U.S. patent number 3,633,372 [Application Number 04/819,681] was granted by the patent office on 1972-01-11 for transfer of cryogenic liquids.
This patent grant is currently assigned to Parker-Hannifin Corporation. Invention is credited to Cleve C. Kimmel, John H. Moll.
United States Patent |
3,633,372 |
Kimmel , et al. |
January 11, 1972 |
TRANSFER OF CRYOGENIC LIQUIDS
Abstract
This invention relates to a system which permits the storage and
transfer of cryogenic fluids without losses due to handling and
venting and which is characterized by reversed-cascade filling
procedure. This system for transfer of a cryogenic liquid from a
supply container to a receiver is characterized in that only a
single fluid connection is made between the container and receiver
without venting the receiver so that the receiver-filling operation
may be achieved without gas or liquid loss by evaporation or
overflow as by the use of a submerged and continuously primed
pump.
Inventors: |
Kimmel; Cleve C. (Torrance,
CA), Moll; John H. (Hawthorne, CA) |
Assignee: |
Parker-Hannifin Corporation
(Cleveland, OH)
|
Family
ID: |
25228762 |
Appl.
No.: |
04/819,681 |
Filed: |
April 28, 1969 |
Current U.S.
Class: |
62/49.2;
62/50.1 |
Current CPC
Class: |
F17C
6/00 (20130101); F17C 2201/0109 (20130101); F17C
2227/04 (20130101); F17C 2250/061 (20130101); F17C
2223/047 (20130101); F17C 2205/0335 (20130101); F17C
2223/0161 (20130101); F17C 2227/0121 (20130101); F17C
2205/0323 (20130101); F17C 2205/0364 (20130101); F17C
2227/0393 (20130101); F17C 2227/0135 (20130101) |
Current International
Class: |
F17C
6/00 (20060101); F17c 007/02 () |
Field of
Search: |
;62/45,55,49 |
References Cited
[Referenced By]
U.S. Patent Documents
Primary Examiner: Davis, Jr.; Albert N.
Claims
We, therefore, particularly point out and distinctly claim as our
invention:
1. A system for transfer of a cryogenic liquid from a closed supply
container into a closed receiver adapted to contain residual liquid
therein at a temperature greater than that of the liquid in said
container; conduit means between said container and receiver
through which liquid from said supply container is introduced into
said receiver; means establishing a pressure differential between
said container and the vapor space of said receiver to effect flow
of liquid from said container into said receiver without venting of
the latter; and temperature control means in said conduit means
operative to maintain the vapor pressure at a predetermined level
in said receiver which is greater than the saturated vapor pressure
of the liquid in said container.
2. The system of claim 1 wherein said means establishing a pressure
differential comprises a pump in said conduit means to establish a
pressure differential for flow of liquid from said container into
said receiver.
3. The system of claim 1 wherein said means establishing a pressure
differential comprises a pump and drive means therefor; wherein
valve means between said supply container and the portion of said
conduit means downstream of said pump opens communication between
said supply container and receiver in response to vapor pressure in
the latter exceeding a predetermined value thus to decrease such
vapor pressure; and wherein a pressure actuated interlock energizes
said drive means in response to decrease of such vapor pressure to
predetermined value thus to drive said pump for flow of liquid from
said container into said receiver.
4. The system of claim 1 wherein said temperature control means
comprises a heat exchanger and a sensor unit therefor through which
liquid may be conducted to increase the saturated vapor pressure in
said receiver to predetermined level.
5. The system of claim 1 wherein said temperature control means
comprises a thermal sensor unit; a heat exchanger; and valve means
operative to divert a portion of the liquid flowing in said conduit
means through said heat exchanger for heating thereof and for
mixing of the heated liquid with the unheated portion of the
liquid; said sensor unit actuating said valve means upon decrease
of vapor pressure in said receiver below a predetermined value.
6. The system of claim 1 wherein said means establishing a pressure
differential comprises a heat exchanger through which a portion of
the liquid from said supply container is conducted and supplied
therefrom to the vapor space of said supply container thus to
effect flow of liquid from said supply container into said
receiver.
7. The system of claim 1 wherein said conduit means terminates in
spray means operative to break up liquid as it enters the vapor
space of said receiver.
8. The system of claim 1 wherein relief valve means exposed to
vapor pressure in said receiver relieves vapor pressure in said
receiver when it exceeds a maximum pressure greater than said
predetermined level.
