公开(公告)号：US20150292402A1

公开(公告)日：2015-10-15

申请号：US14658606

申请日：2015-03-16

Applicant: ROLLS-ROYCE PLC

Inventor： Ahmad RAZAK

IPC: F02C3/14 ,  F02C7/12 ,  F02C3/06

CPC classification number: F02C3/14 ,  F02C3/064 ,  F02C6/003 ,  F02C7/12 ,  F02C9/28 ,  F02K3/06 ,  F02K3/08 ,  F05D2220/323 ,  F05D2240/24 ,  F05D2240/35 ,  F05D2270/082 ,  F23R2900/03341 ,  Y02T50/671 ,  Y02T50/677

Abstract: A gas turbine engine. The engine includes a first compressor coupled to a first turbine by a first shaft, the first turbine having first and second turbine stages. A first combustor is provided downstream of the first compressor and upstream of the first stage of the first turbine. A second combustor is provided downstream of the first stage of the first turbine, and upstream of the second stage of the first turbine. A further turbine is provided downstream of the first turbine, and is coupled to a further compressor by a further shaft.

Abstract translation: 燃气涡轮发动机。 发动机包括通过第一轴联接到第一涡轮机的第一压缩机，第一涡轮机具有第一和第二涡轮级。 第一燃烧器设置在第一压缩机的下游和第一涡轮机的第一级的上游。 第二燃烧器设置在第一涡轮机的第一级的下游，以及第一涡轮机的第二级的上游。 另外的涡轮设置在第一涡轮机的下游，并且通过另一个轴联接到另一个压缩机。

公开(公告)号：US20170036768A1

公开(公告)日：2017-02-09

申请号：US15204141

申请日：2016-07-07

Applicant: ROLLS-ROYCE PLC

Inventor： Rory D. STIEGER ,  Ahmad RAZAK

IPC: B64D13/04 ,  F02C9/26 ,  F02C7/042 ,  B64D41/00 ,  B64D13/06

CPC classification number: B64D13/04 ,  B64D13/06 ,  B64D41/00 ,  B64D2013/0611 ,  B64D2013/0644 ,  B64D2013/0688 ,  B64D2041/002 ,  F02C7/042 ,  F02C9/26 ,  F02C9/28 ,  F02C9/52 ,  F02C9/54 ,  F05D2220/32 ,  F05D2220/50 ,  F05D2270/06 ,  F05D2270/335

Abstract: A gas turbine auxiliary power unit system for an aircraft comprises an aircraft cabin provided with a pressurised air supply, a gas turbine engine comprising a compressor assembly, and a controller.The pressurised air supply is provided to the aircraft cabin through an aircraft cabin air inlet, and exhausted from the aircraft cabin through an aircraft cabin air exhaust, while the gas turbine engine is provided with an inlet air flow from the aircraft cabin air exhaust.The controller is operable to control a flow rate of a fuel supplied to the gas turbine engine responsive to a power demand on the auxiliary power unit, and also to restrict an inlet air flow into the gas turbine engine, so as to maintain an air pressure inside the aircraft cabin within a pre-determined range.

Abstract translation: 控制器可操作以响应于对辅助动力单元的功率需求来控制供应到燃气涡轮发动机的燃料的流量，并且还限制进入燃气涡轮发动机的入口空气流，以便保持气压 在预定范围内的飞机机舱内。

公开(公告)号：US20170363043A1

公开(公告)日：2017-12-21

申请号：US15419533

申请日：2017-01-30

Applicant: ROLLS-ROYCE plc

Inventor： Ahmad RAZAK

IPC: F02K3/10 ,  F02C9/18 ,  F02C3/04 ,  F02C7/36 ,  F02K3/11 ,  F02K3/075

CPC classification number: F02K3/10 ,  F02C3/04 ,  F02C3/14 ,  F02C6/003 ,  F02C7/36 ,  F02C9/18 ,  F02K3/06 ,  F02K3/075 ,  F02K3/11 ,  F05D2220/80

Abstract: An aircraft gas turbine engine comprises a high pressure compressor driven by a high pressure turbine via a high pressure shaft, a first combustor provided downstream of the high pressure compressor and upstream of the high pressure turbine, a low pressure compressor driven by a low pressure turbine via a low pressure shaft, the low pressure compressor being configured to provide air to the high pressure compressor and to a bypass flow. The low pressure turbine comprises at least first and second turbine stages. The engine further comprises a second combustor provided downstream of the first stage of the low pressure turbine and upstream of the second stage of the low pressure turbine. The engine comprises a shaft coupling arrangement configured to transfer power between the high and low pressure shafts.

公开(公告)号：US20170298816A1

公开(公告)日：2017-10-19

申请号：US15292852

申请日：2016-10-13

Applicant: ROLLS-ROYCE plc

Inventor： Ahmad RAZAK ,  Paul FLETCHER

IPC: F02C3/113 ,  F02C9/00 ,  F16H41/24 ,  F02C7/22 ,  F16H61/56 ,  F02C3/14

CPC classification number: F02C3/113 ,  F02C3/14 ,  F02C6/003 ,  F02C7/22 ,  F02C9/00 ,  F02C9/58 ,  F05D2220/323 ,  F05D2220/76 ,  F05D2240/20 ,  F05D2240/35 ,  F05D2260/402 ,  F05D2260/4023 ,  F05D2260/4031 ,  F05D2260/406 ,  F05D2270/02 ,  F05D2270/021 ,  F05D2270/023 ,  F05D2270/303 ,  F05D2270/304 ,  F16H41/24 ,  F16H61/56

Abstract: A gas turbine engine comprises a relatively high pressure compressor coupled to a relatively high pressure turbine by a relatively high pressure shaft; a relatively low pressure compressor coupled to a relatively low pressure turbine by a relatively low pressure shaft rotatable independently of the high pressure shaft; a first combustor located downstream of the high pressure compressor and upstream of the high pressure turbine; and a second combustor located downstream of the high pressure turbine, and upstream of the low pressure turbine. The engine further comprises a coupling arrangement configured to selectively transfer torque between the high pressure shaft and the low pressure shaft.

公开(公告)号：US20170030582A1

公开(公告)日：2017-02-02

申请号：US15216433

申请日：2016-07-21

Applicant: ROLLS-ROYCE plc

Inventor： Ahmad RAZAK ,  Bryce D. CONDUIT

IPC: F23R3/00 ,  F02C3/14 ,  F02C3/04

CPC classification number: F23R3/007 ,  F23R3/002 ,  F23R3/50 ,  F23R3/60 ,  F23R2900/00005

Abstract: A combustor for a gas turbine engine which includes a flame tube made of a ceramic material and a metal casing which surrounds the flame tube. The combustor further includes a thermal insulation layer between the flame tube and the casing which protects the casing from the high temperatures produced by combustion in the combustor and a loading structure which holds the flame tube in a state of axial and radial compression at all engine operating conditions.

Abstract translation: 一种用于燃气涡轮发动机的燃烧器，其包括由陶瓷材料制成的火焰管和围绕火焰管的金属壳体。 燃烧器还包括在火焰管和壳体之间的隔热层，其保护壳体免受由燃烧器中的燃烧产生的高温和在所有发动机操作下将火焰管保持在轴向和径向压缩状态的负载结构 条件。