USRE18115E

USRE18115E - bellanca

Info

Publication number: USRE18115E
Authority: US
Publication date: 1931-06-30

Description

June 30, 1931.

s. M. BELLANCA EXHAUST. MANIFOLD Originia1 Fi1ed Sept. 1 1926" ZSheets-Sheet l v gwwmm fudge e J1me 1931- ca. M. BELLANCA EXHAUS T MANIFOLD t z Filed S p 192s 2 Sheets-Sheet 2 gwuentoz fiz'weppe Mafiafiel/azw Reissued June 30, 1931 I UNITED STATES PATENT GUISEPPE u. BELLA'NcA,

emu: coapoaamon,

OF NEW GA STLE,' DELAWARE, ASSIGNOR TO BELLANGA AIR- OF NEW CASTLE, DELAWARE, A CORPORATION OF DELAWARE EXHAUST MANIFOLD Original No. 1,713,814, dated May 21,1929, Serial No. 135,710, filed September 16, 1926. Application for reissue filed March 27, 1930.

This invention relates to the construction and mounting of an exhaust manifold for aeronautical engines.

In the development of airplanes in connection with which engines of the radial and other more or less similar types are used, considerable difficulty has been found in so mounting the exhaust manifold that it will not present a substantial surface area to produce air resistance and a corresponding restriction in speed of flight of the airplane.

This difliculty arises out of the necessity for mounting the exhaust manifold outside the chamber formed by the shell of the fuselage 16 and in a disposition substantially encircling the cowl portion of the fuselage transversely to the direction of flight. The manifold by thus extending across the line of flight, presents its forward surface throughout its length to the resistance of the air.

A general object of the present invention is to provide an exhaust manifold for radial aeronautical engines which will be free from the objectionable features referred to and which will provide a minimum amount of 'air resistance.

Further objects of the invention are to minimize the eifects of the noise produced by the discharging exhaust, to prevent overheating of the manifold, and to prevent buckling or distortion of the parts under expansion efl'ects arising out of temperature changes.

The invention includes the mounting of the exhaust manifold in a recess or channel formed" in the surface'of the engine cowling, the manifold being thereby partly or wholly protected from engagement of the rushing air therewith.

Another feature of the invention is the mounting of the manifold in a spaced apart relation to the surface of the receiving channel so that air can flow through the space between the manifold and channel surface to produce a cooling effect on the manifold and prevent overheating thereof.

Another feature of the invention is that the manifold is allowed to project slightly outside of the surface of the cowling so as to intercept a part of the air current and direct in the use of flexible Serial No. 439,520.

it through the space between and the channel surface.

Another feature of the invention resides in the provision of an exhaust manifold having a formation in cross-section such as will provide a minimum air-resistanee area.

Another feature of the invention resides joints in the manifold structure to prevent injury to the parts by expansion and contraction effects.

Still another feature of the invention resides in an adaptability of the manifold structure to be mounted in various positions to cause the'exhaust to be discharged at any desired point inthe length of the manifold structure. i

Other features of the invention will be hereinafter referred to.

In the drawings, in which a preferred em bodiment of the invention has been selected for illustration,

Figure l is a diagrammatic view showing a portion of the forward end of an airplane equipped with an exhaust manifold construction embodying the invention.

Figure 2 is a sectional view on an enlarged scale taken on the line 22 of Figure 1.

v Figure 3 is a detail view in perspective showlng the telescoping joint used in my improved manifold.

Figure 4 is a detail view in perspective showing the flexible joint used in the branches of my improved manifold.

Figure 5 is a view in perspective showing the manifold structure detached from the engine cowlingandpresenting a rearward view thereof.

Figure 6 is a sectional view. of a modification of Figure 2.

Referring to the drawings for a more .detailed description of the invention, at 10 is shown the engine cowling portion of the fuselage of an airplane through openings 11 in which the cylinders 12 of an engine of the radial type protrude. The forward portion of the cowling 10 is equipped with a cap member or fairing 13 designed to decrease the effect of air resistance acting on thehub portions of the propeller 14.

