U.S. patent number 3,864,908 [Application Number 05/363,725] was granted by the patent office on 1975-02-11 for dry insulated parts and method of manufacture.
Invention is credited to Paul G. LaHaye.
United States Patent |
3,864,908 |
LaHaye |
February 11, 1975 |
**Please see images for:
( Certificate of Correction ) ** |
Dry insulated parts and method of manufacture
Abstract
An engine component such as a cast iron engine exhaust manifold
having an outer irregular-shaped surface is covered with an
inorganic heat insulating layer preferably having a thermal
conductivity in the range of from about 0.01 BTU/hr/ft/.degree.F to
0.2 BTU/hr/ft/.degree.F. An encapsulating, cast metal layer is
formed over the insulating layer so that when hot fluids within the
manifold reach temperatures of up to 2,000.degree. F and higher,
the temperature at the outer case metal layer does not exceed
450.degree. F.
Inventors: |
LaHaye; Paul G. (South
Portland, ME) |
Family
ID: |
26950323 |
Appl.
No.: |
05/363,725 |
Filed: |
May 24, 1973 |
Related U.S. Patent Documents
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Application
Number |
Filing Date |
Patent Number |
Issue Date |
|
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264199 |
Jun 19, 1972 |
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Current U.S.
Class: |
60/272; 60/323;
138/149; 427/405; 428/34.5; 60/321; 138/109; 164/98; 428/34.1;
428/444 |
Current CPC
Class: |
F01N
13/102 (20130101); Y10T 428/1314 (20150115); F01N
2310/06 (20130101); Y10T 428/13 (20150115); Y10T
428/31656 (20150401) |
Current International
Class: |
F01N
7/10 (20060101); F01m 003/10 () |
Field of
Search: |
;117/71M,71R,138,94
;252/47T ;106/15FP,272 ;60/323,320,321,282 ;164/98,35 ;161/139
;29/527.5 ;138/149,142,145 ;23/111,277 |
References Cited
[Referenced By]
U.S. Patent Documents
Other References
United States Patent Office Classification Definitions for Class
117, pp. 117-122 c, October 1969..
|
Primary Examiner: Van Horn; Charles E.
Assistant Examiner: Ball; Michael W.
Attorney, Agent or Firm: Wolf, Greenfield & Sacks
Parent Case Text
RELATED APPLICATION
This application is a continuation-in-part of applicant's copending
patent application Ser. No. 264,199 filed June 19, 1972 now
abandoned.
Claims
I claim:
1. A cast metallic engine part
said part defining an outer irregularly shaped surface and being
formed of an iron-containing metal defining a fluid carrying
conduit therein uninterrupted by fluid seals,
an inorganic dry insulation layer overlying said outer surface and
having a thermal conductivity in the range of from about 0.01
BTU/hr/ft/.degree.F to 0.2 BTU/hr/ft/.degree.F, and a cast
metallic, protective encapsulating layer conforming to the shape of
and covering said insulating layer,
said cast encapsulating layer being formed of a metal having a high
thermal conductivity and selected from the group consisting
essentially of aluminum, magnesium and alloys of these metals,
said encapsulating layer having a surface temperature below about
450.degree. F at fluid temperatures within said part of from
500.degree. F to at least 2,000.degree. F,
said cast metallic encapsulating layer having a thermal coefficient
of expansion matched to the thermal coefficient of expansion of
said part so that over-all expansion of said part and metallic
encapsulating layer are closely parallel to each other over the
operating temperature range of said part.
2. An engine part in accordance with claim 1 wherein said part is
in the form of an engine exhaust manifold interconnected with an
engine exhaust gas passage and a supercharger,
said manifold having an inlet and an outlet,
said cast metallic encapsulating layer being sealed to said conduit
at said inlet and outlet.
3. An engine part in accordance with claim 1 wherein said
insulating layer thickness is from about 0.1 to 1.5 inch and said
metallic encapsulating layer has a thickness of from about
one-sixth to one-half inch.
4. An engine part in accordance with claim 1 wherein said cast
metallic encapsulating layer has a thermal coefficient of expansion
of from about 10 .times. 10.sup..sup.-6 to about 12 .times.
10.sup..sup.-6 in/in/.degree.F and said part has a thermal
coefficient of expansion of from about 6 .times. 10.sup..sup.-6 to
about 8 .times. 10.sup..sup.-6 in/in/.degree.F.
