A pulse detonation (PD) assembly includes a number of PD chambers adapted to expel respective detonation product streams and a number of barriers disposed between respective pairs of PD chambers. The barriers define, at least in part, a number of sectors that contain at least one PD chamber. A hybri
A pulse detonation (PD) assembly includes a number of PD chambers adapted to expel respective detonation product streams and a number of barriers disposed between respective pairs of PD chambers. The barriers define, at least in part, a number of sectors that contain at least one PD chamber. A hybrid engine includes a number of PD chambers and barriers. The hybrid engine further includes a turbine assembly having at least one turbine stage, being in flow communication with the PD chambers and being configured to be at least partially driven by the detonation product streams. A segmented hybrid engine includes a number of PD chambers and segments configured to receive and direct the detonation product streams from respective PD chambers. The segmented hybrid engine further includes a turbine assembly configured to be at least partially driven by the detonation product streams.
대표청구항▼
The invention claimed is: 1. A pulse detonation assembly comprising: a casing; a plurality of pulse detonation chambers disposed within said casing, each of said plurality of pulse detonation chambers adapted to receive and combust a primary air flow and to expel a respective detonation product str
The invention claimed is: 1. A pulse detonation assembly comprising: a casing; a plurality of pulse detonation chambers disposed within said casing, each of said plurality of pulse detonation chambers adapted to receive and combust a primary air flow and to expel a respective detonation product stream; and a plurality of barriers extending in an axial direction along a length of said pulse detonation chambers and in a radial direction between a central region and the casing defining, at least in part, a plurality of sectors, each of said sectors containing at least one of said plurality of pulse detonation chambers and defining a respective bypass region adapted to receive and conduct a bypass flow; and a plurality of segments, each segment including a mixing zone adapted to receive and mix a respective detonation product stream from said plurality of pulse detonation chambers with the bypass flow from a respective sector to form a segment exhaust flow. 2. The pulse detonation assembly of claim 1, wherein said pulse detonation chambers are arranged in an annular configuration. 3. The pulse detonation assembly of claim 1, further comprising a shaft positioned in said central region, wherein each of said barriers extends between said shaft and said casing. 4. The pulse detonation assembly of claim 1, wherein at least one of said sectors contains at least two of said pulse detonation chambers. 5. The pulse detonation assembly of claim 1, further comprising a plenum configured to supply the primary air flow to said pulse detonation chambers and the bypass flow to said bypass regions. 6. The pulse detonation assembly of claim 1, further comprising a compressor configured to supply the primary air flow to said pulse detonation chambers and to supply the bypass flow to said bypass regions. 7. The pulse detonation assembly of claim 1, wherein said pulse detonation chambers are curved. 8. The pulse detonation assembly of claim 1, wherein a plurality of said segments further comprise fluid communication ports configured for permitting a fluid flow between said segments. 9. The pulse detonation assembly of claim 1, wherein each of said pulse detonation chambers has a coaxial wall structure comprising an inner and an outer wall, and wherein said inner wall and outer wall define a respective coaxial bypass region adapted to receive and conduct a bypass flow. 10. A hybrid engine comprising: a pulse detonation assembly comprising a casing; a plurality of pulse detonation chambers, wherein each of said pulse detonation chambers is adapted to receive and combust a primary air flow and to expel a respective detonation product stream; a plurality of barriers extending in an axial direction along a length of said pulse detonation chambers and in a radial direction between a central region and the casing defining, at least in part, a plurality of sectors, each of said sectors containing at least one of said plurality of pulse detonation chambers and defining a respective bypass region adapted to receive and conduct a bypass flow; and a plurality of segments, each segment including a mixing zone adapted to receive and mix a respective detonation product stream from said plurality of pulse detonation chambers with the bypass flow from a respective sector to form a segment exhaust flow; and a turbine assembly comprising at least one turbine stage configured to be at least partially driven by the segment exhaust flow. 11. The hybrid engine of claim 10, further comprising: wherein said pulse detonation chambers are arranged in an annular configuration; and a shaft positioned in said central region. 12. The hybrid engine of claim 10, wherein at least one of said sectors contains at least two of said pulse detonation chambers. 13. The pulse detonation assembly of claim 10, further comprising a plenum configured to supply the primary air flow to said pulse detonation chambers and the bypass flow to said bypass regions. 14. The hybrid engine of claim 10, further comprising a compressor configured to supply the primary air flow to said pulse detonation chambers and the bypass flow to said bypass regions. 15. The hybrid engine of claim 10, wherein said pulse detonation chambers are curved. 16. The hybrid engine of claim 15, wherein said pulse detonation chambers are arranged in a helix-configuration. 17. The hybrid engine of claim 15, wherein said pulse detonation chambers are lobed in a transition region. 18. The hybrid engine of claim 10, wherein at least one barrier includes a fluid communication port configured for permitting a fluid flow between said sectors. 19. The hybrid engine of claim 10, wherein each of said pulse detonation chambers has a coaxial wall structure comprising an inner and an outer wall, and wherein said inner wall and outer wall define a respective coaxial bypass region adapted to receive and conduct the bypass flow. 20. The pulse detonation assembly of claim 1, wherein said plurality of barriers are made of a high-temperature material. 21. The pulse detonation assembly of claim 20, wherein said high-temperature material is selected from the group consisting of nickel alloy metals and ceramic matrix composites. 22. The pulse detonation assembly of claim 1, wherein each of said plurality of barriers comprises a single wall or multi-wall structure and further comprises at least one coating. 23. The hybrid engine of claim 10, wherein said plurality of barrier is made of a high-temperature material. 24. The hybrid engine of claim 23, wherein said high-temperature material is selected from the group consisting of nickel alloy metals and ceramic matrix composites. 25. The hybrid engine of claim 10, wherein each of said plurality of barriers comprises a single wall or multi-wall structure and further comprises at least one coating.
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이 특허에 인용된 특허 (12)
Butler, Lawrence; Johnson, James Edward; Dunbar, Lawrence Wayne, Combined cycle pulse detonation turbine engine.
Butler, Lawrence; Venkataramani, Kattalaicheri Srinivasan; Murrow, Kurt David; Leyva, Ivett Alejandra, Pulse detonation system for a gas turbine engine.
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