US1621918A

US1621918A - Wing-nose radiator

Info

Publication number: US1621918A
Application number: US703359A
Authority: US
Inventors: Paul G Zimmermann; Boris V Korvin-Kroukovsky
Original assignee: HEALEY AEROMARINE BUS Co
Current assignee: HEALEY AEROMARINE BUS Co; HEALEY-AEROMARINE BUS COMPANY Inc
Priority date: 1924-04-01
Filing date: 1924-04-01
Publication date: 1927-03-22
Anticipated expiration: 1944-03-22

Description

WING NOSE RADIATOR Filed April 1. 1924 2 Sheets-Sheet l March 22,1927. 1,621,918

I P. G. ZIMMERMANN ET AL WING NOSE RADIATOR Filed April 1. 1924 2 Sheets-Sheet 2 WM/ ma g 1 ATTOH/VE Patented Mar. 22,1927.

UNITED STATES PATENT OFFICE.

ram. e. zmunmnunnn B6315 v. xonvm-xnouxovsxr, or narrow, new annsnir, assrenons, BY mnsnn ASSIGNMENTS, 'ro HEALEY-AEBOHABINE nus comm, me, a conrona'rioiv or NEW YORK.

WING-NOSE namaron.

The invention. relates to airplanes, and particularly to the radiator for cooling the cooling water of the engine driving the propeller. The object is to provide a radiator which operates in an nnproved man-V her, besides being advantageously incorporated in the machine with respect to the functions of support and night. The invention comprises a rad ator disposed in the n nose of an aerofoil. The radiator is seetional and flexibly articulated, and other features relate to the construction of the sections, and devices for holding the sections in place and together and Ior permitting removal and replacement or any section.

lathe accompanying drawings illustrating the invention:

Fig. l is a side elevationhaving an intermediate portion broken out, showing the engine and its cooling system in relation to a wing having the radiator in its nose;

Fig. 2 is a Iragmentary plan View or the wing with intermediate portions of the part shown broken out for economy or space;

Fig. 3 is a vertical transverse section on an enlarged scale through the forward part of the wing and the radiator, dotted lines illustrating how the retaining bands may be opened;

Fig.

4 is a section on the irregular line 7 4-4 of Fig.3, through the adjoining ends of two of the radiator sections; and

Fig. 5 is a fragmentary front elevation :.t the same region. 7

The engine of the airplane is seen at.2 in Fig. 1, and 3 is the hot-water pipe leading" from the engine water-jacket, and 4 is the return pipe leading back from the radiator. These-two pipes connect with a duplex leg 5 of streamline form, which extends upward to the forward art of the wing 6. A septum 7 divides is leg into passages 3 and 4 iorming continuations of the pipes 3 and 4, and the leg may be prolonged upwardly through the wing to form a filling neck 8. The forwardspar of the wing is indicated at 9, and the nose of the wing in front-ht the spar is provided with a longitudinally extending recess defined by suitable back and bottom seat members 10, ll againstwhich the radiator 12 for-min the nose rests.

The radiator extea longitudinally ci the nose in opposite directions from the "the

members

10, 11. At the adjoining ends leg 5, the half of the radiator included in Fig. 2 being shown as extending as far as the position of the gasoline tank 13.

Each half of the radiator is composed of a plurality of separate sections 14. Fig. 2 indicates the one half as being composed or two sections, though this may be varied. The sections will be understood as being substantially larger than is actually shown in Fig. 2, where the limited space has neoe?s-. sitated shortening up the wing by breaking out a large part or its area. The several sections or the radiator are flexibly and separably connected with each other and with the central section let forming an enlargement of the leg 5, this section is" having two

chambers

15 and 16 which commumcate, fespectively, with, the two passages of the eg. 7

As clearly illustrated in Figs. 3 and 4 each radiator section is made with front and rear

water chambers ortanks

15 and 16 and an interposed cellular core 17 having upwardly and rearwardly inclined air-passages l8 therethrough, with narrow water spaces between the air spaces through which the water finds its way from the chamber 15 to the chamber'lfi. The cores are advantageously made of cartridge tube construction. The sections are 012 wing-nose form, and the rear tank is shaped to seat against of the sections, including the central leg section 14, are flexible, telescopic circulatory oints comprising necks 19' projecting from the water chambers of one section, and inwardly flanged sockets 20 in the end walls of the chambers of the other section. I Gaskets 21 around the necks compressed between the beveled flanges of" the sockets and the wall at the base of the necks make the joints water-tight, yet the construction is one that permits of suflicient angular movement of the sections relatively to each other to conform to and give with the aero-foil without straining the radiator.

