公开(公告)号：US09970357B2

公开(公告)日：2018-05-15

申请号：US14876550

申请日：2015-10-06

Applicant: ROLLS-ROYCE PLC

Inventor： Paul Fletcher ,  John Richard Webster ,  Anthony John Moran

IPC: F02C7/22 ,  F01D25/04 ,  F16L9/02

CPC classification number: F02C7/222 ,  F01D25/04 ,  F05D2240/35 ,  F05D2260/96 ,  F05D2260/98 ,  F05D2300/174 ,  F05D2300/175 ,  F05D2300/501 ,  F16L9/02 ,  Y02T50/671

Abstract: A fluid conduit for a gas turbine engine. The conduit includes a superelastic material such as TNTZ or Ti2448. The conduit is installed such that at least part of the conduit is subject to a stress which lies in one of a superelastic and a plastic region of the material in use.

公开(公告)号：US20140271119A1

公开(公告)日：2014-09-18

申请号：US14139119

申请日：2013-12-23

Applicant: Rolls-Royce PLC ,  Rolls-Royce Canada, Ltd.

Inventor： Jean-Francois Lebel ,  Alex Davies ,  Frank Haselbach ,  Paul Fletcher

IPC: F01D25/12

CPC classification number: F01D25/12 ,  F01D5/08 ,  F01D5/18 ,  F05D2260/94 ,  F05D2270/303 ,  F05D2270/306 ,  F05D2270/3062 ,  F05D2270/332 ,  Y02T50/676

Abstract: A method of modulating the cooling of a gas turbine component is disclosed. The method includes determining a target component temperature at which the gas turbine component can be maintained without the gas turbine component experiencing a failure over the course of an indicated life of the gas turbine component; scheduling a cooling air value to the target component temperature; and determining one or more of a demanded cooling air temperature and a demanded cooling air mass flow rate based on the scheduled cooling air value.

Abstract translation: 公开了一种调节燃气轮机部件冷却的方法。 该方法包括：确定燃气轮机部件可维持的目标部件温度，而不会在燃气轮机部件的指定寿命的过程中经历故障的燃气轮机部件; 将冷却空气值调度到目标部件温度; 并且基于所设计的冷却空气值来确定要求的冷却空气温度和所需的冷却空气质量流量中的一个或多个。

公开(公告)号：US10794330B2

公开(公告)日：2020-10-06

申请号：US15810263

申请日：2017-11-13

Applicant: ROLLS-ROYCE plc

Inventor： Ahmed M Y Razak ,  Paul Fletcher

IPC: F02C6/00 ,  F02C7/36 ,  F02K3/11 ,  F02K3/08 ,  F02C3/14 ,  F02C3/113 ,  F02K1/06 ,  F02K1/38 ,  F02K3/077 ,  F02K3/10 ,  F02K3/06

Abstract: A gas turbine engine may include a high pressure compressor coupled to a high pressure turbine by a high pressure shaft, a core combustor located downstream of the high pressure compressor and upstream of the high pressure turbine, and a low pressure compressor provided upstream of the high pressure compressor. The low pressure compressor may be configured to direct core airflow to the high pressure compressor and first bypass airflow which bypasses the high pressure compressor, core combustor and high pressure turbine through a first bypass duct. The engine may further include a mixer downstream of the high pressure turbine and low pressure compressor, the mixer being configured to mix the core and first bypass airflows. The engine also may include a re-heat combustor configured to combust fuel with both core airflow and first bypass airflow. A low pressure turbine may be provided downstream of the re-heat combustor and coupled to the low pressure compressor (14) by a low pressure shaft, the low pressure and high pressure shafts being independently rotatable. A shaft power transfer arrangement may be provided, which is configured to selectively transfer power between the low pressure and high pressure shafts.

公开(公告)号：US20200010205A1

公开(公告)日：2020-01-09

申请号：US16552433

申请日：2019-08-27

Applicant: Rolls-Royce plc

Inventor： Peter Swann ,  Paul Fletcher ,  Alvise Pellegrini ,  Ashog Kulathasan

IPC: B64D27/24 ,  F02C9/48 ,  B64D31/06

Abstract: This invention concerns an aircraft propulsion system in which an engine has an engine core comprising a compressor, a combustor and a turbine driven by a flow of combustion products of the combustor. At least one propulsive fan generates a mass flow of air to propel the aircraft. An electrical energy store is provided on board the aircraft. At least one electric motor is arranged to drive the propulsive fan and the engine core compressor. A controller controls the at least one electric motor to mitigate the creation of a contrail caused by the engine combustion products by altering the ratio of the mass flow of air by the propulsive fan to the flow of combustion products of the combustor. The at least one electric motor is controlled so as to selectively drive both the propulsive fan and engine core compressor.

