Rotating pulse detonation system for a gas turbine engine

Details Rotating pulse detonation system for a gas turbine engine Rotating pulse detonation system for a gas turbine engine

F - Mech Eng,Light,Heat,Weapons

02

C

F02C 5/02 (2006.01) F02C 5/04 (2006.01) F02C 5/11 (2006.01) F02C 5/12 (2006.01) F02K 3/06 (2006.01) F02K 7/06 (2006.01) F02K 7/075 (2006.01)

Patent

CA 2464584

A pulse detonation system (40) for a gas turbine engine (10) having a longitudinal centerline axis (12) extending therethrough includes a rotatable cylindrical member (42) having a forward surface (44), an aft surface (46), and an outer circumferential surface (48), where a plurality of spaced detonation passages (52) are disposed therethrough. Each detonation passage (52) includes at least a portion having a longitudinal axis (58) extending therethrough oriented at a circumferential angle (60) to the longitudinal centerline axis (12). The pulse detonation system (40) further includes a shaft (36) rotatably connected to the cylindrical member (42) and a stator (62) configured in spaced arrangement with the forward surface (44) of the cylindrical member (42) and a portion of the shaft (36). The stator (62) has at least one group of ports (72) formed therein alignable with the detonation passages (52) as the cylindrical member (42) rotates. In this way, detonation cycles are performed in the detonation passages (52) so that combustion gases exit the aft surface (46) of the cylindrical member (42) to create a torque which causes the cylindrical member (42) to rotate. Each detonation passage (52) further includes a first end (54) located adjacent the forward surface (44) of the cylindrical member (42) and a second end (56) located adjacent the aft surface (46) of the cylindrical member (42).

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