US1653603A

US1653603A - Airship

Info

Publication number: US1653603A
Application number: US113615A
Authority: US
Inventors: Schroder Paul
Original assignee: EXCAELUM CORP
Current assignee: EXCAELUM Corp
Priority date: 1926-06-04
Filing date: 1926-06-04
Publication date: 1927-12-20
Anticipated expiration: 1944-12-20

Description

Dec. 0 1927. v

. v P. scHROuER AIRSHII' Filed June 1925 3 Sheets-Sheet 1 Pitts go t offered to the wind Parts offered to the wind.

condensed water.

warm liquid.

r" Se "a 0 Vw r. elf M .Aa Tu lnb or Dec. 20, 1927. 1,653,603

1?. SCHRODER nasal? .Fi June 4., 1926 3 Sheets-Sheet Q 42 ATraw/EY Dc. 2O 1927. 1,653,603

9. SCHRODER AIRSBIP Filed June 4, 1926 3 Sheets-Sheet 3 warm liquid Parts offered. to the wmd.

Patented Dec. 20, 1927.

UNITED STATES 1,653,603 PATENT OFFICE.

RAUL scHRonRR, or STUTTGART, GERMANY, ASSIGNOR 'JJO EXCAELUMI coRPoRA'rIoN,

- A CORPORATION on NEW YORK.

AIRSHIP.

Application filed June 4,

The present invention relates broadly to lightcr-than-air air-ships and more especially to apparatus and the method for conserving water in the exhaust gases of the motors and using such water for ballast or other desired uses.

Lighter-than-air airships are usually propelled by hydrocarbon engines, and large sized ships carry a substantial supply of fuel. This fuel is transformed by the engines from a liquid to a gas, while the ship is in flight, and this gas when dissipated to the atmosphere causes the load of the ship to become lighter in weight as the fuel is consumed. This results in the ship rising to undesired heights and necessitates valving of the buoyant gases, particularly when a landing is to be made.

It has been proposed to condense the water in the exhaust engine gases by subjecting the gas carrying conduits to the air around the airship, to cool the hot exhaust gases. This prior known method possesses such disadvantages as to render the same impracticable. The conduits or pipes carrying the exhaust gases are according to the prior art subjected to very great variations in temperature tending to cause bursting of the pipes and loosening of the joints. Furthermore, the cooling of the sides of the hot col umn of gas passing through these pipes cause aneddying action which throws the soot in the exhaust gases outwardly and quickly coats the pipes with a heat insulating coating that tends to clog the pipes, increases the fire hazard, and decreases the heat transferring possibilities, thereby decreasing the efiectiveness of the cooling arrangements. Furthermore, this prior system requires very large areas to be brought in contact with the surrounding air and therefore great head resistance is added which otherwise would not exist. Such prior art systems therefore greatly decrease the effective speed of the airship.

The present invention comprises the method and apparatus for effectually condensing the water in the exhaust gases from hydrocarbon engines used to drive the airship, by means of maintaining the large hot exhaust gas conduits inside of stream line portions of the airship and then utilizing a heat transfer fluid circulating through cooling pipes within the exhaust gas conduits,

1926. Serial No. 113,615.

and leading this cooling fluid from these pipes to relatively small radiators mounted in such manner as to be-exposed to the air surrounding the ship. This method and apparatus facilitates causing the exhaust gases to pass through a grid of cooling pipes, of small diameter within the air ship, filled with a fluid capable of receiving and transferring heatunits from the hot exhaust gases without subjecting the cooling pipes to great variations in temperature. Furthermore, the use of radiators for this fluid, which may comprise water, may be of a more eflicient design than is possible where it is attempted tocool the large volume exhaust gas by running the same through a neces sarily large radiator.

It is realized that the present invention may be carried out by methods and ap aratus other than those herewith speci cally disclosed and therefore it is to be understood that the disclosure herewith is to be considered as diagrammatic and not in a limiting sense.

Fig. 1 is a diagrammatic plan View of a simple form of apparatus for carrying out the present invention.

Fig. 2 is a diagrammatic plan view of another form of apparatus showing multi-stage cooling apparatus for carrying out the invention.

Fig. 3 is a diagrammatic elevational View on line AB of Fig. 2.

Fig. 4: is a diagrammatic plan view illustrating a construction in which the exhaust gases are subjected to a preliminary cooling water bath and are further cooled by a con denser, both of which are cooled by suitable radiators.

Fig. 5 is a diagrammatic elevational view taken on line C-D of the exhaust conduit illustrated in Fig. 4.

Fig. 6 is a plan view of a diagrammatic arrangement of a further development of the present invention in which the exhaust gases are subjected to multiple cooling stages and in which closed condensers are employed for cooling the exhaust gases and the condensed water is carried away after each cooling stage.

Fig. 7 is an elevational view of exhaust conduit taken on the line E--F of Fig. 6.

