Pulsed detonation engine

1. A method of operating a pulsed detonation engine comprising:

providing a pulsed detonation engine comprising:

a detonation tube configured to receive gaseous fuel and an oxidizer to be detonated therein, wherein the detonation tube comprises a perimeter wall, an upstream end, a downstream end, a longitudinal axis extending from the upstream end to the downstream end, and an axially extended portion extending along the longitudinal axis from the upstream end to the downstream end;

one or more fuel-oxidizer injectors configured to inject the gaseous fuel and the oxidizer into the detonation tube, wherein the one or more fuel-oxidizer injectors are disposed at the upstream end and the perimeter wall along the axially extended portion of the detonation tube, wherein the one or more fuel-oxidizer injectors defines an array of orifices having a central orifice and a plurality of elongate orifices substantially surrounding the central orifice, wherein the central orifice is defined at the geometric center of the one or more fuel-oxidizer injectors, wherein the central orifice has a central orifice axis perpendicular to the longitudinal axis of the detonation tube, wherein each of the plurality of elongate orifices defines an elliptical shape or an elongated circle shape and has an orifice axis at an acute angle relative to the central orifice axis, wherein the central orifice is configured to inject the gaseous fuel and oxidizer in a radial direction and wherein the elongate orifices are configured to inject the gaseous fuel and oxidizer in a direction having an axial and radial component into the detonation tube; and

an ignition configured to ignite the gaseous fuel and the oxidizer in the detonation tube so as to initiate detonation of the gaseous fuel and the oxidizer;

injecting the gaseous fuel and the oxidizer into the detonation tube via the one or more injectors; and

igniting the gaseous fuel and the oxidizer in the detonation tube so as to initiate detonation of the gaseous fuel and the oxidizer, wherein the gaseous fuel and the oxidizer are injected into the detonation tube both from the upstream end and along the axially extended portion of the detonation tube.

2. The method according to claim 1 , wherein at least one of the one or more fuel-oxidizer injectors is disposed along the axially extended portion and is inclined toward the downstream end of the detonation tube, and wherein the gaseous fuel and the oxidizer are injected into the detonation tube at least partly in a downstream direction of the detonation tube.

3. The method according to claim 1 ,

wherein the axially extended portion extends also from the longitudinal axis, at any point thereon, in a direction perpendicular to the longitudinal axis, to the perimeter wall,

wherein at least two of the one or more fuel-oxidizer injectors are disposed along the axially extended portion of the detonation tube at different angular positions on the perimeter wall, and

wherein the gaseous fuel and the oxidizer are injected into the detonation tube from different angular positions on the perimeter wall of the detonation tube.

4. The method according to claim 1 ,

wherein one of the one or more fuel-oxidizer injectors is an upstream fuel-oxidizer injector and another one of the one or more fuel-oxidizer injectors is a downstream fuel-oxidizer injector, wherein a first longitudinal distance between the upstream fuel-oxidizer injector and the upstream end is smaller than a second longitudinal distance between the downstream fuel-oxidizer injector and the upstream end,

wherein the pulse detonation engine further comprises, for each of the fuel-oxidizer injectors, a valve corresponding thereto configured to control the injection of the gaseous fuel and the oxidizer from the respective fuel-oxidizer injector into the detonation tube, and, for each of the valves, a controller corresponding thereto configured to control the respective valve so as to adjust the timing of the injection from the fuel-oxidizer injector corresponding to the respective valve, whereby phased injection may be performed, the phased injection comprising injecting of the gaseous fuel and the oxidizer into the detonation tube from the upstream fuel-oxidizer injector and, after commencement of the injecting from the upstream fuel-oxidizer injector, injecting of the gaseous fuel and the oxidizer into the detonation tube from the downstream fuel-oxidizer injector, and

wherein the gaseous fuel and the oxidizer are injected into the detonation tube first from an upstream fuel-oxidizer injector and, after commencement of the injecting from the upstream fuel-oxidizer injector, from a downstream fuel-oxidizer injector.

5. A pulsed detonation engine, comprising:

a detonation tube configured to receive gaseous fuel and an oxidizer to be detonated therein, wherein the detonation tube comprises a perimeter wall, an upstream end, a downstream end, a longitudinal axis extending from the upstream end to the downstream end, and an axially extended portion extending along the longitudinal axis from the upstream end to the downstream end;

a fuel-oxidizer premix chamber configured to premix the gaseous fuel and oxidizer prior to entry of the gaseous fuel and oxidizer into the detonation tube;

one or more fuel-oxidizer injectors configured to uniformly inject the pre-mixed gaseous fuel and the oxidizer from the pre-mix chamber into the detonation tube, wherein the one or more fuel-oxidizer injectors are disposed at the upstream end and along the axially extended portion of the detonation tube, wherein the one or more fuel-oxidizer injectors defines an array of orifices having a central orifice and a plurality of elongate orifices substantially surrounding the central orifice, wherein the central orifice has a central orifice axis perpendicular to the longitudinal axis of the detonation tube, wherein each of the plurality of elongate orifices defines an elliptical shape or an elongated circle shape and has an orifice axis at an acute angle relative to the central orifice axis, wherein the central orifice is configured to inject the pre-mixed gaseous fuel and oxidizer in a radial direction and wherein the elongate orifices are configured to inject the pre-mixed gaseous fuel and oxidizer in a direction having an axial and radial component into the detonation tube; and

an ignition configured to ignite the pre-mixed gaseous fuel and the oxidizer in the detonation tube so as to initiate detonation of the pre-mixed gaseous fuel and the oxidizer.

