US1623128A - Temperature-regulating system for aeronautical motors - Google Patents

Description

' 1927. 1,623,128 Apnl 5 H. c. MUMMERT TEMPERATURE REGULATING SYSTEM FOR AERONAUTICAL MbTORS Filed Dec. 8; 1922 a Sheets-Sheet 1 'INVENTOR HA EvEY C. MUMMEE'T.

1 623128 April 5 1927. H C MUMMERT 9 A I TEMPERATURE REGULATING SYSTEM FOR AERQNAUTICAL MOIORS Filed Dec. 8. 1922 3 Sheets-Sheet 2 INVENTOR HARVEY C. MUM/weer 1 623128 Aprll 5 1927. H. c. MUMMERT TEMPERATURE REGULATING SYSTEM FOR AERONAUTICAL MOTORS Filed Dec. 8. 1922 s Sheets-Sheet 5 lNVENT OR HAEVCYC. MUMMEET.

BY ATTORN Patented Apr. 5, 1927.

UNITED, STATES mvmr c. nunmnnr, or norms, NEW You; assrenon, BY mnsnn Assrennnnrs,

r cunrrss annornmn AND Moron comrm, me, or eannnn cr'rmLon-e 1s- LAND, new Your, A oonrona'rron or NEW YORK.

TEHPEBATUBE-IREGULATING SYSTEKIQB AEBONA'I J'TIGAL MOTORS.

Application. filed December My invention relates to temperature regulating systems for internal combustion mo-.

I shutter the radiator without in any way changing the volume of liquid relied upon' to obtain the desired cooling effect.

A further object of the invention is the incorporation in the cooling circuit of an oil temperature regulator, the latter being so disposed in its relation to the radiator as to provide at all times for an interchange of heat between the cooling agent in circulation and the oil, regardless of whether or not the volume of liquid circulated through the radiatoris varied or kept constant.

A still further obi'ect of the invention is the provision of a p urality of radiator sections having means associated therewith for excluding one or all of said sections from the cooling circuit as temperature conditions may require. j

Otherand further objects of the invention will be hereinafter pointedout. V

In the drawings, wherein like reference characters denote like or corresponding parts Figure 1 is a diagrammatic illustration of the cooling circuit'showing the manner in which the several radiator sections are sepa rately supplied with the cooling agent as well as the preferred disposition of ,the oil temperature regulator in combination therewith; Figure 2 is a detail sectional view of one of the valves;

Figure 3 is a side elevation of a modified form of circuit showing a practical arrangement of the Various feed line connections in so far as applicable to an aeroplane of more or less conventional design;

Figure 4 is a perspective -view of the modified form of circuit illustrated in Figure 3' i Fi re 5 is a longitudinal vertical sectiona view of the regulating valve forming a part of the modified circuit; and,

a, 1922. Serial No. 605,641

Figure is a transverse vertical sectional view of sald valve.

In the embodiment of the invention selected for illustration a wing 'or skin type radiator is shown. It is not intended,'however, that the invention shall be limited to this particular type ofradiator, as the means employed for regulating the volume of liquid flowing through the radiator may be used with equally good results in connection with radiators of varied and different forms.

