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：US20130153184A1

公开(公告)日：2013-06-20

申请号：US13677773

申请日：2012-11-15

Applicant: Rolls-Royce PLC

Inventor： Andrew Martin ROLT ,  Rory Douglas STIEGER

IPC: F28F3/00

CPC classification number: F28F3/005 ,  F28D9/0037 ,  F28F3/046 ,  F28F2250/106

Abstract: This invention relates to a heat exchanger, comprising a plurality of stacked corrugated plates, each plate having a plurality of parallel main corrugations each having longitudinal peak ridges and trough ridges, wherein either or both of the peak ridges and trough ridges have an undulating profile so as to define a plurality of summits in a common plane.

Abstract translation: 本发明涉及一种热交换器，其包括多个堆叠的波纹板，每个板具有多个平行的主波纹，每个波纹具有纵向峰脊和槽脊，其中峰脊和谷脊中的任一个或两个具有起伏的轮廓，因此 以便在公共平面中定义多个顶点。

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。

公开(公告)号：US20140318759A1

公开(公告)日：2014-10-30

申请号：US14150183

申请日：2014-01-08

Applicant: ROLLS-ROYCE PLC

Inventor： Sean Patrick ELLIS ,  Rory Douglas STIEGER

IPC: B64D33/02

CPC classification number: B64D33/02 ,  F02C7/185 ,  F02K3/115 ,  F05D2260/213 ,  F05D2270/112 ,  Y02T50/676

Abstract: A method of controlling an aircraft gas turbine engine cooling system. The cooling system includes a heat exchanger having a first fluid path through which fan air flows, and a second fluid path through which relatively hot compressor air flows. The cooling system includes a valve configurable between an open position corresponding to a first operating mode, where fan air flows through the first path cooling the compressor air in the second path to a lower temperature, and a closed position corresponding to a second operating mode, where fan air may flow through the first path at a reduced rate, thus the compressor air in the second path could be cooled to a lesser extent. The valve is operated in first mode when the aircraft is in a descent mode, or when turbine entry temperature is above a predetermined amount. Otherwise, the valve is operated in second mode.

Abstract translation: 一种控制飞机燃气涡轮发动机冷却系统的方法。 冷却系统包括具有风扇空气流过的第一流体路径的热交换器和相对热的压缩机空气通过的第二流体路径。 冷却系统包括可配置在对应于第一操作模式的打开位置之间的阀，其中风扇空气流过第一路径，将第二路径中的压缩机空气冷却到较低温度，以及对应于第二操作模式的关闭位置， 其中风扇空气可以以降低的速率流过第一路径，因此第二路径中的压缩机空气可被冷却到较小程度。 当飞行器处于下降模式时，或者当涡轮进入温度高于预定量时，阀在第一模式下操作。 否则，阀在第二模式下运行。