公开(公告)号：US20140125121A1

公开(公告)日：2014-05-08

申请号：US14036721

申请日：2013-09-25

Applicant: ROLLS-ROYCE PLC

Inventor： Huw Llewelyn EDWARDS ,  Parag VYAS ,  Malcolm Laurence HILLEL ,  Alasdair GARDNER ,  Sean Patrick ELLIS ,  Nicholas HOWARTH

IPC: B60R16/03

CPC classification number: B60R16/03 ,  B64D2221/00 ,  H02J4/00 ,  H02J7/1446 ,  Y02T50/54

Abstract: A method of operating an electrical power generation system on an aircraft. The method includes assessing a required electrical power of the aircraft, assessing whether a first and a second electrical power source are able to provide the required electrical power in combination, assessing a predetermined condition, determining an operating mode of the first and second electrical power sources to match the predetermined condition, and operating the first and second electrical power sources according to the determined operating mode.

Abstract translation: 一种在飞机上操作发电系统的方法。 该方法包括评估飞行器的所需电力，评估第一和第二电源是否能够组合提供所需的电力，评估预定条件，确定第一和第二电源的操作模式 以匹配预定条件，并且根据所确定的操作模式操作第一和第二电源。

公开(公告)号：US20160153365A1

公开(公告)日：2016-06-02

申请号：US14815207

申请日：2015-07-31

Applicant: ROLLS-ROYCE plc

Inventor： Paul FLETCHER ,  Malcolm Laurence HILLEL ,  Philip Patrick WALSH

IPC: F02C9/32 ,  F02C9/54 ,  F02C9/18 ,  F02C3/13 ,  F02C7/22

CPC classification number: F02C9/32 ,  F02C3/13 ,  F02C3/14 ,  F02C7/222 ,  F02C9/18 ,  F02C9/50 ,  F02C9/52 ,  F02C9/54 ,  F05D2220/32 ,  F05D2240/35 ,  F05D2270/112 ,  F05D2270/3061 ,  F05D2270/31 ,  F23R3/26

Abstract: A method of operating a gas turbine engine (20) comprising a variable geometry compressor (24), a variable geometry combustor (28), and a variable geometry turbine (30). The method comprises operating the variable geometry combustor (28) such that a corrected flow ωc through a combustion zone (46, 48) of the combustor (28) matches a predetermined value.

Abstract translation: 一种操作包括可变几何形状压缩机（24），可变几何形状燃烧器（28）和可变几何涡轮机（30）的燃气涡轮发动机（20）的方法。 该方法包括操作可变几何形状燃烧器（28），使得通过燃烧器（28）的燃烧区（46,48）的校正流量ωc匹配预定值。

公开(公告)号：US20160053721A1

公开(公告)日：2016-02-25

申请号：US14815115

申请日：2015-07-31

Applicant: ROLLS-ROYCE PLC

Inventor： Paul FLETCHER ,  Anthony John MORAN ,  Malcolm Laurence HILLEL ,  Philip Patrick WALSH

IPC: F02K3/02 ,  F02K3/04 ,  F01D17/16 ,  F02K3/115

CPC classification number: F02C9/18 ,  F02C9/54

Abstract: A gas turbine engine (20) comprising a variable geometry engine compressor (24), a variable geometry engine turbine (30) coupled to the engine compressor (24) and a combustor (28). The combustor (28) has an inlet (34) arranged to receive air from a first engine compressor outlet (34), and an outlet arranged to deliver combustion products to the engine turbine (30); a combustor bypass passage (50) having an inlet (53) arranged to receive air from a second engine compressor outlet (53), and an outlet (54) in fluid communication with a main fluid flow path downstream of a combustion zone (46, 48) of the combustor (28), and upstream of a turbine inlet (31); wherein the combustor bypass passage (50) comprises a bypass control valve (52) configured to selectively modulate the ratio of air flowing to the combustor inlet (34) to air flowing through the bypass passage (50).

Abstract translation: 一种燃气涡轮发动机（20），包括可变几何发动机压缩机（24），耦合到发动机压缩机（24）的可变几何发动机涡轮机（30）和燃烧器（28）。 燃烧器（28）具有设置成从第一发动机压缩机出口（34）接收空气的入口（34）和布置成将燃烧产物输送到发动机涡轮机（30）的出口; 具有布置成从第二发动机压缩机出口（53）接收空气的入口（53）的燃烧器旁路通道（50）和与燃烧区（46,46）下游的主流体流动路径流体连通的出口（54） （28）的上游和涡轮机入口（31）的上游; 其中所述燃烧器旁路通道（50）包括旁通控制阀（52），所述旁路控制阀（52）构造成选择性地调节流过所述燃烧器入口（34）的空气与流过所述旁路通道（50）的空气的比例。

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。