公开(公告)号：US20200157965A1

公开(公告)日：2020-05-21

申请号：US16195336

申请日：2018-11-19

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

Inventor： Richard Joseph Skertic ,  Joshua J. Gear ,  John Joseph Costello ,  Geoffrey L. Gatton

IPC: F01D11/20

Abstract: Systems and methods are provided that use a tip clearance control apparatus comprising a mechanical iris, where the tip clearance control apparatus controls a distance between a tip of a blade and a ring of abradable material positioned in an adjustable opening of the mechanical iris.

公开(公告)号：US10605103B2

公开(公告)日：2020-03-31

申请号：US16111793

申请日：2018-08-24

Applicant: Rolls-Royce Corporation ,  Rolls-Royce plc

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

IPC: F01D9/04 ,  F01D25/00

Abstract: A ceramic airfoil system includes a ceramic airfoil shell support by a pair of radially extending pins which penetrate through the shell and connect with a carrier. This pins are disposed at the leading and trailing edges of the airfoil and can be preloaded against the corresponding leading and trailing edge walls to manage thermal growth rates.

公开(公告)号：US20200095877A1

公开(公告)日：2020-03-26

申请号：US16142835

申请日：2018-09-26

Applicant: Rolls-Royce Corporation ,  Rolls-Royce plc

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

IPC: F01D9/04 ,  F01D25/28

Abstract: An airfoil vane assembly includes an anti-wear device for blocking fretting on the airfoil shell and/or carrier as an interface between the airfoil shell and carrier during relative movement. The anti-wear device can be secured with one of the airfoil shell and carrier while slidingly engaged with the other.

公开(公告)号：US20200080431A1

公开(公告)日：2020-03-12

申请号：US16128754

申请日：2018-09-12

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

Inventor： Sachin Dhiwar ,  Ted J. Freeman ,  Thomas Martin

IPC: F01D5/30 ,  F01D5/28 ,  F01D5/22

Abstract: A wheel assembly for a gas turbine engine includes a disk, a blade-attachment system, and a plurality of blades. The disk is configured to rotate about an axis during operation of the gas turbine engine. The blade-attachment system is configured to couple the plurality of blades with the disk for rotation therewith.

公开(公告)号：US10584591B2

公开(公告)日：2020-03-10

申请号：US16031340

申请日：2018-07-10

Applicant: Rolls-Royce Deutschland Ltd & Co KG ,  Rolls-Royce plc

Inventor： Maciek Opoka ,  Thomas Giersch ,  Bernhard Mueck ,  John Dodds ,  Chris Hall

IPC: F01D5/14 ,  F04D29/32 ,  F04D29/66

Abstract: A rotor of a turbomachine includes a plurality of rotor blades, which each have a blade leading edge and a tip, the rotor blades forming a first group and at least one further group of rotor blades of different construction. It is provided that the rotor blades of the first group are nominal rotor blades, the rotor blades of the at least one further group each have a material cutout in the transition from the blade leading edge to the tip, the material cutout not being present in the case of the rotor blades of the first group, and the rotor blades of the first group and of the at least one further group form a non-periodic sequence in a circumferential direction.

公开(公告)号：US10583931B2

公开(公告)日：2020-03-10

申请号：US14585888

申请日：2014-12-30

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

Inventor： Curtis H. Cline ,  Michael J. Armstrong

IPC: F02C6/14 ,  B64D31/12 ,  F02C7/32 ,  F02C9/48 ,  F01D15/10 ,  F02C7/36 ,  F02C9/00

Abstract: An integrated gas turbine engine, electrical power subsystem and thermal management subsystem for aerospace application includes a first motor/generator coupled to a low pressure (LP) shaft of the gas turbine engine, a second motor/generator coupled to a high pressure (HP) shaft of the gas turbine engine, and a system controller coupled to each of the gas turbine engine, a first motor generator and a second motor/generator, wherein the controller receives engine thrust demand and electrical power demand and is programmed to determine total system power demand and the amount of power sharing between the first motor/generator and the second motor/generator to meet thrust and electrical power demand.

公开(公告)号：US20200072066A1

公开(公告)日：2020-03-05

申请号：US16119388

申请日：2018-08-31

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

Inventor： David J. Thomas ,  Aaron D. Sippel ,  Ted J. Freeman

IPC: F01D9/04 ,  F01D25/24 ,  F01D25/00

Abstract: A vane assembly for a gas turbine engine is provided having an outer casing and an inner casing radially spaced apart from the outer casing. An airfoil extends radially between the outer casing and the inner casing. The airfoil includes a spar having an outer endwall positioned adjacent the outer casing and an inner endwall positioned adjacent the inner casing. A pressure side and a suction side extend between the inner endwall and the outer endwall. A ceramic matrix composite cover has a pressure side extending along the pressure side of the spar and a suction side extending along the suction side of the spar.

公开(公告)号：US20200072065A1

公开(公告)日：2020-03-05

申请号：US16119591

申请日：2018-08-31

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

Inventor： Aaron D. Sippel ,  Ted J. Freeman ,  Loic Fabries

IPC: F01D5/30 ,  F01D5/28

Abstract: A wheel assembly for a gas turbine engine includes a disk and a plurality of blades. The disk is configured to rotate about an axis during operation of the gas turbine engine. The blades each include a circumferentially extending root received in the disk and an airfoil that extends radially away from the root.

公开(公告)号：US20200072063A1

公开(公告)日：2020-03-05

申请号：US16119504

申请日：2018-08-31

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

Inventor： Aaron D. Sippel ,  Ted J. Freeman ,  Loic Fabries

IPC: F01D5/30

Abstract: A wheel assembly for a gas turbine engine includes a disk, a plurality of blades, and a platform system that includes a plurality of platforms and pins. The disk is configured to rotate about an axis during operation of the gas turbine engine. The blades each include a circumferentially extending root received in the disk and an airfoil that extends radially away from the root. The platforms are arranged around the wheel to define a flow path of the gas turbine engine and the pins extend into the platforms and the disk to couple the platforms with the disk.

公开(公告)号：US20200063581A1

公开(公告)日：2020-02-27

申请号：US16111793

申请日：2018-08-24

Applicant: Rolls-Royce Corporation ,  Rolls-Royce plc

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

IPC: F01D9/04 ,  F01D25/00

Abstract: A ceramic airfoil system includes a ceramic airfoil shell support by a pair of radially extending pins which penetrate through the shell and connect with a carrier. This pins are disposed at the leading and trailing edges of the airfoil and can be preloaded against the corresponding leading and trailing edge walls to manage thermal growth rates.