公开(公告)号：US20150354464A1

公开(公告)日：2015-12-10

申请号：US14708716

申请日：2015-05-11

Applicant: ROLLS-ROYCE PLC

Inventor： Malcolm HILLEL ,  Thierry MOES ,  Rory Douglas STIEGER

IPC: F02C9/18 ,  F02C3/04

CPC classification number: F02C9/18 ,  B64D2013/0618 ,  B64D2013/0644 ,  F01D15/10 ,  F02C3/04 ,  F04D19/02 ,  F04D27/0223 ,  F04D27/0261 ,  F05D2220/76 ,  F05D2270/101 ,  Y02T50/56

Abstract: A method of operating a gas turbine engine compressor. The method includes: determining an operating point of the compressor, and modulating mass flow of environmental control system input air to maintain the operating point of the gas turbine engine compressor within predetermined limits.

Abstract translation: 一种操作燃气涡轮发动机压缩机的方法。 该方法包括：确定压缩机的工作点，并调节环境控制系统输入空气的质量流量，以将燃气涡轮发动机压缩机的工作点保持在预定的限度内。

公开(公告)号：US20150121842A1

公开(公告)日：2015-05-07

申请号：US14514745

申请日：2014-10-15

Applicant: ROLLS-ROYCE PLC

Inventor： Thierry MOES

IPC: F02C9/18 ,  B64D13/08 ,  B64D13/04 ,  B64D13/06 ,  F02K3/075

CPC classification number: F02C9/18 ,  B64D13/04 ,  B64D13/06 ,  B64D13/08 ,  B64D2013/0603 ,  B64D2013/0618 ,  F02C6/08 ,  F02K3/075 ,  F05D2260/213 ,  F05D2270/101 ,  Y02T50/56

Abstract: A pneumatic system 131 for use with gas turbine engines 10 and aircraft 100. The pneumatic system 131 comprises a first engine core compressor bleed offtake in the form of an engine handling bleed offtake 140, and a second engine core compressor bleed offtake in the form of first and second cabin bleed offtake 132, 134, the handling bleed being configured to supply higher pressure air than the cabin offtakes 132, 134. The system 131 comprises a turbocompressor 144 comprising an air compressor 148 driven by a turbine 146. The handling bleed offtake 140 is in fluid communication with the turbocompressor air turbine 146 to thereby drive the air turbine 146, and the cabin bleed offtakes 132, 134 are in fluid communication with the turbocompressor air compressor 148 such that air from the offtakes 132, 134 is compressed by the turbocompressor air compressor 148.

Abstract translation: 用于与燃气涡轮发动机10和飞机100一起使用的气动系统131.气动系统131包括第一发动机核心压缩机泄放出口处理出口140的发动机的出口，以及第二发动机芯压缩机排出出口 第一和第二舱室泄放出口132,134，处理泄漏被配置为提供比机舱132,134更高的压力空气。系统131包括涡轮压缩机144，涡轮压缩机144包括由涡轮146驱动的空气压缩机148。 140与涡轮压缩机空气涡轮机146流体连通，从而驱动空气涡轮机146，并且出口132,134的舱室泄放与涡轮压缩机空气压缩机148流体连通，使得来自提升器132,134的空气被压缩机 涡轮压缩机空气压缩机148。

公开(公告)号：US20150107261A1

公开(公告)日：2015-04-23

申请号：US14493792

申请日：2014-09-23

Applicant: ROLLS-ROYCE PLC

Inventor： Thierry MOES ,  Rory Douglas STIEGER ,  Malcolm Laurence HILLEL ,  Parag VYAS

IPC: B64D13/06 ,  B64D41/00 ,  B64D13/08

CPC classification number: B64D13/06 ,  B64D13/08 ,  B64D41/00 ,  B64D2013/0618 ,  B64D2013/0648 ,  Y02T50/56

Abstract: A bleed air system for an aircraft has a gas turbine engine and operating method. The system includes an environmental control system (ECS) for providing cabin airflow to the aircraft, including operating modes such as first and second air cycle machine operating modes and heat exchanger operating modes. The ECS includes first, second and third bleed ports each configured to provide engine bleed air from gas turbine engine compressors to the ECS. The ECS includes a bleed air system sensor arrangement configured to sense one or more bleed air system conditions, an environmental control system controller that selects an environmental control system operating mode that provides required cabin air flow and temperature at an optimal specific fuel consumption of the gas turbine engine at the sensed system conditions, and a bleed port valve controller which determines an operating pressure required to operate the environmental control system in the selected mode.

Abstract translation: 用于飞行器的排气系统具有燃气涡轮发动机和操作方法。 该系统包括用于向飞机提供机舱气流的环境控制系统（ECS），包括诸如第一和第二空气循环机操作模式和热交换器操作模式的操作模式。 ECS包括第一，第二和第三排放口，每个排放端口被配置为将燃气涡轮发动机压缩机的引擎排放空气提供给ECS。 ECS包括被配置为感测一个或多个排气系统条件的排气系统传感器装置，环境控制系统控制器，其选择环境控制系统操作模式，其提供在气体的最佳特定燃料消耗下所需的舱室空气流量和温度 涡轮发动机，以及排气口阀控制器，其确定在所选模式下操作环境控制系统所需的操作压力。