US1933998A - Oil cooler - Google Patents

Description

Nov. 7, 1933. s. T. PAYNE. 1,933,999

OIL COOLER Filed Feb. 17, 1950 6 INVENTOR L 2 SAMuELTPAYNE.

n ATTORNEY Patented Nov. 71, 1933 PATENT OFFICE OIL COOLER samuel T. Payne, Freeport, N. Y., assignor to Curtiss Aeroplane & Motor Company, Inc., a

corporation of New York Application February 17, 1930. Serial No. 428,97

16 Claims. (01. 244-31) This application relates to aeronautical motors and more especially to oil cooling systems therefor.

Aeronautical motors designed for either liquid cooling of the cylinders or air cooling thereof, and equipped with separate devicesfor cooling the oil have been proposed prior to my invention. So far as I am aware, however, no devices of this nature have been previously proposed in which the separate device for cooling the oil is positioned in the nose of a nacelle of the engine so that the oil might be cooled by the air blast which necessarily strikes the nose of said nacelle.

One of the objects of my invention is to provide devices for the separate air cooling of the oil of an aeronautical motor which devices are appropriate for use either with air cooled motors or liquid cooled motors.

A further object is to minimize the total surfaces exposed to wind resistance by a utilization of the necessary space in the nose of the nacelle for the purpose of cooling the oil.

A further object of my invention is the provision of new and improved means for regulating the temperature of the oil so that the oil may be pre-heated when the motor is first started and may be later maintained at a proper temperature by suitable cooling thereof.

A further object of the invention is to provide a novel method of cooling oil, in conjunction with an oil reservoir, by directing the oil along the inner surface wall of the reservoir in the form of a thin film, whereby it is cooled by the influence of a cooling draft on the exterior of the tank, after which the oil mingles with the main body of oil in the reservoir.

Further objects of my invention will be apparent from a reading of the subjoined specification and claims and from-a consideration of the accompanying drawing.

In order to explain the invention more clearly, three embodiments thereof are shown in said drawing, in which:

Fig. 1 is an elevation of a part of an airplane and of a liquid cooled motor supported thereon, which motor is constructed according to my invention;

Fig. 2 is a sectional view of a part of the motor nacelle shown in Fig. 1 taken on a vertical line looking laterally of the nacelle;

Fig. 3 is a vertical sectional view taken substantially along the line 3-3 of Fig. 2;

Fig. 4 is a side elevation of a part of a different airplane and a different motor also constructed according to my invention;

Fig. 5 is a vertical sectional view of a part of the motor nacelle shown in Fig. 4 looking laterally of the motor;

Fig. 6 is a vertical sectional view taken substantially along the 11m 66 of Fig. 5; r

Fig. 7 is a view similarto Fig. 5 on an enlarged scale but showing another modification of my invention; and

Fig. 8 is a sectional view on an enlarged scale taken substantially on the line 8-8 of Fig. '7.

In general, I have illustrated my invention by several aeronautical motors. All of these are equipped with propellers of the pusher type. ,One. of the motors is disclosed as a liquid cooled motor and is provided with an oil reservoir situated in the nose of the nacelle of the motor. Oil may pass into this reservoir by either one of two pipe lines and a two-way valve is provided by which the.oil may be selectively directed through either v of the pipe lines so that during the warming 75. up process the oil may pass directly into the top of the reservoir, but after the motor has become sufiiciently warmed the oil" may be switched through the other pipe line to pass as a comparatively thin sheet through a passage way situated between the nose of the nacelle and separated from the oil reservoir by a baflie plate. The oil passes downward through this passage way to the bottom of the oil reservoir and thus is cooled in its passage by the action of the air striking against the nose of the nacelle of the motor.

Another modification disclosed in the drawing illustrates an air cooled motor which is provided with an oil cooling compartment in the nose of the nacelle somewhat similiar to that just described. There is the difference, however, that instead of the oil having unrestricted passage into the oil reservoir below the bottom of the bafile plate separating the cooling compartment-from the reservoir compartment, it must passfrom the cooling compartment to the reservoir compartment through one of a plurality of small holes in the bafile plate.

In a third modification I have disclosed a somewhat similar device in which instead of providing a pair of separate conduits for delivering the oil to the oil reservoir, I provide only one conduit which passes downward adjacent to the nose of the nacelle and sprays the oil to be coo'oled on the nose plate of the nacelle. I also provide a series of shutters by which the air is selectively allowed to or prevented from striking against the true nose of the nacelle so 110 that the oil may be optionally allowed to remain warm or to become cool as desired.

