US1645612A - Air tunnel for aeroplane fuselages - Google Patents

Description

t..18 192 0c 7 J. MILLER AIR TUNNEL FOR AEROPLANE FUSBLAGES Filed April' 9. 1927 Patented Oct. 18, 1927.

STATS PATENT orr'ica.

JOSEPH MILLER, F WALNUT HILL, MAINE.

AIR TUNNEL FOR AEROPLANE FU SELAGES.

Application filed April 9, 1927. Serial No. 182,414.

The present invention relates to an air tunnel to be used in conjunction with an aeroplane fuselage to minimize the head re.- sistance.

The important object of the invention li s in the provision of a tube or tunnel extending longitudinally of the fuselage of an aeroplane so as to minimize the head resistance. At the present time, it is quite common to drive aeroplanes by propellers at the front thereof and there is a great resistance set up by the wind created by these propellers hitting the fuselage and it is the prime object of the invention to minimize the etl'eet as 1!! far as ossible.

Anotlier important object of the invention lies in the provision of a device of this nature having a fan therein operable from the prime mover of the aeroplane.

2a A still further important object of the invention resides in the provision of a device of thi nature, which is exceedingly simple in its construction, inexpensive to construct and install, thoroughly efficient and reliable in its operation, and otherwise well adapted for the purpose for which it is designed.

With the above and numerous other objects in view as will appear as the description proceeds, the invention resides in certain 0 novel features of construction, and in the combination and arrangement of arts as will be hereinafter more fully described and claimed.

In the drawing:

Figure 1 is a side elevation of an aeroplane fuselage with my improved device associated therewith.

gigure 2 is a front elevaton of the device, an

Figure 3 is a fragmentar lon 'tudinal section through the forward brtioii thereof.

Referring to the drawing in detail, it will be seen that 5 denotes an aeroplane fuselage. The numeral 6 denotes a tube or tunnel extended longitudinally of the fuselage, open at the front and rear ends. In the front end of the tube or tunnel 6 there is mounted a pair of s aced internal annular flanges 7. A ring 8 as rollers 9 journaled thereon and ridable in the space between the flanges 7. Turn blades 10 are mounted in the ring 8. A ring gear 11 is secured to the ring 8 by bolts 12, and held spaced from said ring by spacing sleeves 18.

The numeral 14 denotes the prime mover, usually an internal combustion engine, which drives a gear 15, which meshes through a slot 16 with the ring gear 11 and drives the fan blade so as to suck the air through the tunnel or tube and assist in decreasing the head resist ancc.

It. is thought that the construction, utility and advantages of this invention will novs be quite apparent to those skilled in this art, without a more detailed description thereof. The present embodiment of the invention has been disclosed in detail merely by way of example, since in actual practice it attains the features of advantage enumerated as desirable in the statement of the invention and the above description.

I t will be apparent that changes in the details of construction, and in the combination and arrangement of parts may be resorted to, without departing from the spirit or 75 scope of the invention as hereinafter claimed or sacrificing any of its advantages.

Having thus described my invention, what I claim as new is:

1. In combination, an aeroplane fuselage, a tube extending longitudinally through the aeroplane fuselage and open at both ends, the forward end of the tube bein provided with a pair of internal annu ar spaced flanges, a ring, bearings disposed exteriorly of the ring, means for mounting the hearings on the ring, said bearings being ridable between the flanges, bolts extending from the ring inwardly of the tube, a ring gear supported by said bolts, fan blades extending across the ring, and means for operating the ring gear.

2. In combination, an aeroplane fuselage. a tube extending longitudinally through the aero lane fuselage and 0 en at-both ends, the orward end of the tu e. being rovided with a pair of internal annular spaced ilanges, a ring, bearings disposed exteriorly of the ring, means for mounting the hearings on the rings, said bearings being ridable between the flanges, bolts extending from the ring inwardly of the tube, a ring gear supported by said bolts, fan blades extending across the rin said tube being rovided with a slot and a drive gear exten ing through the slot and meshing with the ring ear.

In testimony whereof I a x my signature.

JOSEPH MILLER.

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