In order to dispose of the exhaust from the the manifold radially disposed cylinders 12 through a common discharge conduit an exhaust manifold 15 is made use of which is disposed in a substantially encircling relation to the cowl structure 10, the location of the manifold being just to the rear. of the positions of the engine cylinders 12. Branch pipe connections 16 are provided between the'exhaust discharge ports 17 of the engine cylinders 12 and the manifold 15, the manifold terminat-' ing in a discharge member 18 which is directed rearwardly and may be extended for any desired distance along an outer wall of the fuselage. i Y

' In order to cause the manifold'to present a minimum area of surface to prevent air resistance the manifold is mounted in a recess or groove 19 formed in the outer surface of theengine cowling 10. The groove or recess 19 extends circumferentiall around the entire surface of the cowl an this disposition of the groove provides for the mounting of themanifold 15 in any desired angular relation" to the cowl so as to cause the discharge member 18 to be located at the most convenient point. In Figure 1 of. the drawin the dischar e member '18 of' the manifo d is shown 'sposed beneath the floor wall of the fusela c, this location of the dischargeterminal eing useful in overcoming the effect of noises produced by the exhaust on the occupants of the compartments in the fuselage. 6

It will be clear that the manifold 15 may.

rotatably adjusted within the groove 19 to cause the terminal discharging member 18 to be disposedalong either side of the fuselage or at a point to discharge above the fuselaggand the supporting win :or plane.

- thereby dissipate eat and order to revent over eating of the manifold and t e communication of heat to the adjacent surface of the cowl 10, the manifold is so mounted as to be slightly spaced apart from the adjacent surface of the groove or recess 19as is clearly shown in Figures 1.

and 2 of the drawings. The space 20 which is thus formed provides a passageway through which air can-flow, as is indicated by v the arrows in Fi re 2 of'the drawin to revent over eating of the ad acent parts. 11 order tofacilitate the rush of airvthrough the passageway It will also be noted that the cross-section 20 formed between the manifold 15 and the surface of the groove 19 the forward or leading edge 21 of the manifold is caused 'to protrude slightly be 0nd the adjacent outer su'r face of the cow 10'.to thereby function to provide a scoopin action on the air'stream rushing rearwar. y along the surface of the cowl 10. The air thus caught .or entrapped is diverted through the channel 20 as will be seen and produces the cooling effect referred or formation of the manifold member 15 is a \such as to present-a degree of re- For instance, a nose sistance to the air. In the drawings it will be noted that the manifold has the formation of a flattened tube with forwardly and rearwardly extending an les and a substantially flat, outer surface f0 lowing approximately the contour of the outer surface of. the cow] 10. While this particular formation has'been found effective in practice it will be apparent that other formations of the manifold crosssection may be employed with useful results.

Another feature of the invention resides in the use of flexible or yielding coupling elements in thebody structure of the manifold member and also in the branch pipes 16 through which connections are made between the manifold and the engine cylinders 12. Coupling members orjoints 22 are provided in the branch pipe connections 16 forthis purpose. These coupling members may take the form of split sleeves an example of which sleeve being provided with a clamping boltis shown in Figure 4 of the'drawings, the- 23 and having suitable corrugations 24 to prevent slipping of the coupling member from engagement with the joint sectionsof the branch exhaust pipes 16.

In order to provide for expansion or contraction of the manifold structure itself under changing temperature conditions a telescopic joint 25 is provided which permits of rela-,

tive movement of the contiguous sections of the manifold toward or from each other to ,7

thereby prevent distortion orother injury to the, manifold by the expansion and contraction effects due to changes in tempera-. ture. a

In certain types of construction it is possible that the addition of the exhaust manifold of my invention may interfere with the application and removal of the material of the cowl structure. To obviate this difliculty the construction indicated ilif \Figure 6 maybe used. In this embodiment "the cowl 10 of Figures 1 and'2 may be cut into portions. portion 26 may pro,-

vided, cooperatin with a recess portion 27,

in the recess of w ich the exhaust manifold 21 may be positioned. The manifold may 'be spaced away fromtlie member27 by a small distance as before to provide the passageway 20 for cooling air. This construction permits theready removal of the nose portion of the cowl for access to the engine members, or of the rear portion, or of the manifold .and grooved portion together.

As a further modification the cowl member may be separated "at two points as shown in Figure 6 to provide a noseporti'on 26,.a channel portion 27 and a rear portion 28.

This construction permits the removal of the.

nose portion. and the rear portion of the cowl independently of the exhaust manifold and i of the recess} portion. This modification of the construction provides meansv for a more in said manifold whereby to provide for ex-.

convenient and easy structures. 4

It will-be seen that a manifold structure and a method of mounting the same have been provided which overcomes or obviates the air resistance effects which are ordinarily encountered in the use of a manifold structure which must be disposed transversely to the line of flight of the airplane on which it is carried.

The language and expressions which have been employed throu hout the specification are used as terms 0 description only and not of limitation, and such terms are intended to include all the e uivalents and such modifications as are possi 1e to be employed within the scope of the invention claimed.

I claim: 1. In an exhaust manifold construction for aeronautical engines of'the radial type,

access to the engine a cowl through which the exhaust discharging ends of the radially disposed cylinders project, said cowl being provided with a circumscribing groove in its outer surface adjacent the engine cylinders, an exhaust manifold mounted insaid groove and adjustable circumferentially therein, and a discharge terminal on the exhaust manifold.