Referring first to Figure 3, wherein por tions of the aeroplane areillustrated, desi nates the skeleton framework of the fuse age or body of the aeroplane, 11 the motor, and 12 the upper supporting surface or aeroplane wing. The motor 11 is of the well known multicylinder water-cooled type. It is mounted within and at the forward end of the fuselage 10 upon suitable engine bearers 13. Intemorly said motor 11 is provided with an oil' circuit (not shown) through which oil is adaptedto be circulated under pressure to all of the various parts of the motor requiring lubrication. Within the oil circuit, and preferably upon the exterior of the motor, an oil temperature regulator 14 is disposed. The oil in its circulation through said regulator is adapted to'enter through the oil duct 15, and to return to the motor after its circulation through said regulator, by way of a return duct 16. Duringts passage through the oil temperature regulator 14 an interchange of heat between the circulated oil and the coolin agent (likewise circulated under pressure% fec ted. Preferably the cooling agent isv circulated over andaround the oil temperature regulator 14 as indicated in the diagrammatic views. p The 'coolin motor 11', inc udes a radiator designated in its entirety as 17. The radiator (see Fig. 1) preferably comprises a plurality of radiator sections 18', each of which is constructed in the form of a hollow shell adapted to provide an outer covering for a portion of the aeroplane supporting surface 12. The cooling agent in its circulation is conveyed to each of the several radiator sections so arat'ely, as'in the preferred embodiment o the invention, provision is made for cutting in or is efcircuit, in addition to the require, one or all of. the separate sections of which the radiator 17 is composed; From the water jacket of the motor'the coohng agent is led by way of a pipe 19 to a manifold 20 having branch ducts 21 leading therefrom separately to each of the several radiator sections. Return ducts 22 are likewise provided for each of the separate radiator sections, the latter returning the water circulated through the radiator to a return manifold 23 from which the water is con-,

veyed byway of a pipe 24 to a main control valve 25. The supply ducts 21 and the return ducts 22 for each separate radiator section are each equipped with a separate control valve 26, said valves being in each instance manually operable from a convenient point within the fuselageor body It) so as to cut in or cut out any radiator sections desired.

The valves 26 are identical in construction. Each comprises a rotary valve member 27 having parallel passages 28 and 29 extended not with the valve transversely therethrough. The valve mem-- is adapted to control the volume of water entering'the radiator considered as a whole. Said valve comprises a suitable valve casing 31 and a rotary sleeve valve 32, the latter being provided with two separately formed substantially diamond shaped openings 33 and 34. By turning. the valve 32, said openings 33 and '34-are made to register respectively with the feed line 19 on the one hand and the return line 24 on the other. If the opening 34 is in registry with the return line 24 then, and then only, will the radiator 17 enter into and form a part of the Water circuit. The water, with the radiator forming apart of the water circuit, enters the manifold 20 (in the preferred form of the invention); is distributed by said manifold to the supply ducts 21, and from the supply ducts 21 is carried separately to the several sections 18 of the radiator. In its return flow the water enters the return ducts 22; is conveyed by said ducts 22 to the manifold 23, and by said manifold is conveyed to the return pipe 24, which latter pipe directs the water through the opening 340i the valve to the interior of the valve casing. As the opening 33 'of the valve is out of registry with the branch pipe 31' leading oil from the supply pipe 19, obviously the water must cially advanta eousas a chan leave the valve casing by way of the pipe 32'. From the pipe 32' the Water enters the container 33' within which the oil temperature regulator 14 is enclosed, and after efi'ecting an interchange of heat with the oil confined to-the oil temperature regulator, is conducted again to the motor l1 by way of the pipe 34.

When it is desired that the volume of Water circulated through the radiator 17 be restricted or regulated, the main valve 25 is operated. Such operation has a like effect upon all of the sections 18 of the radiator 17. VVh n it is desired, however that the separate t adiator sections be individually regulated to the end that the effective area of the radiator may be varied, any one of the valves 26 may be operated to obtain the desired result. One, two, three, or all of the separate radiator sections may be either separately cut in or separately cut out as temperature conditions may require.

In the system illustrated in Figs. 3 and 4, no means 1s shown for separately cutting in or cutting out the several radiator sections. If desired, the radiator may be constructed as a unit and the single mam valve 25 operated as hereinbefore explained. This construction, however, is instrumental only in varying the volume of water circulated through the radiator and has noefiect whatsoever in either decreasing or increasing the effective surface area of the radiator. For this reason, the diamond shaped openin s in the rotary valve member 32 are provided. Openings thus formed will give the necessary gradual adjustment.

