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公开(公告)号：US20210222617A1
公开(公告)日：2021-07-22
申请号：US17060986
申请日：2020-10-01
Applicant: ROLLS-ROYCE plc , ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
Inventor： Rory D. STIEGER , Mark D. TAYLOR , Erik JANKE
Abstract: A turboshaft gas turbine engine comprises, in fluid flow series, a gas-generator compressor, a combustor, a gas-generator turbine, and a free power turbine. The expansion ratios of the turbines are dependent upon an outlet temperature of the combustor, and an expansion relationship between the turbines is defined as the ratio of expansion ratios of the turbines over a running range of non-dimensional power outputs of the gas turbine engine. A second derivative of the expansion relationship is from 0.6 to 1.0.
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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
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。
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Patent Agency Ranking
公开(公告)号：US20160075435A1
公开(公告)日：2016-03-17
申请号：US14830143
申请日：2015-08-19
Applicant: ROLLS-ROYCE PLC
Inventor： Rory D. STIEGER , Lorenzo RAFFAELLI
IPC: B64D13/08
CPC classification number: B64D13/08 , B64C21/06 , B64D13/06 , B64D2013/0603 , B64D2013/0611 , B64D2013/0622 , B64D2033/0213 , Y02T50/166 , Y02T50/56
Abstract: An air duct arrangement (58) for an aircraft (40). The arrangement (58) comprises an environmental control system (ECS) (50). The ECS (50) comprises an air inlet (60) arranged to ingest a low velocity portion of a boundary layer flow adjacent the aircraft fuselage (44), and to deliver a flow of air to an environmental control system air intake (66). The arrangement (58) further comprises an ejector (70) arranged to receive an ECS exhaust (76), and boundary layer air from an aft region of the aircraft (40), and to exhaust air to the ambient airstream at an aft portion of the aircraft (40).
Abstract translation: 一种用于飞行器（40）的风道装置（58）。 该装置（58）包括环境控制系统（ECS）（50）。 ECS（50）包括空气入口（60），其布置成摄取邻近飞行器机身（44）的边界层流的低速部分，并且将空气流输送到环境控制系统进气口（66）。 该装置（58）还包括排出器（70），其被安排成接收ECS排气（76）和来自飞行器（40）的后部区域的边界层空气，并且在空气的后部将空气排出到周围空气流 飞机（40）。
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公开(公告)号：US20220235698A1
公开(公告)日：2022-07-28
申请号：US17723736
申请日：2022-04-19
Applicant: ROLLS-ROYCE plc , ROLLS-ROYCE CORPORATION
Inventor： Rory D. STIEGER , Daniel SWAIN
Abstract: A gas turbine engine comprises, in fluid flow series, a gas-generator compressor, a combustor, a gas-generator turbine, and a free power turbine. The gas-generator compressor is an axi-centrifugal compressor comprising a plurality of axial compression stages followed by a single centrifugal compression stage, wherein the International Standard Atmosphere, sea-level static (hereinafter ISA SLS) design point pressure ratio of the axi-centrifugal compressor is from 12 to 16, and a ratio of the ISA SLS pressure rise across the axial compression stages to the ISA SLS pressure rise across the centrifugal compression stage is from 0.75 to 1.
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公开(公告)号：US20190006913A1
公开(公告)日：2019-01-03
申请号：US16014090
申请日：2018-06-21
Applicant: ROLLS-ROYCE plc
Inventor： Rory D. STIEGER
Abstract: Electrical machine apparatus comprising: a rotor having a longitudinal axis and being arranged to rotate about the longitudinal axis in a first circumferential direction, the rotor defining one or more conduits for receiving fluid therein, the one or more conduits including an inlet and an outlet; and a fluid guide defining a first aperture arranged to direct fluid in a second direction towards the rotor, the second direction having a positive circumferential component in the first circumferential direction.
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公开(公告)号：US20180309332A1
公开(公告)日：2018-10-25
申请号：US15959396
申请日：2018-04-23
Applicant: ROLLS-ROYCE plc , Rolls-Royce Marine AS
Inventor： Rory D. STIEGER , Astrid ROKKE
CPC classification number: H02K1/20 , H02K1/16 , H02K1/26 , H02K1/32 , H02K3/24 , H02K3/48 , H02K9/02 , H02K9/197 , H02K2213/12
Abstract: Electrical machine apparatus comprising: a first member comprising a ferromagnetic material and defining a first aperture arranged to provide a coolant to cool an electrical conductor.
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公开(公告)号：US20170284422A1
公开(公告)日：2017-10-05
申请号：US15446337
申请日：2017-03-01
Applicant: ROLLS-ROYCE plc
Inventor： Rory D. STIEGER
CPC classification number: F04D29/667 , F01D5/145 , F02K3/06 , F04D19/002 , F04D19/02 , F04D29/324 , F04D29/329 , F04D29/388 , F04D29/682 , F05D2220/32 , F05D2220/36 , F05D2240/303
Abstract: A fan assembly for a gas turbine engine. The assembly includes a hub and a plurality of blades projecting from the hub. The hub includes an inlet aperture located adjacent a blade root. The inlet aperture is in fluid communication with a passage extending along at least part of a span of the blade, and communicates with an outlet provided on an exterior of the blade, radially outwardly of the inlet.
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