2. In an exhaust manifold construction for aeronautical engines of the radial type, a cowl through which the exhaust discharging ends of the radially disposed cylinders project, an exhaust manifold for said cylinders mounted in circumscribing relation to the cowl, and said manifold being formed with flattened cross-section with its edges ar-- ranged fore and aft to present a minimum degree of air resistance.

3. In an exhaust manifold construction for aeronautical engines of the radial type, a cowl through which the exhaust discharging ends of the radially disposed cylinders of the engine project, an exhaust manifold for said cylinders mounted in circumscribing rela tion to the cowl, branch pipe connections between the cylinders and the manifold, and flexible joint sections contained in said branch pipe connections. 4

4. In an exhaust manifold construction for aeronautical engines of the radial type, an exhaust manifold for the engine cylinders mounted in an encircling disposition with relation to the longitudinal axis of the airplane, said manifold being circumferential 1y adjustable to vary the position of the d1scharge terminal, a yielding joint connection pansion and contraction effects, and said manifold having a flattened cross-sectional formation designed to present a minimum of air resistance.

5. In an exhaust manifold construction for aeronautical engines of the radial type, a cowl through which the exhaust discharging ends of the radially disposed cylinders project, said cowl being provided with a circumscribing groove in its outer surface adgroove to permit a current of air to pass therethrough, a flexible joint in said manifold, branch pipe connectionsbetweeii said cylinders and said manifold, and flexible joint sections in said branch connections.

6. In an exhaust manifold construction for aeronautical engines, a cowl for the engine provided with a circumferential groove in its outer surface, an exhaust manifold mounted in and extending along said groove, said manifold having its underside formed in complement to the formation of the surface of the groove but spaced therefrom, the outer surface of the manifold being substantially flat and conforming approximately to the formation of the cowl ward edge of the manifold protruding slightly beyond the contour of the cowl surface whereby to deflect air through the space between the manifold and the surface of the groove.

7 In an exhaust manifold construction for aeronautical engines of the radial type, a cowl through which the exhaust discharging ends of the radially disposed cylinders project, said cowl being provided with a circumscribing groove in its outer surface adjacent the engine cylinders, said cowl comprising separable portions, whereby a part thereof may be removed independently of said exhaustmembers, an exhaust manifold mounted in said groove, said manifold being circumferentially adjustable in said groove and spaced from the walls of the groove to permit a current of air to pass therethrough, a flexible joint in said manifold, branch pipe connections between said cylinders and said manifold, and flexible joint sections in said branch connections. i

8. In anexhaust manifold construction for aeronautical engines of the radial type, a cowl through which the exhaust discharge end of the radially disposed cylinders project,

an exhaust manifold for said cylinders mounted in circumscribing relation to the cowl, said manifold being flattened in' cross section with its longer dimension extending fore and aft and substantially flush with the cowling.

9. In an airplane, cowl for covering the forward portion of the airplane, said cowl surface, and the forthe airplane, said cowl being provided with a circumferential groove in its outer surface, and an exhaust manifold nested within said groove and being :so formed that its outer surface forms substan- I a tially a continuation of the outer surface of -thecwl.

11. In an airplane, a cowl for covering the forward portion of the airplane, said cowl being provided with a circumferential groove n in its outer surface, and an exhaust manifold nested within said groove and being so formed that its outer surface forms substantially a continuation of the outer surface of Y the cowl and its leading edge projects slightly 1 outside the surface of the cowl.

12. A circular exhaust manifold for radial and similar engines, said manifoldha'ving a flattened cross section, the shortest dimension of its cross section being radial, adapted to 2.0 fit in a cowling groove with the'outer surface substantially flush with the surface thereof. 13. An exhaust manifold having the outer surface thereof substantially flush with, and forming a substantial continuation of an airplane cowling, the manifold being positioned with re t to the cowling to direct air over the enti e surface of the manifold.

' 14. In an airplane, a cowl covering the forward portion thereof, said cowl being provided with a circumferential depression in its outer surface, and an exhaust manifold nested within said depression and being so formed that its outer surface forms substantially a continuation of the outer surface of 86' the cowl. a 15. An exhaust manifold having the outer I I surface thereof flattened and substantially fiush with and forming a substantial continuation of an airplane cowling, the manifold 40 having a single exhaust outlet, and being so positioned with respect to the cowling as to allow for the direction of a current of air over substantially the entire surface thereof. 16: A circular exhaust manifold for radial '45 and similar engines, said manifold having a. flattened'cross section, the shortest dimension of its cross section being radial, one face being-adapted to fit in a depression in an air-' plane cowling, and the other face adapted to be substantially flush with, and forming a continuation of the cowling surface.

In" testimony whereof I afiix my si ature. GUISEPPE M. BELLA CA.