Referring especially to Figs. 1, 2 and 3 of the drawing, I have shown an airplane equipped with a wing 11 and having supported thereon a water cooled motor which is enclosed by a casing 12. The motor is adapted to drive a pusher type propeller 13 for pushing the airplane through the air. The forward portion or nose 14 of the casing 12 is shown-more in detail in Fig. 2. As may be seen therein, it comprises an outer sheet or nose plate 15 behind which is positioned the oil reservoir 16. Arranged substantially parallel to the sheet 15 is a bafile plate 17 so positioned that a very narrow space 18 is provided between the sheet 15 and the baflle' 1.7. The baflie 17 does not extend to the bottom of the tank 16 but is cut off as at 19 for the purpose of allowing the oil which passes downward through the passage 18 to enter the lower part of the oil reservoir 16. Opening into the upper part of the passage 18 is an inlet oil conduit 21 which leads from a manually controlled threeway valve 22. The valve 22 is in turn connected with an oil conduit 23 which is designed to conduct oil from the motor to the valve 22. There is also connected to the valve 22 a third oil conduit 24 through which oil may pass from the pipe 23 directly into the oil reservoir 16. Adjacent to the bottom of the oil reservoir 16 is another oil conduit 25 which serves to withdraw oil from the reservoir 16 and conduct it to the motor as it is needed. A filler pipe26 may also be provided by which the oil reservoir 16 may be replenished with oil.

In the operation of the form of device shown in Figs. 1, 2 and 3, oil normally passes from the motor through the conduit. 23, the valve 22,. the conduit 21 and downward in a thin sheet through the passage 18 into the bottom of the oil reservoir 16. In passing down through the passage 18 part of the heat from the oil is transferred to the sheet 15 and is transferred therefrom to the air which continually rushes past saidsheet inasmuch as it is located in 'the nose of the nacelle. In this way the oil is cooled at'a relatively rapid rate. After the oil has been cooled and passed into the reservoir 16 it may be again delivered to the motor through the oil conduit 25 by means of a pump or by any other suitable means.

When the motor is beginning its operation the oil will for some time be relatively cool and it will not be necessary that it be led through the passage 18 to cool it inasmuch as it is already sutficiently cool. The operator may then by manipulation of the'valve 22 cause the oil to pass through the conduit 23, the valve 22 and the pipe 24 directly into the reservoir 16 without passing through the passage 18 and thus may ac-,

complish a more rapid warming of the oil to the proper temperature.

Referring specifically to the form of my invention shown in Figs. 4, 5 and 6 I have shown an airplane having a motor 10 mounted upon a wing 11*. A nacelle 12* is providedto shield the auxiliary parts-of the motor and to partially streamline the motor. The nacelle may also contain, if desired, .a gasoline tank, etc The motor is designed to push the airplane by means of the pusher propeller 13 The nose 14 of the nacelle 12 is provided with a nose plate 15*, an oil reservoir 16, and a baflie 17 The latter, together wih the sheet 15 forms an oil cooling passage 18. There are also provided oil conduits 21 23 24 and 25*, A three-way -is adapted to similar uses.

holes on to the nose plate 15 vavle 22 similar to the valve 22 is provided and The bafile 17 instead of being cut off as is the baffie 17 at 19, is extended downward to the bottom of the oil reservoir 16, but isprovided with a plurality of small holes 27 through which it is possible for the oil to pass into the oil reservoir 16 from the passage 18*.

The operation of the embodiment of my invention shown in Figs. 4, 5 and 6 is very similar to the operation of the embodiment shown in Figs. 1, 2 and 3. However, inasmuch as my invention is shown in these figures as applied to an air cooled motor, there is no necessity of provision for the cooling of the liquid by which the cylinders are cooled, the cylinders being cooled by the air which passes around the nacelle and strikes against the cylinders of the motor itself. The oil, in passing from the passage 18 to the reservoir 16 obviously passes through the open-, ings 27.

A further embodiment of my invention is shown in Figs. 7 and 8. Therein, an oil reservoir 16 is provided in the nose of a nacelle 12 which may be associated with the wing 11 of an airplane. The nacelle 12 is equipped with a true nose plate 15 against which cooling air is at times adapted to strike. The oil is delivered from the motor through an oil conduit 23 The conduit 23 is continued downward within the reservoir 16* adjacent to the nose plate 15*. A plurality of holes suchas the holes 31 and 32 are formed in the sides of the conduit 23 and the lower end of the conduit is closed. Oil passing through said conduit is sprayed through said This nose plate may be cooled by the passage of air over it and thus the oil which is being sprayed upon it may be in turn cooled. Thereafter, the oil will run down over the inner surface of the nose plate 15 into the reservoir 16 and may later be withdrawn from the reservoir through the conduit 25. In front of the nose plate 15 I provide an air passage 33 which is formed between the true nose plate 15 and a false nose plate or shield 34. This shield 34 is provided with a plurality of shutters such as the shutters 35, 36, 37, 38 and 39. These shutters may be operated in any suitable manner by the operator of the airplane or the engineer in charge of the engine, so that, when they are open, air may flow past the nose plate 15 to cool the oil, but when they are closed air may not flow by the nose plate and thus the oil will be more quickly warmed by the engine. Thus, the oil may more rapidly reach the proper operating temperature after the engine is newly started.

