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Патент USA US3027728

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April 3, 1962
J. J. ROSE
3,027,718
HIGH VOLTAGE FLASHOVER PREVENTION SYSTEM
Filed Nov. 24, 1959
3 Sheets-Sheet 1
motiu
INVENTOR.
JOHN J. OSE
BYLUp-u'
AéNT
April 3, 1962
J. J. ROSE
’
3,027,718
HIGH VOLTAGE FLASHOVER PREVENTION SYSTEM
Filed Nov. 24, 1959
3 Sheets—Sheet 2
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April 3, 1962
J. J. ROSE
3,027,718
HIGH VOLTAGE FLASHOVER PREVENTION SYSTEM
Filed Nov. 24, 1959
s Sheets-Sheet a
20. .52:
INVENTOR.
JOHN
. ROSE
MORNEY
#1
AGE
Patent‘ 6
1
2
is located within the combustion chamber. A compositor
15 produces the high voltage which is applied to the ignite-r
3,027,718
VGLTAGE FLASHOVER PREVENTION
.
3,027,?18
Patented Apr. 3, 1962
plug 13 by means of shielded connector 16. The con
nector 16 is connected to the igniter plug in the manner
SYSTEM
John 3. Rose, 318 Deliwood Ave, Dayton, Ohio
Filed Nov. 24, 195%, Ser. No. 855,246
4 Ciaims. (Cl. all-39.82)
(Granted under Title 35, U.S. Code (1952), sec. 266)
shown in FIG. 3. An ignition unit 18, shownin FIG. 3,
is connected to terminal 17 of compositor 15. Reference
44 shows the path of the air from the compressor to the
plug and compositor. In the prior art, igniter plug of
The invention described herein may be manufactured
FIG. 2, a terminal 20, extends into terminal well 21 and
and used by or for the United States Government for 10 the terminal is electrically sealed by means of a silicon
governmental purposes without payment to me of any
rubber washer 22. This washer ?ts tightly around con
royalty thereon.
nector wire 23 and is urged against the top of the terminal
This invention relates to an improvement in high volt
insulator 25 and the terminal well 21 by means of a
age ignition systems that use an igniter plug and which are
washer 26 and spring 27 and thus electrically seals the
subjected to high temperature and high altitude condi 15 _ well. The ?ring gap 14 is across insulator 31 between
tions, such as exist in systems for turbojet engines.
electrodes 32 and 33. Electrode 33 consists of a portion
One object of the invention is to provide an ignition
of the outer casing of the igniter plug. The inner electrode
ystem for use at high temperature and high altitude which
32 is connected to the connector Wire 23 by means of
eliminates the problems of flashover at the terminal con
terminal means 34 and 35. The terminal at the composi
nections of the igniter plug.
20 tor is identical to that shown in the igniter plug of FIG. 2.
Another object is to provide an ignition system for
When systems of this type are used at high altitude and
use at high temperature and high altitude which make the
high temperature ?ashover occurs due to deterioration of
use of electrical seals unnecessary.
the silicon rubber Washer 22.
These and other objectswill be more fully understood
The terminals are modi?ed according to this invention
from the following detailed description taken with the 25 in the manner shown in FIG. 3 wherein parts like those
drawing wherein:
shown in FIG. 2 are given like reference numerals. A
FIG. 1 shows a turbojet engine with which the ignition
small opening '41 is cut in the outer casing of the igniter
system of the invention might be used.
plug in a portion of the plug which extends into the com
FIG. 2 shows a prior art plug which is used in high
pressor chamber 12. Gaskets 42 and 43 are cut in the
voltage, high altitude ignition systems.
manner shown at 48 in FIG. 4 to permit the pressure from
FIG. 3 shows an ignition system modi?ed according
the compressor to be applied to the terminal wells at
to this invention.
both ends of the connector 16, along the path shown by
FIG. 4 shows a modi?ed seal used with the device of
the dotted line 44. It can be seen that the length of gaps
FIG. 3.
'
45 at both ends of connector 16 are much greater than
The ionizing voltage for the igniter plug gap may at 35 the gap 46 so that with the pressure approximately equal
tain 25 kilovolts which presents a high altitude ?ashover
problem in the terminal well at both ends of the ignition
cable.
Presently the terminals are electrically sealed to pre
in all of these gaps, gap 46 will break down long before
gaps 45.
There is thus provided an ignition system for use at
high temperautre and high altitude which eliminates the
vent ?ashover, however, when temperatures exceeding 40 problem of ?ashover at the terminal connections.
