US2288514A - Cooling system for internal combustion engines - Google Patents

Description

June 30, 1942. H. cARosELLl 2,288,514

COOLING SYSTEM FOR INTERNAL COMBUSTION ENGINES Filed Dec. 16, 1939 2 Sheets-Sheet 2 June 30, 1942- H. cARosi-:LU

COOLING SYSTEM FOR INTERNAL GOMBUSTION ENGINES 2 Sheets-Sheet l Filed Dec. 16, 1939 nga Patented June 30, 1942 COOLING `SYSTEM FOR'INTERNAL CMBUSTIGN ENGINES Hellmut Caroselii, Berlin-Adlershof, Germany Application December 16, 1939, Serial No. 309,683 In Germany December 22, 1938 (Cl. 12S-174) Claims.

This invention relates to Cooling systems in in ternal combustion engines and more particularly to cooling systems for motors in airplanes in which the cooling is effected by liquid means exclusively, In order to render the invention clearly to be understood it must be pointed out, that cooling systems substantially of the kind referred to mostly consist of a chief system and of an auxiliary system. Substantially the main system comprises the pump for moving the cooling means, the cooling jacket of the engine, the radiator proper as well as the requisite pipe lines, and the auxiliary system comprises a storage tank as well as the necessary supply and discharge pipe lines. In order to ensure a continuous circulation of the cooling agent and a uniform withdrawal of heat, an ebullition of the cooling agent Within the cooling jacket must be avoided. Furthermore, an interruption of the current of the cooling agent Within the suction branch pipe of the pump must be prevented, and nally steam and gas bubbles perhaps emanating from the cooling agent must be separated from said current.

The first requirement is fuliilled by the cooling systems known up to the present in that the highest cooling temperature of the cooling uid occurring, that is the temperature ci the cooling agent at the point of discharge from the motor, lies a few degrees, for instance 6 degrees centigrade, below the temperature of steam saturation belonging to the pressure prevailing there.

The second requirement is ensured, when the pressure ahead of the pump for the cooling agent is higher by a suiiicient minimum, for instance 0.2 atmosphere than the steam pressure belonging to the temperature prevailing there. For the purpose of separating the steam and gas, devices of varying construction are known. The said devices are so arranged that the steam and gas bubbles separated out are conducted into the gas chamber of the storage tank.

In respect of a normal system of cooling the following values for instance, are obtained for In this instance the requirements called for above are fullled. But there will be difculties if with respect to a high drop of heat within the radiator, the temperatures of the cooling agent must be chosen very high, and when theipressure at the discharge point of the-cooling agent in the motor or the pressure at the suction branch of the pump respectively, in consequence of external conditions-ior instance at a slight outside pressure particularly during the operation at great altitudesis not greater-or even less than the steam pressure belonging to the temperature of the cooling agent. If in these instances-for considerations of space and weight-the required pressure within the outer branch of the cooling system cannot be produced statically throughasuperimposed water column, the above mentioned requirements cannot be fulfilled without special auxiliary devices.

Therefore it is the object of the invention, to obtain an increase of the pressure in the main system. This increase of pressure is obtained by means of one or more'vortex vessels, which are connected to the main system in such a manner, that the cooling agent from the main system enters tangentially into the boundary zone of the spinning vortex of liquid within the vortex vessel and it will leave said boundary zone in a similar manner.

A further characteristic feature of the invention is to be seen in that the auxiliary system is substantially connected with the center of the vortex vessel, so that the supply of cooling agent from the storage tank to the vortex vessel is effected substantially in the inner zone through static pressure. i

A still further characteristic feature of the invention lies in the fact that the said vortex vessels will act as steam separators. In order to obtain such action, the central zone of the vortex Vessel or vortex vessels is connected to the liquid chamber and the steam chamber of the storage tank by means of separate channels.

A number of modifications according to the invention is shown in the drawings by way of example.

Figures l, 2a, 2b, 3, Ll and 5 show a modification` ranged behind the discharge end of the coolingY jacket B, and the conduit I enters said vortex vessel in such a manner that the conduit will branch off from the boundary zone of the vortex. For that purpose the said conduit I enters the vortex vessel tangentially (see Figures 2a and 2b) and it leaves said vessel again in a tangential direction.

The storage tank C is connected to the vortex vessel by means of the conduit 2, which enters the central zone of the vortex vessel 3. In this manner a higher pressure is obtained within the system I than within the system 2, so that the -system I may be considered as the high pressure system and the system 2 as the low pressure system.

In lieu of the vortex vessel 3 there may be also employed a mechanically acting device, as for instance a driven blade Wheel. By this means the pressure effected through the rotating vortex may be increased within the vessel 3.

In order to replenish the quantities of liquid evaporated from the storage tank C, the vortex vessel 3 must be arranged below the said tank, so that the liquid will freely flow into the vortex vessel through the conduit 2. The said vortex vessel may serve at the same time as steam and air separator. The gas bubbles collecting in the center of the vortex will rise through the conduit 2 into the collecting reservoir.

