Streamlined body and combustion apparatus
View Patent ↗The invention relates to a streamlined body for influencing the flow dynamics of a fluid, wherein the streamlined body at least partly corresponds to a rotationally symmetrical airfoil. A streamlined body of this kind can be used in a number of ways, for example as an impact member, as a flow regulator or as a heat exchanger. It also evens out and accelerates flows. It is used to particular advantage in a mixing and reaction chamber for burning fuels.
1. A streamlined body for influencing flow dynamics of at least one of a flowing fluid or of particles carried by a flowing fluid, comprising:
a body shaped as a solid of revolution of an upper profile of an airplane wing profile,
the upper profile being defined by a continuously convex curve from a front stagnation point of the airplane wing to a rear stagnation point of the airplane wing, and a profile chord extending from the front stagnation point to the rear stagnation point;
the solid of revolution formed by rotating the upper profile about a central axis coinciding with the profile chord such that the solid of revolution forms a substantially blunt first end at the front stagnation point and a pointed second end at the rear stagnation point.
2. The streamlined body of claim 1 , wherein the streamlined body is configured such that when placed with the profile chord in a direction of fluid flow, a suction effect is produced in the direction of fluid flow.
3. The streamlined body of claim 1 , wherein the streamlined body is heat-conducting and acts as a heat exchanger in a fluid flow with a temperature gradient.
4. The streamlined body of claim 1 , additionally comprising: a reaction chamber for enveloping the streamlined body and including a longitudinal axis extending therethrough, the streamlined body being arranged with the profile chord substantially parallel to the longitudinal axis of the reaction chamber.
5. The streamlined body of claim 4 , wherein the second end of the streamlined body is arranged downstream with respect to a direction of fluid flow in the reaction chamber.
6. The streamlined body of claim 5 , wherein the streamlined body is configured to separate, distribute, or atomise gaseous, liquid or solid constituents present in a fuel mixture of the fluid flow.
7. The streamlined body of claim 6 , wherein the substantially blunt first end is configured for slowing down the constituents of the fuel mixture to increase a residence time of these constituents and to mix these constituents more thoroughly.
8. The streamlined body of claim 6 , wherein the streamlined body is configured for accelerating the flow of the fuel mixture and combustion products in the reaction chamber downstream.
9. The streamlined body of claim 4 , wherein the reaction chamber includes at least one inlet port and the streamlined body is spaced apart from the at least one inlet port at a predetermined distance.
10. The streamlined body of claim 1 , wherein the substantially blunt first end acts as an impact surface for the fluid flow.
11. The streamlined body of claim 1 , wherein the body is configured to entrain the flowing fluid or the particles into a laminar flow.
12. A streamlined body for influencing the flow dynamics of at least one of a flowing fluid or of particles carried by a flowing fluid, comprising:
a body shaped as a solid of revolution of a top side of an airplane wing profile about a profile chord of the profile;
the top side being defined by a continuously convex curve from a front stagnation point to a rear stagnation point of the airplane wing profile and the profile chord extending from the front stagnation point to the rear stagnation point;
the body being defined by revolution of the top side, along the profile chord, about a central axis of the body;
such that the solid of revolution forms a substantially blunt first end corresponding to the front stagnation point and a pointed second end corresponding to the rear stagnation point.
13. The streamlined body of claim 12 , wherein the rotational axis is oriented in a direction of flow in an otherwise free cross section of flow to produce a suction effect in the direction of flow.
14. The streamlined body of claim 12 , wherein the streamlined body includes a heat-conducting material that causes the streamlined body to act as a heat exchanger in a fluid flow with a temperature gradient.
15. The streamlined body of claim 12 , wherein the streamlined body is configured to act as a flow regulator.
16. The streamlined body of claim 12 , wherein the substantially blunt first end acts as an impact surface for the fluid flow.
17. The streamlined body of claim 12 , wherein the body is configured to entrain the flowing fluid or the particles into a laminar flow.