5. An engine part in accordance with claim 3 wherein said cast
metallic layer carries outwardly extending heat dissipating
fins.
6. An engine part in accordance with claim 5 wherein said cast
layer comprises material selected from the group consisting
essentially of aluminum and magnesium.
7. An engine part in accordance with claim 3 wherein said one seal
is formed by a convoluted metallic collar providing a long thin
heat restricting path.
Description
BACKGROUND OF THE INVENTION
Particularly in large engines such as marine diesel engines, the
high temperature of the exhaust manifold, located between the
engine exhaust gas passage and a supercharger as well as the
exhaust piping from the engine supercharger to atmosphere and for
non-supercharged engines from the engine to the atmosphere, is
known to cause problems. When flammable liquids or gases are
present, high temperatures at the external surface of the manifolds
can cause a fire or explosion hazard. Moreover, such high
temperatures can be a substantial safety hazard since engine
operators can be easily burned on accidental contact with the
manifolds.
The prior art has sought to alleviate this problem in most cases by
providing for various means for cooling the outside of the
manifold. Such means often include the use of a fluid jacket to
pass a cooling fluid around the manifold and thus reduce surface
temperatures. However, the use of cooling fluids adds to the space
and weight requirements of power packages due to the accessory
pumps, radiators and fluid supply means which also add to cost.
When manifolds and conduits are liquid cooled as between the engine
exhaust gas passageway such as the cylinder head and the
supercharger, hot exhaust gases passed to the supercharger are
reduced in temperature thus causing some drop in the energy
available to the supercharger thus reducing the power available to
supply the engine with air for combustion resulting in lower engine
power output per unit of engine displacement. When engine exhaust
gas is passed through a reactor located in the engine exhaust
manifold or piping as part of an emission reduction system, the gas
temperature entering the reactor influences the performance of the
reactor. Higher temperatures are desirable and the absence of a
cooling medium in the manifold provides such higher temperatures.
Engine power reduction can be substantial, for example as much as
2% or more when temperatures in the manifold are reduced to
850.degree. F from a normal temperature of about 1,100.degree. F.
The power loss can be reduced by merely leaving the manifold
uninsulated and uncooled but, here again, heat dissipation through
the exposed iron or steel surfaces of the manifold causes a
temperature loss and in addition, the safety problem is
substantially multiplied.
It is not a problem to merely insulate the manifolds as by the use
of organic or inorganic insulating layers. However, such layers
often become degraded by moisture or contaminated with hydrocarbons
normally present around an operating engine unless they are
protected. Such hydrocarbon gases and liquids tend to degrade the
insulation reducing its resistance to the flow of heat and can
cause fire hazards. Other means of encapsulating such as
fabricating covers by formed sheet metal have proven costly and
unsatisfactory in protecting the thermal insulation from mechanical
failures in handling of the sheet metal and manifold casting in
service, and in preventing permeation and degrading by hydrocarbons
as well as other liquids and gases.
SUMMARY OF THE INVENTION
It is an important object of this invention to provide a dry, heat
insulated engine part comprising a conduit for hot fluid flow,
which engine part is efficiently heat insulated with minimized cost
and complexity.
Another object of this invention is to provide an engine part
having a complex form in accordance with the preceding object which
can be manufactured without complicated procedures and in a highly
efficient manner with good reliability and with outstanding safety
features.
Still another object of this invention is to provide a method of
forming a dry, heat insulated engine part in accordance with the
preceding objects.
Additional objects of the invention are to provide external metal
encapsulation totally enclosing the thermal insulation to prevent
deterioration due to permeation of the thermal insulation by engine
room air borne contaminants and by contaminants accidently spilled
on the insulation.
According to the invention a dry, heat insulated metallic engine
part has a conduit therethrough allowing hot fluid flow as for
example in an engine exhaust manifold. The part defines an outer
irregularly-shaped surface with an inorganic insulating layer
overlying the surface and having a thermal conductivity preferably
in the range of from about 0.01 BTU/hr/ft/.degree.F to 0.2
BTU/hr/ft/.degree.F. A cast metallic, encapsulating layer conforms
to the shape of the insulating layer and covers the insulating
layer preferably encapsulating it. The engine part is designed to
have a surface temperature at the surface of the encapsulating
layer of below about 450.degree. F at fluid temperatures within the
conduit of from 500.degree. F to at least 2,000.degree. F when the
engine part is operated in normal atmospheric air environments with
air temperatures from 60.degree. to 150.degree. F.