500° F. are present, deterioration of the sealing materials
While one speci?c embodiment has been described in
permits flashovers to occur at high altitudes.
some detail it is obvious that numerous changes may be
According to Paschen’s law the sparkling potential of a
made without departing from the general principles and
gas is a function only of the product of the sparking
scope of the invention.
distance and the pressure of the gas, so that if the product 45
I claim:
of sparking distance and pressure for any gas remains
1. In a high voltage ignition system for a turbojet
constant, the sparking potential will remain constant. In
engine of the type having a compressor chamber and a
the igniter shown in FIG. 2 the sparking gap in the
combustion chamber wherein the ignition unit is con
terminal is about ten times the length of the ?ring gap.
nected to an igniter plug through a compositor unit and a
Thus, if the pressure is kept substantially the same in these
substantially sealed connection having terminal means at
gaps, the ?ring potential in the terminals will be about
the ends thereof adapted to engage terminal wells in the
ten times that in the ?ring gap and the ?ring gap will
compositor unit and igniter plug, the igniter plug having
break down ?rst. To attempt to prepressurize the system
an outer casing adapted to extend through the compression
would require the whole system to be hermetically sealed
chamber into the combustion chamber, comprising: an
55
which would be very costly if not impossible. According
opening in said outer casing in the rigion adapted to ex
to this invention a passageway is provided through the
tend through said compressor and a passageway from said
igniter plug wall which extends into the compressor air
discharge area so that pressure is supplied continuously
opening to said terminal wells to thereby maintain equali
zation of pressure within said terminal wells and said
and directly from the compressor to the terminal wells at
compressor chamber under substantially static ?ow condi—
both ends of ignition cable to maintain the pressure 60 tions.
2. In a high voltage ignition system for a turbojet
within the terminal wells approximately equal to that at
engine of the type having a compressor chamber and a
the ?ring gap. This not only eliminates ?ashover but
combustion chamber, comprising; an ignition unit, a com
also makes the use of electrical seals unnecessary which
simpli?es the system.
Referring more particularly to FIG. 1 of the drawing,
reference numeral 10 refers to a portion of a turbojet
engine having a combustion chamber 11. Air from the
compressor, not shown, flows through the compressor
chamber 12. An igniter plug 13 extends through the
compressor chamber 12 into the combustion chamber 11.
The ?ring gap 14, shown in greater detail in FIG. 2,
positor unit connected to said ignition unit, an igniter
plug, said compositor unit and said igniter plug each
having a terminal well of insulating material therein, a
shielded connection between said compositor unit and
said igniter plug, said shielded connection having terminal
means located within said terminal wells for connecting
70 said compositor unit to said igniter plug, said igniter plug
65
having an outer casing with a portion adapted to extend
through said compressor chamber into said combustion
8,027,718
%
A1%
chamber, an opening in said outer casing in the region
shielded connection between said compositor unit and
said igniter plug, said shielded connection having termi
adapted to extend through said compressor, and a passage
way from said opening to said terminal wells, to thereby
maintain the pressure within said terminal Wells sub
stantially equal to the pressure in said compressor cham
her.
3. An igniter plug for use in ‘a high voltage ignition
system of an engine of the type having a compressor
chamber and a combustion chamber, comprising; an
nal means located within said terminal wells for con
necting said compositor to said igniter plug, said igniter
plug having an outer casing with a portion adapted to
extend through said compressor chamber into said com
bustion chamber which serves as an outer electrode, an
inner electrode which together with said outer electrode
constitutes a ?ring gap, ceramic insulating spacer means
outer casing having a portion adapted to extend through 10 located between said outer electrode and said inner elec
said compressor chamber into said combustion chamber
trode, said insulating'means having said igniter plug
terminal well located at the end thereof opposite said
inner electrode, the depth of said wells being substantial
ly greater than the width of said ?ring gap, an opening
?ring gap, means for spacing said outer electrode from
said inner electrode to thereby provide a ?ring gap, a 15 in said outer casing in the region adapted to extend through
said compressor chamber, and a passageway from said
terminal well with a depth substantially greater than the
opening to said terminal wells, to thereby maintain the
width of said ?ring gap within said outer casing at the
pressure in said terminal Wells substantially equal to the
end remote from said ?ring gap, ‘an opening in said outer _
pressure in said ?ring gap.
casing in the region adapted to extend through said corn
which serves as an outer electrode, an inner electrode
which together with said outer electrode constitutes a
pressor chamber, and a passageway vfrom said opening to
said terminal well.
4. In a high voltage ignition system for a turbojet
engine of the type having a compressor chamber and a
combustion chamber, comprising; an ignition unit, a
compositor unit connected to said ignition unit, an igniter 25
plug, said compositor unit and said igniter plug each
having a terminal well of insulating material therein, a
References Cited in the ?le of this patent
UNITED STATES PATENTS
2,195,025
2,286,233
2,310,575
2,493,743
2,651,298
Couzinet ____________ __
Scott _______________ __
Cattaneo ____________ __
Benson _____________ __
Brinson _____________ __
Mar. 26,
June 16,
Feb. 9,
Jan. 10,
Sept. 8,
1940
1942
1943
1950
1953
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