公开(公告)号：US09829037B2

公开(公告)日：2017-11-28

申请号：US14961124

申请日：2015-12-07

Applicant: ROLLS-ROYCE PLC

Inventor： Stephen Gallimore ,  Paul Fletcher ,  Philip Peters

IPC: F16C27/00 ,  F16C19/54 ,  F16C19/52 ,  F16C19/06 ,  F16C35/04 ,  F01D25/16 ,  F16C41/02 ,  F02C7/06 ,  F16C25/08 ,  F16C33/78 ,  F16C19/16

CPC classification number: F16C19/54 ,  F01D25/16 ,  F01D25/164 ,  F02C7/06 ,  F05D2220/32 ,  F05D2240/54 ,  F05D2260/15 ,  F16C19/06 ,  F16C19/16 ,  F16C19/522 ,  F16C19/542 ,  F16C25/08 ,  F16C33/7823 ,  F16C35/042 ,  F16C41/02 ,  F16C2360/23

Abstract: Load sharing stacked bearing structure including first bearing having a first inner race, first outer race and first set of roller elements housed between first inner race and first outer race and a second bearing having a second inner race, second outer race and second set of roller elements housed between second inner race and the second outer race. A housing surrounds the first and second bearings. First compliant element is provided with the first compliant element connected between the housing and the first outer race. The first compliant element, first outer race and housing define at a pressure chamber. The first outer race axially slidable relative to the second outer race such that an increase in pressure in pressure chamber causes a change in axial spacing between the outer races. This induces an additional axial load on the bearings which helps balance thrust load sharing.

公开(公告)号：US09752462B1

公开(公告)日：2017-09-05

申请号：US15426577

申请日：2017-02-07

Applicant: ROLLS-ROYCE PLC

Inventor： Paul Fletcher

IPC: F02C6/18 ,  F02C1/10 ,  F01K25/10 ,  F01K23/10 ,  F01K7/16 ,  F01K11/02 ,  F02C6/14 ,  F02C6/00 ,  F02C6/16

CPC classification number: F01K25/103 ,  F01K7/165 ,  F01K11/02 ,  F01K23/10 ,  F02C1/10 ,  F02C1/105 ,  F02C6/00 ,  F02C6/14 ,  F02C6/16 ,  F02C6/18 ,  F05D2260/611 ,  Y02E20/16

Abstract: A supercritical working fluid closed cycle heat engine includes, in fluid flow series: a heat source heat exchanger configured to raise the temperature of a working fluid; an expander configured to extract work from the working fluid; a condenser configured to exchange heat between the working fluid and the cooling medium; and a separator configured to separate liquid phase working fluid from gaseous phase working fluid and deliver gaseous phase working fluid to a gaseous compressor and liquid phase working fluid to a fixed displacement liquid pump, the compressor and pump being arranged in parallel. Each of the compressor and fixed displacement pump are configured to return fluid to the heat source heat exchanger. The compressor comprises a variable inlet guide vane and a variable outlet diffuser vane.

公开(公告)号：US09624832B2

公开(公告)日：2017-04-18

申请号：US14229137

申请日：2014-03-28

Applicant: ROLLS-ROYCE PLC

Inventor： Paul Fletcher

IPC: F02C7/14 ,  F02K3/115 ,  F02C7/141

CPC classification number: F02C7/141 ,  F02K3/115 ,  F05D2260/213 ,  Y02T50/676

Abstract: A heat exchange arrangement for a gas turbine engine. The arrangement includes a first conduit for an engine component cooling fluid and a second conduit for a second fluid. The arrangement further includes a heat exchange portion in which fluids flowing through the first and second conduits are in a heat exchange relationship. A valve is provided, which is configured to moderate the mass flow rate of one of the fluids through the heat exchange portion. The arrangement includes divert valve in the first conduit which diverts flow to the second conduit as the flow in the second conduit is moderated to reduce thermal shock in the heat exchange portion.