9. The system of claim 2 wherein check valve means in said conduit
means downstream of said pump prevents reverse flow of liquid in
said conduit means from said receiver into said supply container.
Description
BACKGROUND OF THE INVENTION
Aircraft are now being equipped with inerting systems for fire and
explosion prevention and for fire extinguishment which comprise
dewars containing an inert cryogenic liquid such as N.sub.2 for
release into fuel tank or other spaces which may contain
combustible or explosive liquids or vapors. Accordingly, there is
presented the problem of periodic refilling of the aircraft
dewars.
In known transfer equipment, cryogenic liquid is transferred from a
supply container to a vented receiver thus resulting insubstantial
loss of liquid by evaporation and overflow. Various practices
sometimes provide complex transfer equipment such as an auxiliary
tank and pump between the supply containers and the receiver, a
vapor bleed-off mechanism, and several fluid interconnecting lines
to effect transfer.
SUMMARY OF THE INVENTION
Contrary to the foregoing, the transfer of cryogenic liquids herein
from a ground supply dewar to an aircraft dewar involves only the
connection of a flexible supply hose from the supply dewar to the
disconnect coupling of the aircraft dewar, the latter as aforesaid,
being the inert gas supply source for the aircraft inerting
system.
One object of the present invention is to provide for cryogenic
liquid transfer from a supply dewar to an aircraft dewar without
venting of the latter and without overflow, whereby there is no
evaporation loss of the liquid nor is there any possibility, in the
case of liquid N.sub.2, of erosive or other damage to concrete
pavement and the like due to overflow.
Another object of this invention is to provide for a transfer of
cryogenic liquids, such as N.sub.2, which entails the use of but a
single fluid line connection between the supply dewar and the
aircraft dewar, the supply dewar cart or trailer having the
necessary control equipment to obtain desired automatic filling of
the aircraft dewar with cryogenic liquid at predetermined saturated
vapor pressure and to predetermined level.
Another object of this invention is to provide for the transfer of
cryogenic liquids which utilizes a pump means between the supply
dewar and the aircraft dewar, and an intervening heat exchanger
which assures filling of the aircraft dewar to a predetermined
saturation level for most effective use in inerting the fuel tank
and other spaces of an aircraft.
Other objects and advantages of the present invention will become
apparent as the following description proceeds.
BRIEF DESCRIPTION OF THE DRAWING
FIG. 1 is a schematic drawing of a preferred embodiment of the
invention wherein an aircraft dewar is supplied with cryogenic
liquid from a portable supply dewar; and
FIG. 2 is a similar schematic drawing illustrating a modification
wherein a heat exchanger in an emergency application is substituted
for the pump means of FIG. 1 to discharge liquid from the supply
dewar.
DISCUSSION OF THE INVENTION
Referring to FIG. 1, the ground supply unit 1 may constitute a cart
or trailer which carries thereon a supply container 2, i.e., a
vacuum-insulated, double-wall dewar, a centrifugal pump 3, a heat
exchanger 4, valves 5, 6, and 7, a thermal sensor unit 8, and an
operating unit 9.
The outlet of the supply dewar 2 is connected to the inlet of pump
3 by conduit 10 and the outlet of said pump 3 is connected to the
disconnect coupling 11 by conduit 12 via the check valve 13, the
control valve 5, the mixing valve 7, and the thermal sensor unit 8.
A bypass conduit 14 has therein the heat exchanger 4 and the
control valve 6 whereby a portion of the pump discharge may be
heated as hereinafter described in detail.
The airplane 15 has therein an aircraft dewar 16 having an outlet
conduit 17 leading to the inerting system via a shutoff valve 18. A
filling conduit 19 leads from the disconnect coupling 11 to a spray
device 21 disposed within said dewar 16 and above the filling level
switch 23 which has its electrical lead 24 plugged into a socket
element 25 in the lead 26 of the operating unit 9. A relief valve
27 in conduit 19 is set to relieve vapor pressure in aircraft dewar
16 exceeding a predetermined maximum. When the dewar 16 is to be
filled a flexible hose 28, preferably of vacuum evacuated,
double-wall construction, is connected to the disconnect coupling
11.