The sections of the radiator are drawn. together by means otfasteriings consisting of bracket lugs 23 fixed to the upper an lower sides of the sections at the ends, and

bolts 24 passed through perforations in the adjacent limbs 25 of these brackets and eqfiped with nuts 26.

jeaections 1a are held in place by upper purpose and lower

flexible metal straps

27, 28, the rear ends of which are fixed, respectively, to the upper and lower parts of the aerofoil. These straps embrace the radiator sections at the ends of the sections, and the forward ends of the complementary straps are formed with interfitting eye loops 29 through which are passed fastening pins 30. As shown in Fig. one of these pins may be employed with advantage to serve the adjacent retaining straps of two sections,

and it will be kept from coming out by a cotter pin 31. The straps overlie the basal limbs 32 of the brackets 23 of the fastenings which draw the sections together, these limbs having out-turned ends 33 so that the straps are confined laterally between said ends and the limbs 25. This engagement of the retaining fastenings, which are fixed to the body of the aerofoil, with projections or recesses on the radiator sections consolidates the general structure and resists relative dislacement longitudinally ofthe wing, or aterally with respect to the straps.

Fig. 3 indicates in dotted lines how the straps can open when 'unfastened so as to permit the removal of one or more of the sections. Such removal may be for'the purpose of re lacement and re air, or for the reducing the ra iating capacity. The-latter purpose can also be..attained by opening the radiator and plugging circulatory connections between sections, so as to block one or more of the sections out of circuit.

It will be perceived that with our radiator the cooling is dependent on the angle of attack rather than on speed alone, and 'that thereby the cooling conforms more truly to the varying needs of the engine. 7 As the angle is flattened the region of greatest vacnum efiect above the nose shifts rearward, and thereby the flow of air through the air passages of the core is affected.

What we claim as new is:

1. in an aerofoil, an engine-cooling radiator comprising a front water chamber, a

rear water chamber and an interposed core having upwardly inclined air' passages extending upwardly therethrough, the whole being embodied within and of a form with the nose of the aeroifoil.

2. A. radiator occupying the nose of an aerotoii and composed ct, separate sections havin water chambers and interposed cores of cellular construction providing 12 wardiy extending air-passages, with fiexihe tel scopic joints between the water chambers of adjoining radiator sections, substantially as set forth.

3. An aerofoil, and a radiator of flexibly articulated sections extended along the nose of the aerofoil.

4. A wing-nose radiator composed of separate sections having front and rear water chambers and interposed cellular cores with upwardly extending air passages, -flexible ings separably connecting the ends of said bands.

6. In combination with an aerofoil having its nose recessed, a radiator of wingnose form seated in the recess of the nose and forming the nose of the aerofoil, said radiator composed of separate sections having upwardly extending air passages therethrough, circulatory connections between the sections, and means for securing the sections, substantially as set forth.

7. An aeroi'oil having a longitudinally rccessed nose, and a, radiator lying in said recess composed of separate, removable, flexibly connected sections, with upwardly extending air passages therethrough.

8. An aerofoil having its nose longitudinally recessed, a radiator seated in said recess, flexible bands secured to the upper and lower portions of the aeroi'oil to embrace and hold. the radiator in place, and fastenings separably connecting the ends oi said bands.

9. in combination with an aeroioil having its noserecessed in front, a radiator composed of separate sections seated in said recess, retaining straps secured to the aerofoil and embracing the sections, and projec" tions on the sections with which the stra )S are engaged preventing displacement, su stantially as set forth.

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