公开(公告)号：US09546570B2

公开(公告)日：2017-01-17

申请号：US14290512

申请日：2014-05-29

Applicant: ROLLS-ROYCE PLC

Inventor： Paul Fletcher ,  John Richard Webster ,  Alan Robert Maguire

IPC: F16C27/04 ,  F01D25/16 ,  F16C35/077 ,  F16C41/02 ,  F16C41/00 ,  F02C7/28 ,  F16C19/54 ,  F16C19/10 ,  F16C27/08 ,  F16C37/00 ,  F16C25/08

CPC classification number: F01D25/16 ,  F01D25/162 ,  F02C7/28 ,  F05D2300/174 ,  F05D2300/501 ,  F16C19/10 ,  F16C19/54 ,  F16C25/083 ,  F16C27/08 ,  F16C35/077 ,  F16C37/007 ,  F16C41/004 ,  F16C41/02 ,  F16C2202/08 ,  F16C2204/42 ,  F16C2360/23

Abstract: A bearing arrangement is disclosed. The bearing arrangement includes first and second bearings, with each bearing including a respective support element and a respective set of rolling elements and defining a respective load path extending through the respective support element and rolling elements. The support elements are coupled such that a load applied to either support element is transmitted through both the first and second load paths. The arrangement further includes a pair of superelastic titanium alloy elements located in the respective load paths to provide resilient movement between the bearings when a load is applied to the bearing arrangement.

Abstract translation: 公开了一种轴承装置。 轴承装置包括第一和第二轴承，每个轴承包括相应的支撑元件和相应的一组滚动元件，并且限定延伸通过相应支撑元件和滚动元件的相应负载路径。 支撑元件被耦合，使得施加到任一支撑元件的负载通过第一和第二负载路径传输。 该装置还包括位于相应负载路径中的一对超弹性钛合金元件，以在负载施加到轴承装置时在轴承之间提供弹性运动。

公开(公告)号：US09470262B2

公开(公告)日：2016-10-18

申请号：US14631245

申请日：2015-02-25

Applicant: ROLLS-ROYCE PLC

Inventor： Stephen Gallimore ,  Paul Fletcher ,  John Richard Webster ,  Alan Robert Maguire

IPC: F16C27/04 ,  F16C25/08 ,  F01D25/16 ,  F16C41/02 ,  G01M13/04 ,  F16C33/58 ,  F16C19/54 ,  F16C19/16 ,  F16C19/52 ,  F16C27/08

CPC classification number: G01M13/04 ,  F01D25/162 ,  F05D2240/52 ,  F05D2260/83 ,  F05D2300/501 ,  F16C19/16 ,  F16C19/522 ,  F16C19/54 ,  F16C19/542 ,  F16C25/083 ,  F16C27/08 ,  F16C33/586 ,  F16C41/02 ,  F16C2233/00 ,  F16C2237/00 ,  F16C2360/23 ,  Y02T50/671

Abstract: A bearing arrangement comprises: first and second thrust bearings, each including an inner race which is disposed on a shaft and an outer race which is supported by at least one resilient element. Applying a shaft thrust load elastically deforms the resilient elements so as to axially displace the respective outer races in order that the thrust load is shared between the first and second thrust bearings.

Abstract translation: 一种轴承装置包括：第一和第二推力轴承，每个包括设置在轴上的内圈和由至少一个弹性元件支撑的外座圈。 施加轴推力载荷使弹性元件弹性变形，从而轴向移动相应的外座圈，以便推力载荷在第一和第二止推轴承之间共享。

公开(公告)号：US09885251B2

公开(公告)日：2018-02-06

申请号：US14139119

申请日：2013-12-23

Applicant: Rolls-Royce PLC

Inventor： Jean-Francois Lebel ,  Alex Davies ,  Frank Haselbach ,  Paul Fletcher

IPC: F01D25/12 ,  F01D5/08 ,  F01D5/18

CPC classification number: F01D25/12 ,  F01D5/08 ,  F01D5/18 ,  F05D2260/94 ,  F05D2270/303 ,  F05D2270/306 ,  F05D2270/3062 ,  F05D2270/332 ,  Y02T50/676

Abstract: A method of modulating the cooling of a gas turbine component is disclosed. The method includes determining a target component temperature at which the gas turbine component can be maintained without the gas turbine component experiencing a failure over the course of an indicated life of the gas turbine component; scheduling a cooling air value to the target component temperature; and determining one or more of a demanded cooling air temperature and a demanded cooling air mass flow rate based on the scheduled cooling air value.