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）。

公开(公告)号：US20150252732A1

公开(公告)日：2015-09-10

申请号：US14569282

申请日：2014-12-12

Applicant: United Technologies Corporation

Inventor： Daniel B. Kupratis

IPC: F02C9/18 ,  F02C7/143 ,  F02K3/077 ,  F02K3/02 ,  F02K3/075

CPC classification number: F02C9/18 ,  F02C7/143 ,  F02K3/025 ,  F02K3/075 ,  F02K3/077 ,  Y02T50/675

Abstract: A gas turbine engine includes an intercooling turbine section to selectively cool the core flow. An intercooling turbine section bypass is also included to selectively bypass at least a portion of a core flow through an intercooling turbine section bypass path around the intercooling turbine section.

Abstract translation: 燃气涡轮发动机包括中间冷却涡轮机部分，以选择性地冷却核心流。 还包括中间冷却涡轮机旁路以选择性地绕过中间冷却涡轮机部分周围的中间冷却涡轮部分旁路的核心流的至少一部分。

公开(公告)号：US20150211441A1

公开(公告)日：2015-07-30

申请号：US14553284

申请日：2014-11-25

Applicant: United Technologies Corporation

Inventor： Francis R. Moon ,  Daniel B. Kupratis

IPC: F02K1/46

CPC classification number: F02K1/12 ,  F02K1/06 ,  F02K1/36 ,  F02K1/38 ,  F02K1/386 ,  F02K1/46 ,  F02K3/06 ,  F02K3/077 ,  F05D2220/323

Abstract: A gas turbine engine includes an outer case structure around a central longitudinal engine axis. An intermediate case structure is included inboard of the outer case structure. An inner case structure is included inboard of the intermediate case structure. A variable area exhaust mixer is included, which is movable between a closed position adjacent to the intermediate case structure and an open position adjacent to the inner case structure.

Abstract translation: 燃气涡轮发动机包括围绕中心纵向发动机轴线的外壳结构。 中间壳体结构包括在外壳结构内。 内壳结构包括在中间壳结构的内侧。 包括可变面积排气混合器，其可在与中间壳体结构相邻的关闭位置和与内壳结构相邻的打开位置之间移动。