Figure 3 shows an arrangement in which the movement of the counter currents of gas and liquid in the conduit 2 is facilitated in that this conduit consists of two pipes 4 and 5, with the pipe 5 located within the pipe 4. The pipe 5 connects the inner Zone with the steam chamber of the storage vessel C, while the pipe 4 connects the inner Zone of the vortex vessel 3 with the liquid chamber of the storage vessel C.

In Figure 4 the liquid conduit I between the center of the vortex and the storage tank and the gas conduit 5 are separated through a two-sided tapping of the center of the vortex.

Figure 5 shows an arrangement in which the storage tank C is located below the discharge point of the cooling agent from the motor, as such is customary in many cases with motors in airplanes for the sake of saving space. In order to render possible a ventilation of the cooling system at the highest place, which lies in this instance at the discharge point of the cooling agent, a vortex vessel 6 serving as gas separator is provided, in which the main conduit I enters and leaves at the periphery, while the ventilation conduit 5 starts from the center thereof. A second vortex vessel 3 is arranged according to Figure 4. From this vessel a Ventilating duct may be passed by way of the vortex Vessel B to the container C. In the high pressure circuit I both vessels are arranged in succession. In the upside-down position of the motor the vortex vessels 3 and 6 will change their action. Such vortex vessels may be arranged at all those points where a ventilation of the cooling system appears necessary.

Each Vortex vessel may be made integral with its adjacent part of the cooling system, for instance with the motor or storage tank.

The dimensions of the vortex vessels are governed through the pressure necessary within the high pressure part of the cooling system.

Cooling systems are known, in which vortex vessels of a form similar to that described above, are used as steam and air separators. However, with cooling systems of that type the storage vessel is located either in the main system-denominated as high pressure part in the present instanceor in shunt with a communication of the liquid chamber with the main vsystem (Figure 6) in such a manner that through said connection cooling agent is to flow from the storage tank C to the main system I. As the pressure in the storage tank C at a slight external pressure cannot be continuously higher than the steam pressure of the cooling liquid at the temperature prevailing within the storage tank, the pressure in the main system must be less at the entering point 'I of the supply line from the storage vessel C than the steam pressure in the collecting vessel, in order to permit the liquid to flow from the latter to the main system. But as already mentioned above this requirement will cause an interruption of the cooling current at the entry point of the pump; or in consequence of the centrifugal action of the steam-air separators 3 within the conduit I such a high pressure level is obtained, that ahead of the entry point of the pump there is a pressure, which is higher than the steam pressure. Subsequently the cooling agent is forced from said point I into the storage tank C. In consequence the quantity of gas 8 contained in the storage vessel is pushed into the conduit l by way of the steam-air separator 3.

Thus the steam-air separator in this arrangement will be unsuccessful.

The novel feature over this known arrangement, as stated above, consists in that both the liquid chamber and the gas chamber of the of the storage tank are in communication with the center of the vortex vessel, which is under a slight pressure only.

I claim:

l. Cooling system for internal combustion engines particularly for motors in airplanes in which the cooling is effected by liquid means comprising in combination: a main system consisting substantially of a pump for the liquid, a cooling jacket for the engine, a radiator and pipe lines connecting said pump, jacket and radiator, an auxiliary system consisting substantially of a storage tank and supply and discharge pipe lines connected to said storage tank and means connecting said supply and discharge pipe lines to said main system for maintaining in said main system a higher pressure than in the auxiliary system, said means comprising a cylindrical vortex vessel having tangential connections to the main system and a connection to said supply pipe at a point of reduced pressure in the vortex vessel.

2. Cooling system for internal combustion engines particularly for motors in airplanes in which the cooling is effected by liquid means comprising in combination: a main system consisting substantially of a pump for the liquid, a cooling jacket for the engine, a radiator and pipe lines connecting said pump, jacket and radiator; an auxiliary system consisting substantially of a storage tank and supply and discharge pipe lines connected to said storage tank and means connecting said supply and discharge pipe lines to said main system for maintaining in said main system a higher pressure than in the auxiliary system, said means comprising a cylindrical vortex vessel having at its ends tangential connections to the main system and axial connections to said supply and discharge pipes of said auxiliary system.

3. Cooling system for internal combustion engines particularly for motors in airplanes in which the cooling is effected by liquid means compris'- ing in combination: a main system consisting substantially of a pump for the liquid, a cooling jacket for the engine, a radiator and pipe lines connecting said pump, jacket and radiator; an auxiliary system consisting substantially of a storage tank and supply and discharge pipe lines connected to said storage tank and means connecting said supply and discharge pipe lines to said main system for maintaining therein a higher pressure than in the auxiliary system, said means comprising a cylindrical vortex Vessel having at its ends tangential connections to the main system and a connection to the supply pipe of the auxiliary system extending axially from an end thereof.