In the preferred embodiment, the engine part is a cast iron or
steel engine exhaust manifold or conduit having a conventionally
irregular shape to suit the internal fluid flow and external
geometric constraints imposed by the over-all engine configuration.
The insulation conforms to the outer irregular configuration of the
manifold as does an overlying cast metallic encapsulating layer
preferably having a thickness of one-sixteenth to one-half inch
which provides mechanical protection and preferably hermetically
encapsulates the insulation through sealing of the outer metallic
layer to the engine part.
According to the method of this invention, an irregularly-shaped
member subject to operating temperatures in the range of from
500.degree. F to at least 2,000.degree. F, is insulated by forming
an inorganic self-supporting insulating layer over a surface of the
member with the insulating layer defining an outer irregular
configuration. A thin mechanically strong impervious metal casing
is then formed over the insulating layer and sealed to the member
to encapsulate the insulation by direct seals or through the use of
heat flow restricting joining means. It is important that the
method of this invention provide a cast outer metallic layer over
an irregularly shaped member which outer layer can be maintained at
a temperature below 450.degree. F regardless of the temperature of
the underlying engine part. In the preferred method, a transient
coating such as wax is placed over the insulation layer, a mold
conforming to the so insulated engine part is formed using the
engine part as a form, the transient layer is removed and the outer
metallic layer cast directly in the mold replacing the transient
layer over the insulation layer and engine part preferably at
temperatures high enough to form required hermetic seals with the
engine part thus encapsulating the insulation.
In some cases the outer metallic layer can be cast first and sealed
to the metallic engine part with an insulation layer later formed
to fill the space between the metallic part and the cast layer.
It is a feature of this invention that engine efficiency can be
substantially increased by maintaining the heat within a manifold
rather than dissipating any substantial portion of the heat to an
outside environment.
Another feature of the invention is its anti-pollution aspects when
used to maintain heat in a flowing gas which gas is later processed
in a reactor more efficiently since the heat is maintained to the
reactor inlet.
Still another feature of the invention relates to the safety
increase permitted by encapsulation of the insulating layer,
cooling of the outer surface and prevention of moisture or
hydrocarbon contamination of an insulating layer.
BRIEF DESCRIPTION OF THE DRAWINGS
The above and other features, objects and advantages of the present
invention will be better understood from the following
specification when read in conjunction with the accompanying
drawings in which:
FIG. 1 is a top perspective view of an insulated exhaust manifold
in accordance with a preferred embodiment of this invention;
FIG. 2 is a bottom view thereof;
FIG. 3 is a cross sectional view thereof taken through line 3--3 of
FIG. 2;
FIG. 4 is a top perspective view of an element thereof;
FIG. 5 is a diagrammatic showing of the manifold connected between
a supercharger and an engine;
FIG. 6 is a cross sectional view through line 6--6 of FIG. 2
showing a modified seal construction; and
FIG. 7 is a top view of the manifold before insulation is
applied.
DESCRIPTION OF PREFERRED EMBODIMENTS
With reference now to the drawings and more particularly FIGS. 1
and 5, a preferred embodiment of an engine part in the form of a
heat insulated engine exhaust manifold 10 is shown for mounting
between an engine block 11 and an engine supercharger 12 as
conventionally found in a marine diesel engine.
The manifold 10 comprises a conventional single or alloyed iron or
steel fabricated or cast part 13 (FIG. 7) in a substantially
conventional form having engine block rectangular mounting flanges
14, 15 and 16 preferably provided with bolt holes 17 and bolt
receiving notches 18 to allow the manifold to be attached to an
engine block. The manifold 10 receives hot fluid in the form of
combustion gases passing through inlet openings 20, 21, and 22
converging to a center passageway extending substantially from one
closed end to the other closed end of the manifold and from thence
through an outlet integral passageway opening at 23. Opening 23
carries an outwardly extending flange 24 with suitable bolt holes
24' for attachment to an engine supercharger. Hot gases from the
engine cylinders pass in the direction of arrows 25 out of the
opening 23 as known in the art.
