公开(公告)号：US10094279B2

公开(公告)日：2018-10-09

申请号：US14764186

申请日：2013-01-29

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Daniel B. Kupratis ,  Francis R Moon

IPC: F02C3/14 ,  F02K3/11 ,  F23R7/00 ,  F02K3/06 ,  F02C5/02 ,  F02C7/06 ,  F02C7/36 ,  F23G7/06 ,  F02C3/107

Abstract: The engine (10) includes a low spool (16) disposed aft of an air inlet (12) and a high spool (34) disposed aft of the low spool (16). An intake reverse-duct (44) is disposed radially outward of the high spool (34) and reverses direction of low pressure compressed air from the low spool (16) into a forward-flow high pressure compressor (40) of the high spool (34). A discharge reverse-manifold (48) directs flow of an exhaust gas stream (50} from a forward-flow low pressure turbine (20) into a rearward-flow direction and into at least one pulse detonation firing tube (54). An annular bypass air duct (72) directs cooling air along the engine (10)—The at least, one firing tube is positioned radially outward of the high spool (34), overlies the high spool (34) and is also positioned within the bypass air duct (72).

公开(公告)号：US20150377125A1

公开(公告)日：2015-12-31

申请号：US14764186

申请日：2013-01-29

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Daniel B. Kupratis ,  Francis R Moon

IPC: F02C3/14 ,  F02C3/107

CPC classification number: F02C3/145 ,  F02C3/107 ,  F02C3/14 ,  F02C5/02 ,  F02C7/06 ,  F02C7/36 ,  F02K3/06 ,  F02K3/11 ,  F05D2250/31 ,  F05D2250/311 ,  F05D2260/16 ,  F23G7/065 ,  F23R7/00

Abstract: The engine (10) includes a low spool (16) disposed aft of an air inlet (12) and a high spool (34) disposed aft of the low spool (16). An intake reverse-duct (44) is disposed radially outward of the high spool (34) and reverses direction of low pressure compressed air from the low spool (16) into a forward-flow high pressure compressor (40) of the high spool (34). A discharge reverse-manifold (48) directs flow of an exhaust gas stream (50} from a forward-flow low pressure turbine (20) into a rearward-flow direction and into at least one pulse detonation firing tube (54). An annular bypass air duct (72) directs cooling air along the engine (10)—The at least, one firing tube is positioned radially outward of the high spool (34), overlies the high spool (34) and is also positioned within the bypass air duct (72).

Abstract translation: 发动机（10）包括设置在空气入口（12）后面的低阀芯（16）和设置在低阀芯（16）后面的高阀芯。 进气反向管道（44）设置在高阀芯（34）的径向外侧，并将低压压缩空气的方向从低阀芯（16）反向转向高阀芯的前进高压压缩机（40） 34）。 排放反向歧管（48）引导排气流（50）从前向流动的低压涡轮（20）流向向后流动方向并进入至少一个脉冲爆燃发射管（54），环形 旁路空气管道（72）沿着发动机（10）引导冷却空气 - 至少一个发射管定位在高线轴（34）的径向外侧，覆盖在高线轴（34）上，并且还位于旁路空气 导管（72）。