Means for enhancing combustion efficiency in internal combustion engines

Claim 2

In an internal combustion engine according to claim 1, said turbine being mounted in said inlet portion of the intake manifold.

Claim 3

In an internal combustion engine according to claim 1, said turbine being mounted between said downdraft side of the carburetor and said inlet portion of the intake manifold.

Claim 4

In an internal combustion engine according to claim 4, said means comprising a gasket clamped between said downdraft side of the carburetor and said inlet portion of the intake manifold and having diametrically opposed notches therein, a bar extending across said conduit and registering in said notches, said turbine being mounted on a pin centrally positioned on and extending from said bar.

Claim 5

In an internal combustion engine according to claim 5, said notches extending part way upward through the bottom surface of said gasket, said turbine being positioned below said bar.

Claim 6

In an internal combustion engine according to claim 1, said conduit having a bar extending thereinto along a diameter thereof and having a pin thereon positioned along the axis of the conduit, said turbine being rotatably mounted on said pin.

Claim 7

In an internal combustion engine according to claim 7, said bar having a ring thereon positioned at said axis of the conduit, said pin extending through the passage through said ring.

Claim 8

In an internal combustion engine according to claim 1, said downdraft side of the carburetor having a cylindrical sleeve of reduced diameter supported coaxially therein, webs extending from opposite sides of said sleeve and secured to the wall of said conduit for supporting said sleeve, said means comprising a yoke which includes a base portion and two forked legs extending upward from said base portion, each of said webs registering in one of said forked legs, the extremities of said legs extending beyond the upper edges of said webs, said extremities being pinched together above said webs to support said yoke, said base portion having a pin thereon, said turbine being rotatably mounted on said pin.

Claim 9

In an internal combustion engine according to claim 1, said downdraft side of the carburetor having the lower portion of the internal wall thereof tapering in an upward direction, said means comprising a complementarily tapering hoop force fixed within said tapering wall, a diametrical bar extending across said hoop, said bar having a pin extending from the center thereof, said turbine being rotatably mounted on said pin.

Claim 10

In an internal combustion engine according to claim 1, said second set of blades having a zero tilt with respect to said axis of the turbine.

Claim 11

In an internal combustion engine according to claim 1, said second set of blades having a reverse tilt with respect to said axis of the turbine which is anywhere within a range between zero degrees and 5*.

Claim 12

In an internal combustion engine according to claim 1, said second set of blades having a tilt which is at an angle in a direction reverse to the direction of the tilt of said first set of blades, said reverse angle of said second set of blades lying within a range which extends between a small fraction of a degree in excess of zero as a minimum and 5* as a maximum.

Claim 13

In an internal combustion engine according to claim 1, said second set of blades having a tilt which is at an angle in a direction reverse to the direction of the tilt of said first set of blades, said reverse angle of said second set of blades lying within a range which extends between a small fraction of a degree in excess of zero as a minimum and at least 5* as a maximum.

Claim 14

In an internal combustion engine which includes a carburetor and an inlet portion leading into the intake manifold of the engine whereby the downdraft side of the carburetor and said inlet portion together constitute a continuous conduit, means for improving the intermixing of fuel and air prior to entrance into said manifold consisting of a turbine mounted in said conduit in a position wherein the axis of the turbine is longitudinal with respect to the direction of flow of the mixture of fuel and air, said turbine having an even number of a first set of blades each of which has a tilt with respect to said axis at an angle sufficient to direct said mixture in a helical path through the turbine while the turbine is rotating, said turbine having a like even number of a second set of blades each of which is positioned between two of said first set of blades, said second set of blades lying at an angle with respect to said first set of blades, said last-named angle ranging between zero angle with respect to said axis and Approximately 5* with respect to said axis in a direction reverse to the direction of tilt of said first set of blades, said first-named angle having a magnitude substantially larger than that of said last-named angle.