Persistent vortex generating high regression rate solid fuel grain for a hybrid rocket engine and method for manufacturing same
An additively manufactured solid fuel grain for a hybrid rocket engine having a cylindrical shape, defining a center combustion port and comprising a stack of fused layers of polymeric material suitable for hybrid rocket fuel. Each layer is formed as a plurality of fused abutting concentric beads of solidified material arrayed around the center port. An oxidizer is introduced into the solid fuel grain through the center port, with combustion occurring along the exposed surface area of the solid fuel grain center port wall. Each concentric bead possesses a surface pattern that increases the combustion surface area and when stacked forms a rifling pattern of undulations that induces oxidizer-fuel gas axial flow to improve combustion efficiency. The port wall surface pattern persists during the rocket engine's operation as the fuel phase changes from solid to gas and is ablated.
1. A method of making a fuel grain for a hybrid rocket engine, the method comprising:
forming a first layer of grain material further comprising a plurality of concentric circular beaded ring-shaped structures of different radii fused together to form a cylindrically-shaped disc and defining a central opening therein;
forming a plurality of additional layers of grain material each comprising a plurality of concentric circular ring-shaped beaded structures of different radii fused together to form a cylindrically-shaped disc and defining a central opening therein;
the first layer and the plurality of additional layers of cylindrically shaped discs having a substantially equal outer and inner diameter or non-equal outer and inner diameter;
stacking and fusing the first layer and the additional layers together to form the fuel grain such that the central opening of the first layer and each of the additional layers is aligned to form a center combustion port extending through the fuel grain;
wherein the grain material includes at least one chemical component suitable for a hybrid rocket propulsion combustion reaction,
each one of the plurality of concentric circular ring-shaped beaded structures of the first layer and each one of the plurality of concentric circular ring-shaped beaded structures of the additional layers having an outer circumference defining undulations therein and an inner circumference defining undulations therein; and
wherein the undulations present a larger surface area available for combustion within the center combustion port and provide an increased regression rate of the fuel grain material relative to a fuel grain lacking such undulations.
2. The method of claim 1 wherein a material of each concentric circular ring-shaped beaded structure comprises a solidified material, further comprising a polymer or a solidified polymer-metal blend formulation.
3. The method of claim 1 wherein a material of each concentric circular ring-shaped beaded structure comprises Acrylonitrile Butadiene Styrene (ABS).
4. The method of claim 1 wherein a material of each concentric circular ring-shaped beaded structure comprises a blend of Acrylonitrile Butadiene Styrene (ABS) and aluminum powder.
5. The method of claim 1 wherein the steps of forming the first layer and forming the plurality of additional layers are performed on an additive manufacturing apparatus.
6. The method of claim 1 wherein the steps of forming the first layer and forming the plurality of additional layers are performed on a fused deposition modeling type machine.
7. The method of claim 1 wherein the steps of forming the first layer and forming the plurality of additional layers are performed by depositing a viscous polymer extruded along a circular or irregular closed path.
8. The method of claim 1 wherein a cross-sectional shape of each extruded ring-shaped bead of grain material comprises an elliptical shape having minor elliptical axis extending parallel to the center combustion port.
9. The method of claim 8 wherein the additive manufacturing apparatus allows placement of grain material in three dimensions.
10. The method of claim 1 wherein the plurality of undulations form a progressive twist through the center combustion port thereby forming a helical grooved rifling pattern of undulations to induce a swirling gaseous flow within the center combustion port.
11. The method of claim 1 wherein a shape of the center combustion port comprises a circular shape, an oval shape, a polygonal shape, a quatrefoil shape, a star shape, or an irregular shape.
12. The method of claim 1 wherein the center combustion port is polygonal in shape with each layer's orientation adjusted to create a progressive helical twist thereby, forming a rifling pattern to induce a swirling gaseous flow within the center combustion port.
13. The method of claim 1 wherein the undulations comprise one or more of a corrugation pattern, a truncated pyramidal pattern, a rifled truncated pyramidal pattern, or a rifled polygonal pattern.
14. The method of claim 1 wherein the plurality of fused concentric circular ring-shaped beaded structures forming a first layer and the fused concentric circular ring-shaped beaded structures forming additional layers, in their plurality forming a cylindrically shaped fuel grain has an outer diameter of about 19.0 inches and the center combustion port has an initial diameter of about 4 inches prior to consumption of the fuel grain material during a combustion process.
15. The method of claim 1 wherein the first layer and each one of the plurality of additional layers has a thickness of between about 0.005 inches and 0.25 inches.
16. The method of claim 1 further comprising a step of assembling multiple fuel grain sections into a complete multi-section fuel grain.
17. Forming a fuel grain segment according to the method of claim 1 further comprising vertically orienting a plurality of the fuel grain segments and disposing viscous ABS material between a lower surface of a first fuel grain segment and an upper surface of an abutting second fuel grain segment to fusion bond the first and second segments.
18. The method of claim 1 wherein the first layer and the plurality of additional layers are substantially uniform in material composition.
19. A method of constructing a hybrid rocket fuel grain comprising steps of:
(a) using an additive manufacturing process, forming a first layer of oxidizer free grain material;
(b) forming a succession of additional layers of oxidizer free grain material, each successive layer bonded to an adjacent layer; and
(c) abutting the fuel grain to the rocket nozzle or post-combustion chamber;
wherein the oxidizer free grain material includes at least one chemical component suitable for a hybrid rocket propulsion combustion reaction, the layers forming a fuel grain having at least one combustion port;
wherein each of the first layer and the additional layers comprises a plurality of fused concentric circular ring-shaped beaded structures each forming a cylindrically shaped disc of substantially equal outer and inner diameter, laterally stacked and bonded together to form a hybrid rocket fuel grain with each layer defining undulations therein; and
wherein the pattern of undulations presents a center port wall presenting a larger surface area available for combustion and as each concentric circular ring-shaped beaded structure is consumed during combustion, the next outer concentric circular ring-shaped beaded structure is revealed and available for combustion, thus producing an increased regression rate of the fuel grain relative to a fuel grain lacking such pattern of undulations.