公开(公告)号：US10782054B2

公开(公告)日：2020-09-22

申请号：US15902648

申请日：2018-02-22

Applicant: Rolls-Royce North American Technologies Inc. ,  Rolls-Royce Corporation

Inventor： Daniel G. Edwards ,  Eric E. Wilson

IPC: F01P3/00 ,  F25B45/00 ,  F25B17/02 ,  B60H1/00 ,  F25B41/06 ,  F25D3/00 ,  F28D20/00 ,  F25B25/00 ,  F25D17/02 ,  F25D16/00 ,  F02B29/04

Abstract: A cooling system may include a cooling pump, a cooling source, a thermal energy storage, a mixing valve, a recharge valve, a recharge pump. The mixing valve may be in fluid communication with a thermal load. A first input of the mixing valve may be in fluid communication with the thermal energy storage. A second input of the mixing valve may be in fluid communication with the recharge pump. Operation of the recharge pump may cause heated cooling fluid output from the thermal load to bypass the cooling pump and flow to the second input of the mixing valve. The recharge valve may be in fluid communication with the thermal energy storage and the cooling pump. The recharge valve may regulate a recharge fluid flow comprising cooling fluid received from the thermal energy storage.

公开(公告)号：US20200284693A1

公开(公告)日：2020-09-10

申请号：US16297305

申请日：2019-03-08

Applicant: Rolls-Royce Corporation

Inventor： Brett Barker ,  Eric Koenig ,  Tyler Gillen

IPC: G01M15/14 ,  G05B19/042 ,  F02C7/12 ,  F01D25/12 ,  F01D21/00

Abstract: A gas turbine engine probe comprises a housing mounted in a borescope port of the engine. The housing includes at least one coolant passage that conducts coolant through the housing. The probe develops an indication of an engine condition, such as blockage in the engine due to sand and/or other debris.

公开(公告)号：US20200284337A1

公开(公告)日：2020-09-10

申请号：US16293790

申请日：2019-03-06

Applicant: Rolls-Royce Corporation

Inventor： John R. Gebhard ,  Adam L. Kempers

IPC: F16H57/04 ,  F01D25/20

Abstract: A gearbox is provided for use in a gas turbine engine. The gearbox includes a plurality of gears, a casing surrounding the plurality of gears, and a lubricant re-circulation system. The casing defines a sump positioned beneath the plurality of gears to retain lubricant. The lubricant re-circulation system includes a re-circulation pump, a re-circulation inlet positioned within the sump, and a re-circulation outlet positioned to supply lubricant to the plurality of gears.

公开(公告)号：US20200284201A1

公开(公告)日：2020-09-10

申请号：US16293030

申请日：2019-03-05

Applicant: Rolls-Royce Corporation

Inventor： John R. Gebhard ,  Adam L. Kempers ,  Andrew D. Copeland

IPC: F02C7/36 ,  F02C3/10 ,  F02C7/268

Abstract: A gas turbine engine includes a first spool and a second spool. The first spool includes a compressor stage, a first turbine stage, and a first shaft configured to transmit rotational energy between the first turbine stage and the compressor stage. The second spool includes a fan, a second turbine stage, and a second shaft configured to transmit rotational energy between the second turbine stage and the fan.

公开(公告)号：US10767497B2

公开(公告)日：2020-09-08

申请号：US16124970

申请日：2018-09-07

Applicant: Rolls-Royce Corporation ,  Rolls-Royce plc

Inventor： Daniel K. Vetters ,  Michael J. Whittle ,  Eric Koenig ,  Jeffrey A. Walston

IPC: F01D9/02 ,  F01D5/28 ,  F01D11/08 ,  F01D25/00 ,  F01D9/04

Abstract: Turbine vane assemblies incorporating both metallic and ceramic matrix composite materials are provided in the present disclosure. The turbine vane assemblies further include interface components that allow for differing rates of thermal expansion in the ceramic matrix composite components and the metallic components.

