzle. The smaller diameter end of the nozzle
is then provided by machine with a large and fairly deep annular
recess 26 for receiving the integrated lower ends 10 of the
combustion chamber elements 6. The joint is suitably brazed as
indicated at 27. It is apparent that the spacing of the grooves
(FIG 6) which eventually form the coolant channel 12, must be
accurately determined so that, when the combustion chamber and
nozzle elements are fitted together at the recess 26, continuous
passageways are provided along the entire length of the chamber and
nozzle. A well-known split-filler block 28 is secured to the
outside surface of the throat region of the structure in order to
provide extra material at this position to dissipate the excess
heat. In addition, a number of metal-bracing bands indicated at 29
can also be employed to ensure that the multipart chamber and
nozzle elements are held rigidly in the circular direction. In
order to return the coolant from the circular enclosure 11 back to
its source of supply, an escape pipe 30 extends from said enclosure
to the pipe 5. The pipe 30 may be secured in any suitable manner to
several of the bracing rings 29 to thus add rigidity to the
structure as a whole. The escape pipe contains a one-way check
valve 31 of well-known type, which allows fluid to pass only in the
direction of the arrow.
OPERATION OF THE COOLING SYSTEM
When the oxidant and fuel are introduced into the combustion
chamber 1 through the pipes 4, 5 part of the fuel supply is
diverted and flows through the conduit 9 into the annular chamber
8. The latter connects with the upper ends of the chamber 1 and the
fuel is caused to flow through the passageways or channels 12 which
extend along the chamber, the throat and nozzle sections into the
circular compartment 11. The gas is then caused to flow through the
return conduit 30, past the check valve 31 into the pipe 5 where it
joins the mainstream of the fuel being ejected into the combustion
chamber. None of the fuel is lost through the circulatory system
and yet the passing gas serves to cool all the parts of the engine
including the throat and nozzle portions.
From the foregoing, it is evident that I have disclosed not only an
improved nozzle which effectively receives a coolant but also is
adapted to serve as accessory for a combustion chamber which is
cooled by the use of the fuel or the oxidant. In addition to the
improved nozzle as a structure, there is disclosed an effective
method of making the nozzle, assuring that the channels 12 are
equidistantly spaced from one another and the machine work for
producing the channels is kept at a minimum.
* * * * *