ing, 'with the motor cold, the most eflicient operating temperature can be quickly obtained by simply rotating the valve mem ber 32, to cut out the radiator from the cooling circuit. Having cut out the radiator from the cooling .circuit, the water in circulation is "merely by-passed over and around the oil temperature regulator back again to the motor. When the most eflicient operating temperature is reached the valve member 32 may be gradually J, turned to thereby gradually increase the. volume of water admitted'to the radiator considered as It is obvious from the above that in starta whole. In this way that temperature deemed most eflicient can be easily and readily maintained. If desired, instead of merely varying the volume in circulation through the radiator, the valves 26 'may' be separately operated, in which event one or more of the sections of the radiator can be brought into service from time to time as needed. In a wing type radiator, incapable of being shuttered, such adjustments are espee in volume or a change in edbctive areaw' give thesame results as shuttering practised heretofore.

Another advantage 1n constructing the radiator of a plurality of radiator sections is that in military craft,even should one of the radiator sections be rendered unfit for continucd use through gun fire the remaining sections can be still used without a loss in volume by simply cutting the damaged radiator section out of the cooling circuit. Especially is this true in a win type radiator, which due to its vulnerability is extremely likely to be damaged due to gun fire. Moreover, as a substitute for the plural number of independently operable valves 26,- a unit valve may beprovided having multiple ports so organized that different settings of the valve member will control the cutting in and cutting out of the several radiator sections according to such setting.

While I have described my invention in detail in its present preferred embodiment, it will be obvious to those skilled in the art after understanding my invention, that various changes and modifications may be made therein without departing from the spirit or scope thereof. I aim in the appended claims to cover all such modifications and changes.

What I claim is 1. In a temperature regulating system for aeronautical motors, the combination with the oiling system of the motor of an oil radiator, a circuit for the liquid coolin agent including a container within whic the oil radiator is enclosed and thru which the liquid cooling agent is continuously passed, a radiator within said coolin circuit, a by-pass around said last mentioned radiator, and means to open and close said by-pass whereby the cooling agent in circulation may be directed thru said container and over the oil radiator without its first having been passed-thru the radiator of the cooling circuit.

2. The combination, in an aeronautical motor, of an oil circuit within which oil is circulated under pressure, an oil radiator within said circuit, a cooling circuit, a radiator withm said coolin circuit, said radiator comprising a plura ity of radiator sections, a radiator supply pipe within said cooling circuit, a supply manifold o 'n to said supply pi e, branch pipes leading off from said mani old, one pipe leadin to each radiator section, a separate valve or each branch pipe, said valves bein independently operable to either open or c ose said radia tor sections respectively to and from said cooling circuit, a return manifold, return pipes e ading ofl, one from each said radiator section, to said return manifold, a return pipe leading off from said return manifold, a container 0 n to said return pipe within-which said 011 radiator is enclosed, a"

its passage thru the radiator of the cooling circuit or over the radiator without its having first been passed thru the radiator of said cooling circuit.

3. The combination, in an aeronautical motor, of an oil circuit within which oil is circulated under pressure, an oil radiator within said circuit, a cooling circuit, a radiator within said coolin circuit, said radiator comprising a lura ity of radiator sections, means for a mitting or excluding the cooling agent respectively to and from said radiator sections, a return pipe common to the several radiator sections, a container open to said return pipe within which the oil radiator is enclosed, a by-pass leading off from the radiator supply pipe and open to said return pipe at a point intermediate said radiator sections and the container, and a valve operable within the cooling circuit to either direct the cooling agent over the oil-radiator after its passage thru one or more of the radiator sections of the cooling circuit or over the oil.radiator without the cooling agent having first been passedthru one or more of said radiator sections.

4. A temperature re lating system for aeronautical motors inc uding, in'combination with the oiling system. of the motor an oil radiator, a circuit for the liquid cooling agent including a container within which the oil radiator is enclosed, a radiator comprising a pluralit of radiator'sections within said cooling circuit, means operable to cut in or out any one or more of said radiator sections from said coolin circuit a by-pass around said sectional radlator, and I In testimony whereof I hereunto a'ffix my signature.

' HARVEY C. MUMMERT.

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