초록 ▼

An engine includes at least one pulse detonation chamber configured to receive and detonate a fuel and an oxidizer. The pulse detonation chamber has an outlet end and includes a porous liner adapted to fit within an inner surface of the pulse detonation chamber within a vicinity of the outlet end. T

An engine includes at least one pulse detonation chamber configured to receive and detonate a fuel and an oxidizer. The pulse detonation chamber has an outlet end and includes a porous liner adapted to fit within an inner surface of the pulse detonation chamber within a vicinity of the outlet end. The engine also includes a casing housing the pulse detonation chamber.

대표청구항 ▼

What is claimed is: 1. An engine comprising: at least one pulse detonation chamber configured to receive and detonate a fuel and an oxidizer, said pulse detonation chamber having an outlet end and comprising a porous liner adapted to fit within an inner surface of said pulse detonation chamber with

What is claimed is: 1. An engine comprising: at least one pulse detonation chamber configured to receive and detonate a fuel and an oxidizer, said pulse detonation chamber having an outlet end and comprising a porous liner adapted to fit within an inner surface of said pulse detonation chamber within a vicinity of said outlet end; and a casing housing said at least one pulse detonation chamber. 2. The engine of claim 1, wherein said porous liner is shorter than said pulse detonation chamber. 3. The engine of claim 1, wherein said porous liner comprises a perforated liner attached to said inner surface of said pulse detonation chamber. 4. The engine of claim 3, wherein said perforated liner comprises a material selected from the group consisting of metals, metal alloys, ceramics, and combinations thereof. 5. The engine of claim 3, wherein said perforated liner defines a plurality of holes oriented perpendicular to a surface of said perforated liner. 6. The engine of claim 3, wherein said perforated liner has a surface normal and defines a plurality of holes angled relative to the surface normal. 7. The engine of claim 3, wherein said perforated liner defines a plurality of holes and has a porosity of at least about thirty percent (30%). 8. The engine of claim 7, wherein said perforated liner has a porosity in a range of about fifty percent (50%) to about seventy percent (70%). 9. The engine of claim 3, wherein said perforated liner defines a plurality of annular cavities. 10. The engine of claim 1, wherein said porous liner comprises a porous section of a wall of said pulse detonation chamber. 11. The engine of claim 1, wherein said porous liner comprises a metal fiber material, said metal fiber material being affixed to the inner surface of said pulse detonation chamber. 12. The engine of claim 1, wherein said porous liner and the inner surface of said pulse detonation chamber are separated by a gap, and wherein said porous liner is in fluid communication with said gap. 13. The engine of claim 12, wherein said gap is configured to exhaust flow at the outlet end of said pulse detonation chamber. 14. The engine of claim 13, wherein said gap is further configured to be in fluid communication with a bypass flow outside of said pulse detonation chamber. 15. The engine of claim 12, wherein said pulse detonation chamber further comprises a damping material situated within said gap. 16. The engine of claim 1, wherein said porous liner comprises a porous insert. 17. The engine of claim 16, wherein said porous insert comprises a plurality of flow tubes, each of said flow tubes having a wall defining a plurality of holes. 18. The engine of claim 17, wherein said holes comprise through-holes extending through a respective one of said walls. 19. The engine of claim 1, further comprising a turbine sub-system positioned downstream from said at least one pulse detonation chamber, said turbine subsystem being in flow communication with said at least one pulse detonation chamber and being housed within said casing. 20. The engine of claim 19 further comprising a transition piece positioned between said at least one pulse detonation chamber and said turbine sub-system and being configured to modify a velocity profile of a high pressure gas exiting said at least one pulse detonation chamber. 21. The engine of claim 20, wherein said transition piece comprises a porous liner adapted to fit within an inner surface of said transition piece downstream from said outlet end of said at least one pulse detonation chamber. 22. The engine of claim 1, further comprising a turbine sub-system positioned upstream of said at least one pulse detonation chamber and in flow communication with said at least one pulse detonation, wherein said casing houses said turbine sub-system. 23. An engine comprising: at least one pulse detonation chamber configured to receive and detonate a fuel and an oxidizer, said pulse detonation chamber having an outlet end; a transition piece disposed downstream from said pulse detonation chamber and being configured to modify a velocity profile of a high pressure gas exiting said pulse detonation chamber; and a detonation damper adapted to dampen a plurality of shock waves generated by said pulse detonation chamber, wherein said detonation damper comprises a porous liner adapted to fit within an inner surface of said pulse detonation chamber within a vicinity of said outlet end. 24. The engine of claim 23, further comprising a turbine sub-system disposed downstream from said transition piece, wherein said pulse detonation chamber, said transition piece and said turbine sub-system are arranged in a serial flow relationship. 25. An engine comprising: at least one pulse detonation chamber configured to receive and detonate a fuel and an oxidizer, said pulse detonation chamber having an outlet end; a transition piece disposed downstream from said pulse detonation chamber and being configured to modify a velocity profile of a high pressure gas exiting said pulse detonation chamber; and a detonation damper adapted to dampen a plurality of shock waves generated by said pulse detonation chamber, wherein said detonation damper comprises a porous liner adapted to fit within an inner surface of said transition piece downstream from said outlet end of said at least one pulse detonation chamber. 26. The engine of claim 25, wherein said detonation damper further comprises a porous liner adapted to fit within an inner surface of said detonation chamber within a vicinity of said outlet end. 27. An engine comprising: at least one pulse detonation chamber configured to receive and detonate a fuel and an oxidizer, said pulse detonation chamber having an outlet end; and a casing housing said at least one pulse detonation chamber, said casing comprising a porous liner adapted to fit within an inner surface of said casing downstream of said outlet end, wherein said pulse detonation chamber comprises a porous liner adapted to fit within an inner surface of said pulse detonation chamber within a vicinity of said outlet end.