Referring now more especially to Fig. 1

which diagrammatically illustrates one form of carrying out the present invention, the exhaust conduit 1 is of relatively large size to carry away the large volume of gases produced by such hydrocarbon engines as are adapted for airship propulsion. -A condenser member comprising a plurality of condenser tubes 2, connected with suitable headers 4, are mounted within the exhaust conduit 1 in such manner as to provide ample space for the passage of exhaust gases between and through the condenser pipes. The headers 4 are connected by suitable carrying pipes 6 and 7 to a radiator 8 located outside of the airship body and constructed in such manner as to dissipate heat to the air surrounding the ship. The pipe 7 may be provided with a pump 9 in order to facilitate the circulation of the cooling fluid, which may be water. The parts of the system other than the radiator 8 are all located within the airship proper in such manner as to be protected from the outside air through which the ship moves, so that these parts are not subjected to great variations in temperature, nor do they increase the head resistance of the ship. The construction of the condenser pipes across the exhaust conduit does not encourage the formation or deposit of soot, for the reason that the passage of the exhaust gases directly across these tubes tend to keep the tubes clean, and thesoot which drops from the tubes is carried away by the condensed water which falls into the trap 11 and is transferred to ballast tanks or other storage vessels which may be emptied and cleaned at the end of the voyage. The construction disclosed in Fig. 1 is a very simple diagrammatic illustration of the present invention as applied to small airships or to airships operating in a relatively moist climate where the air itself carries a considerable content of moisture, so that the condensation of the water in the exhaust gases need not be as full and complete as may be required with larger ships operating in a dry atmosphere.

Referring now more especially to Figs. 2 and 8, which show diagrammatically a further development of my invention, the exhaust conduit 21 is crossed by a multi-stage cooling apparatus comprising the preliminary condenser 22 connected with a radiator 24 exposed to the Wind in such manner as to dissipate the heat transferred to the condenser 22. Back of the condenser '22 is the second condenser 25 which is similarly connected to a second radiator 26 also exposed to the wind. The first condenser will remove a portion of the heat units from the exhaust gases and the second condenser will remove still more of the heat units. A water trough 27 may be arranged across the exhaust conduit beyond the condensers in such manner that the exhaust gases by their movement through the conduit 21 will Carry along globules of condensed water which will fall into the trough 27 from which the condensed water may be drained through thepipe 28 to suitable ballast tanks. .Where desired,

pumps

29 and 30 may be provided in the preliminary and in the final cooling systems respectively; and also the pump 31 may be utilized in the drain pipe 28.

In Figs. 4 and 5 that diagrammatically show a further development of my invention, the exhaust conduit 101 is provided with a water reservoir 102 in such manner that the exhaust gases pass over a 001 of cooling water which water is carried y suitable pipes 104 and 105 to air exposed radiator 106. Condenser pipes 107 are constructed to cross the exhaust conduit 101 in such manner that the exhaust gases must pass over and around the condenser pipes after having passed the open reservoir. These condenser pipes are also connected by

suitable carrying pipes

108 and 109, to a radiator 110, also exposed to the air outside the airship. A second reservoir 111 is provided in the exhaust conduit 101 and preferably is connected by an equalizer pipe 112 with the reservoir 102. The hot exhaust gases, while being cooled by the water in reservoir 102, vaporize some of the water so that the gases tend to be very humid when they strike cooling tubes 107. This is desirable because it will cause a maximum amount of condensation on the cooling tubes with the result that the tubes will be drenched and soot deposits effectively washed off. The condensate may run both to reservoir 102 and reservoir 111. The second reservoir 111 will usually receive the larger amount of the water condensed from the exhaust gases and by means of the pipe 112 will maintain the reservoir 102 properly filled. Preferably, an outlet pipe 114 leads from the reservoir 111 to storage tanks for the condensed water. Suitable pumps 115 'and 116 may be provided to circulate the Water in the cooling systems and a pump 117 may be used to withdraw the water of condensation and transfer the same to the ballast tanks or other storage tanks as may be desired. The upwardly inclined portion of the exhaust conduit leading from the second reservoir 111 may be provided with staggered bafile plates 118 which present a relatively large area to receive and collect water particles which may be carried along with the exhaust gases after leaving the cooling zones and such condensed water will drain back into the reservoir 111. The construction disclosed in Figs. 4 and 5 comprises an open cooling system including in its arrangement the

open water reservoirs

102 and 111 connected by suitable pipes with an air cooled radiator; and a closed cooling system comprising the condenser tubes 107, also connected through suitable pipes to its air 1 carried along by the cooled radiator. In this type of device, the open water reservoirs tend to collect and carry away the soot and heavy part1cles from the exhaust gases and to provide a preliminary cooling means for these gases. The condenser tubes comprise the main cooling system and the baflie plates the final water collecting medium. Thls system is well adapted for larger airships and in this system, as in the one shown in Figs. 1 and 2, the only part of the system exposed to the free air around the airship are the radiators 106 and 110, all the other parts being properly housed within the a1rsh1p structure.

The construction diagrammatically disclosed in Figs. 6 and 7 comprises a construction in which the exhaust gases are subjected to a preliminary cooling, then pass over an open reservoir of condensed water, and then through the final cooling devices and over another reservoir, and finally are subjected to battle plates which catch any freely suspended globules of water being exhaust gases.

