公开(公告)号：US08887488B1

公开(公告)日：2014-11-18

申请号：US13084800

申请日：2011-04-12

申请人： Jose R. Paulino

发明人： Jose R. Paulino

IPC分类号： F02C9/18 ,  F02K3/12

CPC分类号： F01D13/003

摘要： A high efficiency power plant for a UAV with a high pressure ratio gas turbine engine used for low power operation such as loiter speed and a low pressure ratio gas turbine engine used for high power operation. A power turbine receives hot gas flows from the two engines to drive an output shaft. At low power operation, only the high pressure ratio engine is operated. At high power operation, both engines are operated where the exhaust from the high pressure ratio engine is used to drive a turbine of the low pressure ratio engine. A compressor of the low pressure ratio engine supplies compressed air to a combustor that produces a hot gas stream that is passed through the power turbine.

摘要翻译： 用于具有用于低功率操作的高压比燃气涡轮发动机的无人机的高效率发电机，例如用于大功率运行的低速运行和低压比燃气涡轮发动机。 动力涡轮机接收来自两个发动机的热气流以驱动输出轴。 在低功率运行时，只有高压比发动机运转。 在大功率操作中，两个发动机都是在来自高压比发动机的排气被用于驱动低压比发动机的涡轮机的情况下操作的。 低压比发动机的压缩机将压缩空气供给到产生通过动力涡轮机的热气流的燃烧器。

公开(公告)号：US08844266B1

公开(公告)日：2014-09-30

申请号：US13251946

申请日：2011-10-03

申请人： Jose R. Paulino

发明人： Jose R. Paulino

IPC分类号： F02C6/02 ,  F02K3/12

CPC分类号： F02C6/12 ,  F01D5/025 ,  F01D5/043 ,  F05D2220/40 ,  F05D2260/37

摘要： A variable bypass ratio augmented gas turbine engine system for a UAV with a high pressure ratio gas turbine engine used for low power operation such as loiter speed and a low pressure ratio gas turbine engine used for high power operation. A power turbine receives hot gas flows from the two engines to drive an output shaft. At low power operation, only the high pressure ratio engine is operated. At high power operation, both engines are operated where the exhaust from the high pressure ratio engine is mixed with bleed off air form the second compressor to produce a second hot gas flow in a second combustor to drive the second turbine. The remaining compressed air from the second compressor is passed into a third combustor to produce a third hot gas flow that then flows into the power turbine.

摘要翻译： 一种用于UAV的可变旁路比增强燃气轮机发动机系统，其具有用于低功率运行的高压比燃气涡轮发动机，例如用于大功率运行的低速运行和低压比燃气涡轮发动机。 动力涡轮机接收来自两个发动机的热气流以驱动输出轴。 在低功率运行时，只有高压比发动机运转。 在高功率操作下，两个发动机都在来自高压比发动机的排气与排出空气混合形成第二压缩机的情况下操作，以在第二燃烧器中产生第二热气流以驱动第二涡轮机。 来自第二压缩机的剩余压缩空气被送入第三燃烧器，产生第三热气流，然后流入动力涡轮。