18. A method for influencing flow dynamics of at least one of a flowing fluid or of particles carried by a flowing fluid, comprising:
providing a streamlined body shaped as a solid of revolution of an upper profile of an airplane wing profile, the upper profile being defined by a continuously convex curve from a front stagnation point of the airplane wing to a rear stagnation point of the airplane wing, and a profile chord extending from the front stagnation point to the rear stagnation point, the solid of revolution formed by rotating the upper profile about a central axis coinciding with the profile chord such that the solid of revolution forms a substantially blunt first end at the front stagnation point and a pointed second end at the rear stagnation point; and
placing the streamlined body within the flowing fluid.
19. The method of claim 18 , wherein the step of placing the streamlined body within the flowing fluid comprises utilizing the substantially blunt first end as an impact surface for the particles.
20. The method of claim 18 , wherein the step of placing the streamlined body within the flowing fluid comprises utilizing the streamlined body to produce laminar flow of the flowing fluid.
21. A reactor comprising:
a vessel including a cylindrical main portion in communication with an outwardly tapered head portion terminating in an outlet opening, an inner chamber for accommodating fluid flowing therethrough, at least one inlet port extending at least into the inner chamber defined by the cylindrical main portion, and a longitudinal axis extending through the vessel; and,
a streamlined body within the inner chamber for influencing the flow dynamics of at least one of a flowing fluid or of particles carried in a flowing fluid, the streamlined body shaped as a solid of revolution of an upper profile of an airplane wing profile, the upper profile being defined by a continuously convex curve from a front stagnation point of the airplane wing to a rear stagnation point of the airplane wing, and a profile chord extending from the front stagnation point to the rear stagnation point
the solid of revolution having an outer surface formed by rotating the upper profile about a central axis coinciding with the profile chord such that the solid of revolution forms a substantially blunt first end at the front stagnation point and a pointed second end at the rear stagnation point,
the streamlined body producing laminar flow of at least one of the flowing fluid or of the particles carried by the flowing fluid along the outer surface.
22. The reactor of claim 21 , wherein the streamlined body is spaced apart from the at least one inlet port at a predetermined distance, for fuel from the at least one inlet port to impact the outer surface.
23. The reactor of claim 22 , wherein the profile chord defines an axis of symmetry for the streamlined body and the longitudinal axis defines an axis of symmetry for the interior chamber of the vessel.
24. The reactor of claim 21 , wherein the cross-sectional shape of the airplane wing is configured to entrain fluids and any particles carried by the fluids into the laminar flow.
25. A reactor comprising:
a vessel for supporting ignition of fuel and fluid flow therethrough, the vessel including at least one inlet port and at least one outlet opening; and
a streamlined body within the vessel positioned intermediate the inlet port and the outlet opening, the streamlined body shaped as a solid of revolution of an upper profile of an airplane wing profile, the upper profile being defined by a continuously convex curve from a front stagnation point of the airplane wing to a rear stagnation point of the airplane wing, and a profile chord extending from the front stagnation point to the rear stagnation point,
the solid of revolution having an outer surface formed by rotating the upper profile about a central axis coinciding with the profile chord such that the solid of revolution forms a substantially blunt first end at the front stagnation point and a pointed second end at the rear stagnation point, the streamlined body including a rotationally symmetric surface for causing laminar flow of the flowing fluid and any particles in the flowing fluid along the streamlined body.
26. The reactor of claim 25 , wherein the streamlined body is spaced apart from the at least one inlet port at a predetermined distance, and the rotationally symmetric surface acts as an impact surface for distributing fuel from the at least one inlet port.
27. The reactor of claim 25 , including a longitudinal axis extending through the vessel and the profile chord is coincident with the longitudinal axis.
28. The reactor of claim 25 , wherein the streamlined body is configured to entrain fluids and any particles carried by the fluids into the laminar flow.