In normal operation the saturated vapor pressure in the aircraft
dewar 16 operates at a predetermined level that is greater than the
saturated vapor pressure in the supply dewar 2. In the event that
the pressure in dewar 16 is higher than the predetermined level,
this pressure must be reduced.
To fill the dewar 16, the flexible hose 28 is connected to the
disconnect coupling 11 and the socket 25 is plugged into lead 24 of
the level switch 23. The operating unit 9 is then actuated to the
"fill" position to open control valve 5. If the pressure in the
aircraft dewar 16 is higher than predetermined, control valve 29 is
opened to allow the pressure to decrease. The operating unit 9 is
provided with a pressure-actuated interlock 30 arranged to turn on
the pump drive motor 31 when the pressure in the aircraft dewar 16
has reached the predetermined level, and when the pump 3 is driven
it draws liquid from the supply dewar 2 and pumps it through the
conduit 12, valves 5 and 7, thermal sensor unit 8, hose 28, and
conduit 19 into the vapor space of the aircraft dewar 16.
Initially, the conduit 12 and hose 28 between the supply dewar 2
and aircraft dewar 16 is somewhat warm and heat will be transferred
to the liquid as it flows to the dewar 16. This causes the gas
pressure in the space of the dewar 16 to start to increase at the
time that the pump 3 is started. However, this flow action is
followed by some liquid carried along with the gas and the two
phase mixture enters the dewar 16 through the spray device 21
whereby the amount of gas initially introduced is rechilled by the
cold walls of the dewar 16 and by the vapor therein.
The pressure increase at startup peaks out just below the relief
pressure of the relief valve 27 and at this point liquid droplets
start to enter the dewar 16 to cause a pressure collapse of the
vapor therein. The pressure decay continues and when it drops below
the predetermined saturated level as pressure or temperature sensed
by the thermal sensor unit 8, the latter is activated to position
the control valves 5 and 6 so that some of the liquid delivered by
the pump 3 is conducted through the heat exchanger 4, whereby the
heated liquid passes through the control valve 6 to mix in the
mixing valve 7 with the liquid passing through the other control
valve 5. The filling rate is preferably such that the thermal heat
gain in the liquid between the thermal sensor unit 8 and the dewar
16 is insignificant so that the sensor unit 8 constitutes a fairly
accurate measurement of temperature of the liquid flowing into the
dewar 16. Generally, the allowable range of saturation control of
the liquid is wide enough so that additional controls are not
required. However, should the range be relatively small such as,
say, 5 p.s.i., the thermal sensor unit 8 may be installed in or
adjacent the dewar 16 in which case, the signal to the control
valves 5 and 6 constitutes a signal indicating the precise
temperature in or adjacent the dewar 16.
When the level of the cryogenic liquid in the dewar reaches the
level switch 23, the indicating light 32 is turned on, and the pump
drive motor 31 is deenergized and the control valves 5 and 6 are
closed, whereby no further liquid is supplied from the supply dewar
2 to the aircraft dewar 16. At that time, the operating unit 9 may
be shifted from "fill" to "stop" and the electric plug-in and fluid
disconnect couplings 25 and 11 may be separated, and as evident,
the disconnect coupling 11 may be provided with self-sealing valve
units to prevent escape of vapor or liquid.
As shown in FIG. 2, if the ground supply unit 1 is not provided
with a pump 3, discharging pressure on the liquid in the supply
dewar 33 may be generated by opening solenoid valve 34 for flow of
liquid through a pressure build up coil 35 into the top of the
supply dewar 33 so that the increased vapor pressure on the liquid
constitutes a pump means for forcing the liquid through the common
discharge conduit 12. This method, of course, decreases the thermal
efficiencies of the system when used in continuous operation.
As evident from the foregoing, there is but a single fluid line
connection 28 between the ground supply cart 1 and the aircraft
dewar 16 through which the latter is filled to a predetermined
level as controlled by the level switch 23 and to predetermined
saturation level as determined by the thermal sensor unit 8 whereby
the saturated vapor pressure in the dewar 16 will be at a
predetermined magnitude.
When the aircraft dewar 16 has thus been filled, the supply hose 28
and electrical lead 26 may be disconnected from the aircraft 15 and
the aircraft is ready for takeoff. The pressurization of the fuel
by N.sub.2 and the supply of N.sub.2 for other uses on the aircraft
is not restricted or impaired by the servicing.
* * * * *