6. The pulsed detonation engine according to claim 5 ,

wherein the detonation tube comprises (a) a height extending in a vertical direction perpendicular to the longitudinal axis, and (b) a width extending in a horizontal direction perpendicular to the longitudinal axis, and

wherein at least one of the one or more fuel-oxidizer injectors is disposed along the axially extended portion and is inclined relative to the vertical direction and/or the horizontal direction.

7. The pulsed detonation engine according to claim 5 , wherein at least one of the one or more fuel-oxidizer injectors is disposed along the axially extended portion and is inclined toward the downstream end of the detonation tube.

8. The pulsed detonation engine according to claim 5 , wherein the axially extended portion extends also from the longitudinal axis, at any point thereon, in a direction perpendicular to the longitudinal axis, to the perimeter wall, and wherein at least two of the one or more fuel-oxidizer injectors are disposed along the axially extended portion of the detonation tube at different angular positions on the perimeter wall.

9. The pulsed detonation engine according to claim 5 , wherein the axially extended portion extends also from the longitudinal axis, at any point thereon, in a direction perpendicular to the longitudinal axis, to the perimeter wall, and wherein at least two of the one or more fuel-oxidizer injectors are disposed along the axially extended portion of the detonation tube in a staggered arrangement, whereby the at least two or more injectors are located at different positions in the direction of the longitudinal axis and at different angular positions on the perimeter wall.

10. The pulsed detonation engine according to claim 5 , wherein the plurality of elongate orifices are arranged around the central orifice in a shape that is at least partly curved.

11. The pulsed detonation engine according to claim 5 ,

wherein one of the one or more fuel-oxidizer injectors is an upstream fuel-oxidizer injector and another one of the one or more fuel-oxidizer injectors is a downstream fuel-oxidizer injector, wherein a first longitudinal distance between the upstream fuel-oxidizer injector and the upstream end is smaller than a second longitudinal distance between the downstream fuel-oxidizer injector and the upstream end, and

wherein the pulse detonation engine further comprises, for each of the fuel-oxidizer injectors, a valve corresponding thereto configured to control the injection of the pre-mixed gaseous fuel and the oxidizer from the respective fuel-oxidizer injector into the detonation tube, and, for each of the valves, a controller corresponding thereto configured to control the respective valve so as to adjust the timing of the injection from the fuel-oxidizer injector corresponding to the respective valve, whereby phased injection may be performed, the phased injection comprising injecting of the pre-mixed gaseous fuel and the oxidizer into the detonation tube from the upstream fuel-oxidizer injector and, after commencement of the injecting from the upstream fuel-oxidizer injector, injecting of the pre-mixed gaseous fuel and the oxidizer into the detonation tube from the downstream fuel-oxidizer injector.

12. The pulsed detonation engine according to claim 5 ,

wherein the axially extended portion extends also from the longitudinal axis, at any point thereon, in a direction perpendicular to the longitudinal axis, to the perimeter wall, and

wherein the pulsed detonation engine further comprises a cooling jacket surrounding at least a portion of the detonation tube, the cooling jacket comprising one or more flow channels extending in a direction of the perimeter wall.

13. The pulsed detonation engine according to claim 5 , further comprising:

a fuel heater configured to heat a liquid fuel to a temperature below its boiling point; and

a second heater configured to heat the oxidizer.

14. The pulsed detonation engine according to claim 5 , wherein a cross-section of the axially extending portion taken perpendicular to the longitudinal axis, at one or more points along the longitudinal axis, has a shape comprising, at least in part, one or more straight line sections.

15. The pulsed detonation engine according to claim 5 , wherein a jet ejected from a first orifice of the plurality of orifices has an angular extent that is different than the angular extent of a second orifice of the plurality of orifices.

16. The pulsed detonation engine according to claim 5 , wherein the pulse detonation engine further comprises:

for each of the fuel-oxidizer injectors, a rotary valve corresponding thereto configured to control the injection of the pre-mixed gaseous fuel and the oxidizer from the respective fuel-oxidizer injector into the detonation tube;

for each of the rotary valves, a controller corresponding thereto configured to control the respective rotary valve so as to adjust the timing of the injection from the fuel-oxidizer injector corresponding to the respective rotary valve; and

for each of the rotary valves, a corresponding stepper motor configured to independently drive each of the rotary valves.

17. The pulsed detonation engine according to claim 5 , wherein the upstream end of the detonation tube is closed by an endwall, wherein at least one of the one or more fuel-oxidizer injectors is disposed on the endwall, wherein at least one of the one or more fuel-oxidizer injectors is disposed at the upstream end, and wherein at least one of the one or more fuel-oxidizer injectors is disposed along the axially extended portion of the detonation tube.

18. The pulsed detonation engine according to claim 5 , further comprising:

a Shchelkin spiral positioned in the axially extended portion of the detonation tube, wherein the Shchelkin spiral is configured to promote detonation in the detonation tube; and

a means for cooling the Shchelkin spiral.

19. The pulsed detonation engine of claim 5 , wherein each of the plurality of elongate orifices has a cross-sectional shape that is a completely convex, closed curve when viewed parallel to the longitudinal axis of the detonation tube.

20. The pulsed detonation engine of claim 19 , wherein each of the plurality of elongate orifices is elliptical in shape when viewed parallel to the longitudinal axis of the detonation tube.