Referring more particularly to the drawings, Figures 6, and 7, the exhaust condu t 201 preferably leads downwardly and is crossed by condenser tubes 202 comprising the preliminary condensing or cooling unit. These tubes 202 are connected by

suitable pipes

204 and 205, with the radiator 206 which is exposed to the free air around the airship. A second and final cooling device comprises the condenser tubes 207 connected by pipes. 208 and 209, to an exposed radiator 210. Both of these condenser systems are closed circuits and may be provided with

suitable pumps

211 and 212, for circulating the cooling liquid as is desired. Open reservoirs 214C and 215 may be arranged on each side of the final condenser and preferably are connected by communicating pipe 216. These reservoirs are adapted to receive the condensed water, which may be carried away by a pipe 217 to suitable ballast or other tanks. The flow through pipe 217 may be controlled by a pump 218. Preferably, the exhaust conduit in its final portion is provided with baflie plates 219, which are adapted to present a relatively large area to collect globules of moisture bein carried along by the exhaust gases in t eir tortuous path through these bafiie plates.

From the foregoing, it will appear that my invention contemplates arranging the large exhaust conduits Within the airship, and the utilization of a heat transferring fluid connected with radiators mounted outside the airship to dissipate heat into the atmosphere. The heat is taken away from the main body of the exhaust gases, and the exhaust conduits cool gradually as the gases are cooled without great heat variations, therefore, these large conduits are not undul stressed. Furthermore, any soot carrie by the exhaust gases is floated away by the condensed water without choking or clogginv the conduits for the exhaust gases.

IIaving described my invention, what I claim is 1. In an airship propelled by an internal combustion engine, an exhaust conduit within the airship for the exhaust gases, means for abstracting the heat from said gases and transferring the heat to the outside of said airship to dissipate the same into the surrounding atmosphere, water collecting means comprislng an open pan over which the exhaust gases flow, and storage means to collect and receive the water condensed by the cooling of the exhaust gases.

2. In an airship propelled by internal combustion engines, an exhaust conduit, preliminary cooling means comprising an open water pan and final cooling means comprising condenser. tubes, both of said means being adapted to transfer the heat of exhaust gases within said conduit to radiators lo cated in the atmosphere outside of said airship, and storage means to store the water recovered by the cooling of said gases.

3. The method of cooling the hot exhaust gas from an internal combustion engine driving an airship, comprising flowing the hot gas directly over the exposed surface of a cooling liquidwithin the airship, transferring said liquid to the exterior of the airship and there dissipating the heat to the outside atmosphere.

4. The method of cooling the hot exhaust as from an internal combustion engine driving an airship, comprising flowing the hot gas over a cooling medium comprising an open pool of water within the airship, transferring a portion of said water to the exterior of the airship and there dissipating the heat from said water to the outside atmosphere.

5. The method of condensing the moisture in the hot exhaust gases from an internal combustion engine propelling an airship, comprising passing the hot exhaust gases at least mediately over a constantly liquid cooling fluid, cooling said liquid at a point outside the airship, and collecting and storing the water condensed by the cooling of the hot gases.

6. In an airship propelled by at least one internal combustion engine, a radiator outside of the airship, a constantly liquid cooling fluid, means to conduct said fluid to and from the radiator from a point within the airship, an exhaust conduit within the airship, and means to transfer heat from exhaust gases in the conduit to said cooling fluid.

7. In an airship propelled by at least one internal combustion engine, an exhaust conduit, means to condense moisture from gases flowing through said conduit, and means to humidify said ases before the moisture 1s condensed there rom.

' 8. In an airship propelled by at least one internal combustion engine; at least two radiators located outside of the airship, one for a preliminary cooling circuit and one for a secondary cooling circuit; a constantly liquid cooling fluid for each of said cooling circuits; means to conduct the fluids to and from the radiators from points within the airship; an exhaust conduit Within the airship; means in one zone along the exhaust conduit to transfer heat from the exhaust gases to the cooling fluid of the preliminary cooling circuit; "and means in another zone along the exhaust conduit to transfer additional heat from the exhaust gases to the cooling fluid of the secondary cooling circuit.

9. In an airship propelled by at least one internal combustion engine; an exhaust conduit located within the airship; cooling means comprising a heat absorbing surface within the exhaust conduit, and a pair of water pans opening into said conduit, one

located on the up-stream side of said cooling surface and the other located on the downstream side of said coolin surface.

10. In an airship propelled by at least one internal combustion engine; an exhaust con- I 11. In an airship propelled by at least one internal combustion engine; an open water pan; and means to carry 'the exhaust gases over the surface of the water in the pan, the path of approach to the Water being arranged to cause the exhaust gases to be defiected by the Water surface.

12. In an airship propelled by at leastone internal combustion engine; an open water pan; and means to carry the exhaust gases over the surface of the Water in the pan, the path of approach to the water being inclined downwar ly and the path of departure being inclined upwardly.

PAUL SCHRODER.