The cast iron component 13 of the manifold 10 is of a conventional
irregular configuration. Overlying the outer configuration is an
insulating layer 31 formed of an inorganic material preferably
having a thermal conductivity in the range of from 0.01
BTU/hr/ft/.degree.F to 0.2 BTU/hr/ft/.degree.F. The thickness of
the insulation layer can be whatever is required to balance the
heat from the cast iron component of the manifold portions which
reaches substantially the temperature of the hot inside fluids or
gases to an outside manifold temperature, at the surface of a skin
casing 40, to maintain the surface at a level below 450.degree. F
and preferably lower for safety reasons. Insulation thicknesses of
from 0.1 inch to 1.5 inches are preferred. Inorganic insulating
materials such as Fiberfrax, a trademarked product of Carborundum
Corporation of Niagara Falls, N.Y., and comprising an aluminum
silicate, Min-K, a trademarked product of Union Carbide Corporation
of New York, N.Y., an aluminum oxide powder, foamed ceramic, sand,
refractory oxides, mixtures thereof and the like can be used for
the insulating material. It is necessary that the insulating
material not be degraded at the temperatures normally encountered
in engine operation or encountered in subsequent casting processes
of the outer metallic layer as will be described.
The insulating layer is preferably formed with a substantially
uniform thickness and preferably conforms to the outer
configuration of the cast iron component 13 of the manifold.
However, in some cases, it may be desirable to form the insulation
layer with nonuniform thicknesses and/or with an outer
configuration different than that of the outer configuration of the
cast iron component. For example, thicker sections of insulation
can be used at local points of high heat flux as at the turn in the
passageway illustrated in FIG. 3.
Preferably the insulating layer is directly adjacent the outer
surface of the cast iron component 13 with no voids present. Over
the insulating layer 31 is a thin metallic, outer skin casing layer
40 which is cast and which acts to provide mechanical protection
and encapsulation to the insulating layer. The cast layer 40 is
preferably formed of a good heat dissipating material such as
aluminum, aluminum alloys which melt at low enough temperatures for
casting and are non-destructive to the insulating layer. It is
preferred to use aluminum or magnesium or alloys thereof having a
thermal conductivity of at least about 50 BTU/hr/ft/.degree. F.
These materials serve to minimize local hot spots because of the
high thermal conductivity of the layer 40. Materials such as carbon
or alloy steel, cast iron and the like can also be used for the
casing 40. Thin coatings are preferred, preferably in the range of
from one-sixteenth to one-half inch. The layer 40 preferably has a
substantially uniform thickness and entirely surrounds and conforms
to the outer configuration of the insulating layer being bound
thereto at least because of the encircling nature of the layer to
the irregular configuration of the manifold.
In addition to the above considerations for selection of the metal
material of the outer skin layer 40, the material is preferably
designed to have a suitable coefficient of thermal expansion to the
coefficient of thermal expansion of the component 13 over the
expected operating temperature range of the component 13 and skin
40 so that the actual physical differential in expansion between
points on component 13 and between corresponding overlying points
on skin 40 is as close to equal as possible at operating
temperatures. Thus ideally for example, if the manifold 10 is to be
operated at a temperature of substantially 1,000.degree. F at the
component 13 and a resulting temperature of 400.degree. F at the
skin 40 the thermal expansion of part 13 at 1,000.degree. F is
preferably equal to the expansion of the skin 40 at 400.degree. F.
Although exact matching of differential expansion at the two
different operating temperatures is difficult to obtain, careful
selection of materials can result in only small acceptable
differences. For example, when the component 13 is formed of a
ferritic material such as cast iron, ordinary carbon steel or a
series 400 alloy steel having a thermal coefficient of expansion of
from 6 .times. 10.sup..sup.-6 in/in/.degree.F to 8 .times.
10.sup..sup.-6 in/in/.degree.F the skin material is preferably
selected to have a thermal coefficient of expansion of from 10
.times. 10.sup..sup.-6 in/in/.degree.F to 12 .times. 10.sup..sup.-6
in/in/.degree.F and thus could be a cast aluminum or an aluminum
alloy. In this case, the physical expansion of the skin is closely
parallel to the physical expansion of the inner ferritic part.
Assuming both the skin 40 and component 13 are both at 80.degree. F
and are then heated to their operating temperatures as described
above, the differential expansion from point to point for the inner
component 13 and the outer skin 40 would be determined by:
.DELTA.L.sub.1.sub.-2 = L[(.DELTA.T.sub.1) (E.sub.1) -
(.DELTA.T.sub.2) (E.sub.2) ]
where
.DELTA.L.sub.1.sub.-2 = differential in thermal expansion
L = linear distance between points over which thermal expansion
takes place
E = coefficient of thermal expansion for material
.DELTA.T = difference between starting temperature and operating
temperature
subscript 1 refers to the inner component 13 and 2 refers to the
encapsulating skin material.