公开(公告)号：US20200277871A1

公开(公告)日：2020-09-03

申请号：US16510184

申请日：2019-07-12

Applicant: Rolls-Royce North American Technologies, Inc. ,  Rolls-Royce Corporation

Inventor： Jun Shi ,  Matthew R. Gold

IPC: F01D11/12

Abstract: In some examples, a component includes a substrate and a non-continuous abradable coating on the substrate. The abradable coating includes a first portion defining a first plurality of coating blocks, a second portion defining a second plurality of coating blocks, and a blade rub portion extending between the first portion and the second portion and defining a third plurality of coating blocks. At least one of the first plurality of coating blocks or the second plurality of coating blocks is different than the third plurality of coating blocks in at least one coating block parameter.

公开(公告)号：US20200271060A1

公开(公告)日：2020-08-27

申请号：US16281995

申请日：2019-02-21

Applicant: Rolls-Royce Corporation ,  Rolls-Royce North American Technologies Inc.

Inventor： Christopher Hall ,  William Barry Bryan

IPC: F02C9/22 ,  F01D17/14 ,  F02C3/107

Abstract: A system and method for meeting take off noise requirements in a gas turbine engine with a multi-stage fan, comprising an inlet passage, a core passage, a bypass passage and a mid-stage offtake passage; the core passage comprising a core inlet, high pressure compressor, combustor, high pressure turbine, low pressure turbine and a core exhaust; the bypass passage comprising a primary bypass inlet and a primary bypass exit; the mid-stage offtake passage comprising an offtake inlet and offtake exit; a first stage comprising a first rotor, and a second stage comprising a second rotor; and a variable guide vane located axially between the first rotor and the second rotor; an actuator coupled to and selectively varying the variable guide vane between two or more orientations; a variable offtake exit thrust nozzle; and, wherein a gas stream exiting the inlet passage enters one of the core, bypass or mid-stage off take passages as a function of the two or more orientations.

公开(公告)号：US20200271055A1

公开(公告)日：2020-08-27

申请号：US16281789

申请日：2019-02-21

Applicant: Rolls-Royce Corporation

Inventor： Adam L. Kempers ,  John R. Gebhard

IPC: F02C7/06

Abstract: A gas turbine engine includes a fan and an engine core configured to provide rotational power during operation of the gas turbine engine. The engine core includes a compressor, a combustor, and a turbine. An oil sump is located in the engine core and is configured to collect oil from the engine core. The gas turbine engine further includes a gearbox configured to be driven by the engine core during operation of the gas turbine engine and an oil pump assembly configured to move the oil from the oil sump to an oil tank and/or to the engine core.

公开(公告)号：US10753884B2

公开(公告)日：2020-08-25

申请号：US15603389

申请日：2017-05-23

Applicant: Rolls-Royce Corporation

Inventor： Joseph P. Henderkott

IPC: G01J1/58 ,  G01N21/91 ,  G01N21/64 ,  G01N21/84

Abstract: Systems and methods associated with nondestructive inspection of composite material components using fluorescent penetrants for detecting undesirable defects in such components are described. Ceramic matrix composite components include high porous surfaces making defect detection challenging, including contributing to excessive bleed back during the process. The systems and methods include a solvent washing of the component prior to inspection.

公开(公告)号：US10752999B2

公开(公告)日：2020-08-25

申请号：US15458489

申请日：2017-03-14

Applicant: Rolls-Royce Corporation

Inventor： Edward Claude Rice ,  Maxwell Layman ,  Robert F. Proctor ,  Philip M. Bastnagel ,  Mark E. Bartolomeo ,  Jonathan Michael Rivers ,  Eric Handa ,  Aaron Martin ,  Christopher I. Hamilton ,  Jonathan P. Acker ,  Nathan J. Cooper

IPC: C23C30/00 ,  C25D7/04 ,  C25D5/00 ,  C25D5/18 ,  C25D5/56

Abstract: An article that includes a structured substrate having a macro-porous structure that defines a plurality of pores, and a metallic nano-crystalline coating on at least a portion of the structured substrate, where the metallic nano-crystalline coating defines an average grain size less than about 20 nanometers.