4. Cooling system for internal combustion engines particularly for motors in airplanes in which the cooling is effected by liquid means comprising in combination; a main system consisting substantially of a pump for the liquid, a cooling jacket for the engine, a radiator and pipe lines connecting said pump, jacket and radiator, an auxiliary system consisting substantially ol a storage tank and supply and discharge pipe lines connected to said storage tank and means connecting said supply and discharge pipe lines to said main system for maintaining therein a higher pressure than in the auxiliary system, said means comprising a cylindrical vortex vessel having at its ends tangential connections to the main system and an axial connection to the supply pipe from the storage tank of the auxiliary system from a point of reduced pressure in the vortex vessel.

5. Cooling system for internal combustion engines particularly for motors in airplanes in which the cooling is eifected by liquid means comprising in combination: a main system consisting substantially of a pump for the liquid, a cooling jacket for the engine, a radiator and pipe lines connecting said pump, jacket and radiator; an auxiliary system consisting substantially of a storage tank and supply and discharge pipe lines connected to said storage tank and means connecting said supply and discharge pipe lines to said main system for maintaining therein a higher pressure than in the auxiliary system, said Ymeans comprising a cylindrical vortex vessel having tangential connections to the main system and axial connections with said discharge and supply pipes, said pipes terminating in the steam chamber and the liquid chamber of the storage tank, respectively.

6. Cooling system for internal combustion engines particularly for motors in airplanes in which the cooling is effected by liquid means comprising in combination: a main system consisting substantially of a pump for the liquid, a cooling jacket for the engine, a radiator and pipe lines connecting said pump, jacket and radiator; an auxiliary system consisting substantially of a storage tank and supply and discharge pipe lines connected to said storage tank and a cylindrical vortex vessel having co-axial connections with said supply and discharge pipe lines and tangential connections With said main system for producing a higher pressure in the main system than in the auxiliary system, said vortex vessel effecting a separation of gas and steam from the liquid.

7. Cooling system for internal combustion engines particularly for motors in airplanes in which the cooling is effected by liquid means comprising in combination: a main system consisting substantially of a pump for the liquid, a

cooling jacket for the engine, a radiator and pipe lines connecting said pump, jacket and radiator; an auxiliary system consisting substantially of a storage tank and supply and discharge pipe lines connected to said storage tank and cylindrical vortex Vessels having axial connections to said supply and discharge pipe lines and tangential connections to said main system for producing a higher pressure in the main system than in the auxiliary system.

8. Cooling system for internal combustion engines` particularly for motors in airplanes in which the cooling is effected by liquid means comprising in combination: a main system consisting substantially of a pump for the liquid, a cooling jacket for the engine, a radiator and pipe lines connecting said pump, jack and radiator; an auxiliary system consisting substantially of a storage tank and supply and discharge pipe lines connected to said storage tank, means connecting said supply and discharge pipe lines to said main system for maintaining a higher pressure in the main system than in the auxiliary system, said means comprising cylindrical vortex vessels arranged so the functions of said supply and discharge pipe lines can be automatically interchanged, said vortex vessels having the connections to the main system effected tangentially and in succession and having their central Zones connected with the storage tank by said supply and discharge pipes.

9. Cooling system for internal combustion engines particularly for motors in airplanes in which the cooling is elected by liquid means comprising in combination: a main system consisting substantially of a pump for the liquid, a cooling jacket for the engine, a radiator and pipe lines connecting said pump, jacket and radiator; an auxiliary system consisting substantially of a storage tank and supply and discharge pipe lines connected to said storage tank; means connecting said supply and discharge pipe lines to said main system for maintaining a higher pressure in the main system than in the auxiliary system, said means comprising cylindrical vortex vessels arranged so the functions of said supply and discharge pipe lines can be automatically interchanged, said Vortex vessels having the connections to the main system effected tangentially and in succession and the central zones thereof connected with the storage tank by said supply and discharge pipes, the vortex vessel serving for the separation of gas and steam from the liquid being located above the storage tank and the vortex vessel serving for the production of the pressure proper being arranged below the said storage tank.

10. Cooling system for internal combustion engines particularly for motors in airplanes in which the cooling is effected by liquid means comprising in combination: a main system consisting substantially of a pump for the liquid, a cooling jacket for the engine, a radiator and pipe lines connecting said pump, jacket and radiator: an auxiliary system consisting substantially of a storage tank and supply and discharge pipe lines connected to said storage tank and means connecting said supply and discharge pipe lines to said main system for maintaining therein a higher pressure than in the auxiliary system, said means consisting of a cylindrical vortex vessel having tangential connections with the main system and axial connections with the auxiliary system at its central zone of reduced pressure.

HELLMUT CAROSELLI'

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