The operation of the form of my invention shown in Figs. '7 and 8 will be apparent from the drawing and description. The heated oil is withdrawn from the motor through the conduit 23 and is sprayed upon a nose plate 15 Depending upon whether the shutters 35 to 39, inclusive, are open or closed, the oil will be relatively rapidly or almost inappreciably cooled by contact with the said plate. After the cooling process the oil will drop down into the main body of oil in the reservoir 16 and may thereafter be withdrawn through the conduit 25 for'use in lubricating the motor.

It is to be understood that the above described embodiments of the invention are for the purpose of illustration only and various-changes may be made therein without departing from the spirit and scope of the invention.

I claim as my invention:

1. An oil reservoir having formed therein an inner shell for directing and confining the oil admitted'thereto over the inner surface wall of said reservoir.

2. An oil reservoir comprising an outer shell, a shell within said outer shell and spaced therefrom forming between said shells a space, said space being open to said reservoir, and an oil inlet connection in said outer shell and opening into said space. V

3. In an oil reservoir, an inlet oil passage, an inner shell spaced from and in close proximity to the external wall of said reservoir to provide between said reservoir and said inner shell an oil space open respectively to said inlet passage and to said reservoir.

4. An oil reservoir comprising an outer shell, a shell within said reservoir lying close ,to and substantially parallel with said outer shell, said inner shell forming by its proximity to said outer shell a narrow space, and an'oil inlet passage open to said space.

5. In aircraft, a heat generating power plant through which oil is circulated, an oil reservoir comprising an outer shell, an inner shell spaced close to and lying substantially parallel to said outer shell. forming between said shells a narrow space, an inlet passage in said outer shell and open to said space, said space being open to said reservoir at a point remote from said passage, and a conduit from said power plant to said inlet passage.

6. An oil reservoir comprising an outer shell, a shell within said reservoir lying close to and substantially parallel with said outer shell forming by its proximity to said outer shell a narrow space, and forming thereby, a main reservoir within said inner shell, said space being open to said main reservoir, an inlet connection to said space, another inlet connection to said main reservoir, and selective means to connect said inlet connections in operable relation to either said oil reservoir or said space respectively.

'7. In aircraft, a heat generating power plant through which oil is circulated; an oil reservoir comprising an outer shell, an inner shell spaced from said outer shell and covering a substantial portion of the area thereof, forming between said shells a space through which oil is adapted to flow, said space being open to said reservoir, an inlet connection to said space, an inlet connection to said reservoir; a conduit adapted to conduct oil from said power plant to said reservoir, and means to selectively connect sai'i conduit with either of said inlet connections.

8. The combination in aircraft of a heat generating power plant through which oil is circulated under pressure, and a casing for said power plant against the inner surface wall of which the oil in circulation is discharged and cooled.

9. For use with an aerial vehicle, an oil lubricated aeronautical motor, a casing associated with said motor having walls and having a substantially stream-line shape and over the outer surface of one of the walls of which air flows when the aerial vehicle is in flight, and means for conducting oil from said motor and for causing the oil to be discharged against an inner surface of said positioned in said nose, means for conducting oil to said reservoir comprising an oil passage contiguous with said nose, means for supplying heated oil from said motor to said oil passage, and means for by-passing the oil from said motor directly to said oil reservoir.

12. In a device of the character described, in combination an aeronautical motor, a nacelle associated with said motor, said nacelle having a nose, an oil reservoir positioned in said nose, means for conducting heated oil from the motor to the oil reservoir, means for optionally cooling the heated oil in its passage from the motor to the reservoir, and means for optionally preventing the operation of said cooling means whereby the oil may be pre-heated when desired.

13. In a device of the character described, a motor, a nacelle for said motor, said nacelle having a nose, an oil reservoir disposed within the confines of said nose, and means for conducting oil to said reservoir including an oil passage within said nose, one wall of said nose comprising the outer wall of said oil passage.

14. In a device of the character described, a motor, a nacelle for said motor, said nacelle having a nose, an oil reservoir disposed within the confines of said nose, means for conducting oil to said reservoir including an oil passage within said nose, one wall of said nose comprising the outer wall of said oil passage, and means for supplying heated oil from the motor to said oil passage.

15'. The combination in aircraft of an oil lubricated motor, a nacelle for said motor, said nacelle having a nose, an oil passage within said nose, one wall of said nose comprising the outer wall of said oil passage, a shield disposed in spaced apart relation to said wall of said nose and havin substantially the same configuration as said wall of said nose, thereby providing a passage between said wall of said nose and said shield, and means carried by said shield for controlling the flow of air through said last named passage.

16. In a device of the character described, in combination; an aeronautical motor; a nacelle associated with said motor, said nacelle having a nose; an oil reservoir positioned in said nose; and a partition within said oil reservoir positioned adjacent to the nose of said nacelle, and positioned at all points substantially equidistant fromthe nose, said reservoir having an inlet opening positioned forward of said partition, whereby there is formed an oil passage of relatively small cross section contiguous with the nose of said nacelle and leading from said inlet to the main portion of said oil reservoir.

SAMUEL T. PAYNE.

Images