US1730978A - Arrangement for mounting radiators in aeroplane wings - Google Patents

Description

Oct. 8, 1929. LEPERE 1,730,978

ARRANGEMENT FOR MOUNTING RADIATORS IN AEROPLANE WINGS Filed April 10, 1929 i i r i l //V V15 N 70%? [agne fiarie o/yes Lqoere Patented Oct. 8, 1929 EUGEN E GEORGES LEPERE, OF PARIS, FRANCE ARRANGEMENT FOR MOUNTING BADIATOBS IN .AEBOPLANE WINGS Application filed April 10, I829,

The invention relates to an improved arrangement of the radiator of water-cooled engines for aeroplanes in the aeroplane wings.

It hasalready been proposed to mount radiators of aeroplane engines in apertures of aeroplane wings, for the double purpose of improving the aerodynamic qualities of the aeroplane, due to the fact that theradiator is concealed, and of automatically regulating the temperature of coolin water, inasmuch as the maximum power 0 sponds to a flight with the steepest angle of attack, that is, to the most intense circulation of air through the radiator, While the minimum power corresponds very small angle of attack, in which the flow of air through the aperture is much reduced.

Although this arrangement afforded a certain degree of self-regulation of the temperature, it has been found, however, that the aperture containing the radiator was a source of much disturbances in the performance of the wings, that the maximum altitude of flight as well as the maximum speed were greatly reduced, so that the mounting of the radiator in the wings was finally abandoned.

On the other hand, it has been found in the recent period that certain apertured wings are,

equally as efficient as plain wings, and even superior. I

The present lnvention relates to a wing for aeroplanes or the like which comprises one or more apertures, and it is chiefly characterlzed by the fact that in the saidaperture or apertures, whose outline is such as to preserve the proper aerodynamic features of the wing, are mounted one or more radiators having parallel tubes or plates and so disposed that there will be no change in the direction of the air streams traversin the aperture.

In the appended rawing, which is'given solely by way of example:

Fig. 1 is a diagrammatic cross section of a wing radiator arrangement of the known type. r

Fig. 2 is a like section of a wing having an aperture whose outline is so designed as to preserve or improve the aerodynamic qualities of the wing.

Fig. 3 is a sectional View similar to Figure a the discharge the engine correto a flight with a] Serial No. 354,185, and in France June 9, 1928.

2, in which a radiator ture, according to the invention.

Fig. 4 is an inverted plan view of Figure 3.

In the diagrammatic sectional view of the known arrangement, shown in Fig. 1, 1 denotesthe set of radiator tubes; 2 and 3 are the collectors for the supply of hot water and of cooled water, res ctively. The arrows show the direction'o the air streams. It is readily observed that eddies are produced in the region a b 0, while streams of air impinge against the rear vertical surface (1 e. For these difl'erent reasons the qualities of the wing are greatly impaired, and the above arrangement hasbeen set aside in practice.

Fig. 2 is a diagrammatic sectional view of a wing provided with an air channel 4, of a current type. The wing is thus divided into a front part 5 and a'rear part 6 whose respective rear and front outlines are such that the air streams are practically not deflected, as shown by the arrow.

Figs. 3 and 4 show an arrangement according to the invention, wherein the radiator, consisting of a set of cooling members 7, is disposed in an aperture 4 of a wing quite similar to that shown in Figure 2; 8 is the Water supply collector and 9 the collector for the discharge of cooled water; the relative disposition of the collectors may also be reversed.

The dotted line 10 denotes an adjustable shutter, which may be provided above the air channel and consists for example of a Persian blind arrangement or a plate which is slidable from front to rear, whereby the aperture of the wing may be wholly or'partially obturated. V The said shutter is required only for certain classes of aeroplanes, which are adapted to travel in regions where the temperature is considerably variable.

The operation of the device is as follows. The air flowing-through the air channel will pass along the flat tubes of the radiator,

which are thus efficiently cooled, The air is mounted in said aperor in rising flight.

' the form ofconstruction face-by a curved surface,

, wherein said radiator tack. This self-regulation is due to the fact that the maximum power required from the engine corresponds to flight at steep angles, that is, to the most intense circulation of air through the radiator, whilst the minimum power corresponds to flight at small angles, that is, to a reduced circulation of air through the air channel. I

'Another advantage of this arrangement resides in that the maximum altitude and speed are little affected by the provision of the air channel, since the radiator, which is situated in the said channel, will occasion a loss of pressure which is favourable to the improvement of the qualities of the wing at the angles of attack normally employed in horizontal Obviously, the invention is not limited to herein described and represented, which is given solely by way of example; For instance, a wing has been represented which has but a single air channel or slot, but wings having several slots also fall within the scope of the invention. The wing may further comprise several distinct radiators, mounted in each channel.

Having now'describedmy invention what I claim as new and desire to secure by Letters Patent is:

1'. An arrangement for mounting the radiator of a water-cooled aeroplane engine in the aeroplane wing, comprising a thick wing 6. An arrangement as claimed in claim 1, which further comprises an adjustable obturating member consisting of a series of pivoted blades at the upper part of said air channel.

In testimony whereof I have signed my name to this specification.

. resins MARIE GEORGES tartan having an air channel whose outline is so determined as not to impair the aerodynamic qualities of the wing, and a radiator mounted within said channel and comprising radiating elements parallel with the aeroplane axis.

2. An arrangement for mounting the radiator of a water-cooled aeroplane engine in the aeroplane wing, comprising a thick wing having an air channel upwardly inclined from the front to the rear, and a radiator mounted within said channel and comprising radiating elements parallel with the aeroplane axis.

3. An arrangement for mounting the radiaftor ofa water-cooled aeroplane engine in the aeroplane wing, comprising a thick wing having an air channel upwardly inclined from the front to the rear and whose front wall is connected with the wing 'underiace by a curved surface of small curvature, the rear wall being connected with the wing upper and a radiator mounted within said channel and comprising radiating elements parallel with the aeroplane axis.

4:. An arrangement as claimed in claim 1,

comprises a set of parallel fiat channels of small thickness and comparatively large width.

5. An arrangement as claimed in claim 1, which further comprises an adjustable obturating member associated with said air channel.

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