公开(公告)号：US20170016349A1

公开(公告)日：2017-01-19

申请号：US15187542

申请日：2016-06-20

Applicant: ROLLS-ROYCE PLC ,  ROLLS-ROYCE DEUTSCHLAND LTD & CO KG

Inventor： Gideon Daniel VENTER ,  Ivan POPOVIC

IPC: F01D25/16 ,  F01D5/02 ,  F01D15/12

Abstract: A gas turbine engine includes a spool which rotates in use, a static structure and an air bearing, the air bearing being provided at an interface between the spool and the static structure.

Abstract translation: 燃气涡轮发动机包括在使用中旋转的阀芯，静态结构和空气轴承，空气轴承设置在阀芯和静态结构之间的界面处。

公开(公告)号：US20210214094A1

公开(公告)日：2021-07-15

申请号：US17197708

申请日：2021-03-10

Applicant: ROLLS-ROYCE PLC

Inventor： Richard HARWOOD ,  Kalyani G. MENON ,  Joseph PALMER ,  Ivan POPOVIC

IPC: B64D27/24 ,  B63H21/20 ,  H02P5/74 ,  B61C5/00 ,  B63H21/17 ,  B64D27/02 ,  H02J3/46 ,  H02J7/34 ,  H02J3/02

Abstract: An aircraft propulsion system includes at least first and second electrical generators, each being configured to provide electrical power to a respective first and second AC electrical network. The system further comprises at least first and second AC electrical motors directly electrically coupled to a respective AC network and coupled to a respective propulsor, and a DC electrical network electrically coupled to the first and second AC networks via respective first and second AC to DC converters, and to a further electrical motor, the further electrical motor being coupled to a propulsor.

公开(公告)号：US20200300119A1

公开(公告)日：2020-09-24

申请号：US16815309

申请日：2020-03-11

Applicant: ROLLS-ROYCE plc

Inventor： David MASON ,  Paul WILSON ,  Ivan POPOVIC

IPC: F01D25/16

Abstract: A gas turbine engine (10) having a bearing support structure (100) comprising: a bearing chamber (104); a first buffer fluid passage (110) disposed radially outwardly of the bearing chamber (104); a second buffer fluid passage (116) disposed radially outwardly of the first buffer fluid passage (110); and a core fluid passage (132) disposed radially outwardly of the second buffer fluid passage (116); the bearing chamber (104), first buffer fluid passage (110), second buffer fluid passage (116) and core fluid passage (132) being separated by respective hub walls.

公开(公告)号：US20180079515A1

公开(公告)日：2018-03-22

申请号：US15684265

申请日：2017-08-23

Applicant: ROLLS-ROYCE PLC

Inventor： Richard HARWOOD ,  Kalyani G. MENON ,  Joseph PALMER ,  Ivan POPOVIC

IPC: B64D27/24

CPC classification number: B64D27/24 ,  B61C5/00 ,  B63H21/17 ,  B63H21/20 ,  B64D27/02 ,  B64D27/10 ,  B64D2027/026 ,  H02J3/005 ,  H02J3/02 ,  H02J3/46 ,  H02J7/34 ,  H02P5/74 ,  Y02T30/10 ,  Y02T50/44 ,  Y02T50/64 ,  Y02T70/5209 ,  Y02T70/5236 ,  Y02T90/46

Abstract: An aircraft propulsion system (10) comprises at least first and second electrical generators (15a, 15b), each being configured to provide electrical power to a respective first and second AC electrical network (16a, 16b). The system (10) further comprises at least first and second AC electrical motors (19a, 19b) directly electrically coupled to a respective AC network (16a, 16b) and coupled to a respective propulsor (4), and a DC electrical network electrically coupled to the first and second AC networks (16a, 16b) via respective first and second AC to DC converters (17a, 17b), and to a further electrical motor 19c), the further electrical motor (19c) being coupled to a propulsor (4).

公开(公告)号：US20170106985A1

公开(公告)日：2017-04-20

申请号：US15205648

申请日：2016-07-08

Applicant: ROLLS-ROYCE plc

Inventor： Rory D. STIEGER ,  Ivan POPOVIC

IPC: B64D13/06 ,  B64D13/02 ,  H02K7/18 ,  B64D27/16 ,  F02C9/18 ,  F02C3/13 ,  F01D15/10 ,  B64D41/00

CPC classification number: B64D13/06 ,  B64D13/02 ,  B64D27/16 ,  B64D41/00 ,  B64D2013/0603 ,  B64D2013/0611 ,  B64D2013/0618 ,  B64D2013/064 ,  B64D2013/0644 ,  B64D2013/0648 ,  F01D15/10 ,  F02C3/13 ,  F02C6/08 ,  F02C7/08 ,  F02C7/277 ,  F02C9/18 ,  F05D2220/323 ,  F05D2220/50 ,  F05D2220/76 ,  H02K7/1823 ,  Y02T50/44 ,  Y02T50/56 ,  Y02T50/671

Abstract: An aircraft pneumatic system comprises a main gas turbine engine (10) comprising a main compressor (14, 16), a recuperated auxiliary gas turbine engine (40) comprising a core compressor (42) having an inlet in fluid communication with a main compressor bleed (32) of the main gas turbine engine(10) and an environmental control system inlet in fluid communication with the main compressor bleed (32) of the main gas turbine engine (10). The environmental control system comprises a compressor (68) driveable by power provided by the auxiliary gas turbine engine (40).

公开(公告)号：US20160146089A1

公开(公告)日：2016-05-26

申请号：US14928363

申请日：2015-10-30

Applicant: ROLLS-ROYCE PLC

Inventor： Ivan POPOVIC

IPC: F01P5/06 ,  F02C9/18 ,  F01P1/06

CPC classification number: F01P5/06 ,  F01P1/06 ,  F02C7/18 ,  F02C9/18 ,  F05D2240/127 ,  Y02T50/675

Abstract: A cooling arrangement for a compressor drive cone (48) in a gas turbine engine (10). An annular cavity (62) defined by the drive cone (48), a portion of a compressor rotor disc (44) and a downstream cavity wall (52). The cavity (62) comprising a recirculation zone (66) at its radially outermost region. The cavity (62) arranged to ingest hot working gas radially inwardly into the recirculation zone (66). An annular array of pipes (70) that penetrate through the cavity wall (52) close to the radially inward extent of the recirculation zone (66). The pipes (70) coupled to a supply of cooling fluid and having an open end arranged to direct the cooling air, in use, across the recirculation zone (66) towards the drive cone (48).

Abstract translation: 一种用于燃气涡轮发动机（10）中的压缩机驱动锥（48）的冷却装置。 由驱动锥体（48）限定的环形空腔（62），压缩机转子盘（44）的一部分和下游空腔壁（52）。 空腔（62）在其径向最外侧区域包括再循环区（66）。 空腔（62）布置成将热工作气体径向向内吸入再循环区（66）。 穿过空腔壁（52）的靠近再循环区域（66）的径向向内范围的管状环形阵列（70）。 管道70耦合到冷却流体源，并且具有开口端，该开口端设置成在使用时将冷却空气引向再循环区域66朝向驱动锥体48。