In the case described above with 1,100.degree. F exhaust gas from
an engine the inner part 13 metal temperature would be
approximately 1,000.degree. F and the typical length for an exhaust
manifold would be 30 inches long, the inner part is iron and the
outer encapsulating skin material is aluminum so that:
.DELTA.L.sub.1.sub.-2 = 30 [(1,000-80) (6 .times. 10.sup..sup.-6) -
(400-80) (11 .times. 10.sup..sup.-6)]
differential expansion = .DELTA.L.sub.1.sub.-2 = 0.06 in
This difference in thermal expansion would be absorbed mechanically
by the system. It is preferred that .DELTA.L.sub.1.sub.-2 that is
the differential expansion be maintained in the range of from 0 to
0.10 inch. However, the value can vary depending on the specific
sizes of parts used. If the differences in expansion
characteristics are not matched, particularly with long length or
large diameter manifolds, they can cause destruction of the seals
used or physical rupture of the skin or other parts of the device.
In smaller manifolds, this feature is of lesser significance since
over-all physical expansion of parts is small.
Heat dissipating fins 30 are preferably integrally formed in the
layer 40. The fins improve natural convection to a surrounding
fluid environment such as air, to dissipate the small amount of
heat passing to the layer 40 through the insulation. The fins 30
have uniform fin heights of three-fourth inch with widths of
one-fourth inch and a fin to fin spacing of 1 inch although the
dimensions can vary as desired and in some cases the fins can be
eliminated.
In the case of an exhaust manifold, the joint between the outer
metallic layer 40 and the inner manifold 13 occurs at the flanges
which connect the manifold to the engine block and at the flange 24
which connects the manifold to the turbo supercharger. Since the
engine block is liquid cooled, the manifold connecting flanges are
only slightly hotter than the engine block to which they are
connected. Thus, at this location, there is not sufficient heat
flow from the manifold to the outer metallic layer to cause the
external temperature to exceed the objective of keeping it below
450.degree. F. At the other end, this is not the case. The
supercharger is not liquid cooled and the connecting end of the
manifold part 13 is at a high temperature. If it were directly
connected to the outer metallic layer, a large heat leak would
occur causing the outer metallic layer to exceed the desired
temperature. In cases such as this, a flexible thin walled metallic
seal is provided to restrict the flow of heat from the manifold to
the outer metallic layer.
The metallic layer 40 is preferably hermetically sealed to the cast
iron or stainless steel component of the manifold during the
casting operation as by joints shown at 50 in FIG. 6 where the
mounting flanges are overturned as shown, or by joints as shown in
FIG. 3 directly to part 13 adjacent the flanges. Such joints are
formed by contact of the molten outer layer with the part 13 during
the casting process as will be described. Such joints are
preferably made at the lower temperature or inlet end of the
manifold where there is no great heat dissipation in operation,
from the cast iron section of the manifold to the outer skin due to
the small area of contact and the cooler operating temperature of
this end of the manifold. At the outlet end 23 of the manifold,
where temperature of the manifold is highly elevated, it is
preferred to seal the outer metallic layer 40 to the inner cast
iron or stainless steel component 13 through a heat restricting
seal ring such as 51. The seal ring 51 is a convoluted
circumferentially extending enclosing collar with its inner
cylindrical surface 52 bonded to the cast iron component 13 of the
manifold as by welding or brazing and its outer cylindrical surface
53 sealed directly to the skin or outer metallic layer 40 during
casting procedure. The ring 51 is preferably formed of a low
thermal conductivity metal in a thin convoluted encircling shape.
For example, the ring can be formed of titanium or sheet steel
having a thickness of from 0.01 to 0.03 inch to restrict heat flow.
The ring is preferably resilient and can flex to allow for a small
differential in expansion between the encapsulating layer 40 and
the component 13 without destruction of the seal.
Because of the metallic mechanical properties of the outer skin 40,
it provides mechanical protection to the insulating layer. In
addition, it can be sealed as described above to prevent moisture,
hydrocarbons or other fluids from contaminating the insulating
layer as could otherwise be the case during normal operation of the
engine. By proper selection of materials and design of layer
thicknesses, it is possible to obtain any reasonable desired
temperature at the outer layer 40. For example, when the gas flow
in the manifold reaches temperatures of 900.degree. F, by the use
of the construction noted, the outer skin temperature can easily be
maintained below 350.degree. F.
In the preferred method of this invention, the manifold cast iron
component 13 is 24 inches from end to end having an outside
diameter of 5 inches with a roughly uniform wall thickness of
one-fourth inch. Component 13 is coated with an inorganic
insulating layer such as Fiberfrax as by applying it in
conventional castable form containing a binder. The cast insulation
is coated with a ceramic paint or other sealer known in the art to
seal the porous insulation preventing permeation by the later
applied molten metal.
The insulated part is then coated with a layer of a transient
material such as a hydrocarbon wax having a thickness of one-fourth
inch corresponding to the thickness desired for the outer metallic
layer to be cast thereover. Where fins are to be formed, they can
be carved in the wax. The so coated insulated part is then used as
a form and a conventional sand casting mold is formed thereover
conforming to the outer surface of the wax layer.
The temperature is raised to melt the wax and it runs out of the
casting mold. Preferably the temperature of the part 13 and the
mold is heated approximately to the melting temperature of aluminum
and molten aluminum then poured into the mold to form the cast
layer 40 bonded to the ring collar 51 and seals 50 during the
casting operation. The mold is then cooled at ambient temperatures
and the completed manifold 10 removed.
The above preferred method is basically the "lost wax" procedure
for forming castings as well-known in the art. Application of this
procedure to the specific materials and components noted has
significant advantages as pointed out above. Costs are lowered and
mechanically strong, advantageous results are obtained. However,
the cast coating 40 can be formed by several other methods. For
example, the insulation can be formed around the part 13 and a
metal outer coating provided by dipping in molten metal to build up
the desired thickness of metallic outer layer 40. In still another
procedure, a wooden pattern representing the external shape of the
outer layer 40 is formed and a split mold made of it. The part 13
is then coated with insulation and placed in the mold so formed.
The outer layer 40 is then cast around the insulation. This method
avoids the chance of contamination by wax. In all of these methods,
the use of the temperature of the molten metallic layer aids in
degassing the insulation and assuring removal of contaminants from
the insulation.
In still another method, a pattern can be made for the exterior
shape of the outer layer 40. A core is then made representing the
shape of the part 13 with its insulated coating. The aluminum or
other metallic layer 40 is then cast using the core in the mold
formed from the pattern. The mold is preferably a two-piece mold
allowing the layer 40 to be formed as a two-piece jacket which can
be opened and resealed around the part 13. The part 13 can then be
left with an air gap in place of the insulating layer or
alternatively, filled with a powdered insulation after sealing of
the layer 40 to the part 13. Preferably the space is evacuated of
moisture and other contaminants prior to filling through a fill
opening and then the opening is sealed to form the final
product.
While a specific embodiment of this invention has been shown and
described, it should be understood that many variations are
possible. For example, the engine part which is insulated by a dry
insulating material need not be a manifold but could be other parts
such as cylinder heads, liners, piping, casings and the like used
in marine engines, diesel engines, gas turbine engines, steam
generators and the like wherever the presence of unburned
hydrocarbons, moisture and the spillage of fuel and lubricating oil
could tend to contaminate thermal insulation not protected by a
sealing capsule.
The seals formed are preferably formed as at the collar or ring 51
and seals 50. Such seals when formed during the casting operation
unite parts 13 and 40 forming tight seals which restrict the flow
therethrough to a value small enough so that there is no problem
with whatever normally would pass through the seal. For example, if
normal capillary action forces at one atmosphere pressure
differential keep out contaminants, moisture and fluids, such a
seal is sufficient even though the seal may not be a hermetic
seal.
While the manifold part 13 is preferably cast iron or steel as
conventionally used, other metallic parts can be insulated in
accordance with this invention. The configurations of these parts
are normally irregular in that geometrical, cylindrical, square or
the like shapes are not present but irregular shapes are present in
accordance with required engine specifications and the like. Thus,
to form outer layers 40 by machining, sheet metal forming and
conventional fabricating techniques, would involve high expense.
However, the casting procedure of this invention enables low cost
formation of the required parts with the required encapsulated
insulation.
* * * * *