公开(公告)号：US11268386B2

公开(公告)日：2022-03-08

申请号：US16554713

申请日：2019-08-29

Applicant: ROLLS-ROYCE plc

Inventor： Christopher Benson ,  Stephane M M Baralon

IPC: F01D5/14 ,  F01D5/28

Abstract: A gas turbine engine comprises carbon fibre fan blades. At cruise conditions, the fan tip air angle θ in the range: 64 degrees≤θ≤67 degrees. Additionally or alternatively, the fan blade tip angle β is in the range of from 62 to 69 degrees. Arrangements in accordance with the present disclosure provide advantages which may include improved bird-strike performance. This may allow advantages associated with carbon fibre fan blades to be better exploited.

公开(公告)号：US10145250B2

公开(公告)日：2018-12-04

申请号：US15057407

申请日：2016-03-01

Applicant: ROLLS-ROYCE plc

Inventor： Christopher Benson

IPC: F01D5/32 ,  F01D5/30 ,  F01D25/06 ,  F01D5/28

Abstract: A device for chocking and retaining a dovetail root of a blade of a gas turbine engine in a corresponding axially-extending slot in the rim of a disc includes a retention body having a key portion receivable in a keyway formed in the base of the slot, and a mating portion for mating with a complementary mating portion of the root to prevent relative axial movement between the retention body and the root. The retention body has a lowered position in which the key portion is received sufficiently deeply in the keyway to allow the root to be positioned in the slot without interference from the retention body and also has a raised position in which, after the root is positioned in the slot, a part of the key portion is still received in the keyway while the mating portion mates with the complementary mating portion of the root.

公开(公告)号：US10100961B2

公开(公告)日：2018-10-16

申请号：US14962540

申请日：2015-12-08

Applicant: ROLLS-ROYCE PLC

Inventor： Christopher Benson

IPC: F16L37/14 ,  F16B3/04 ,  F16B7/04 ,  F16B21/07 ,  F16B21/18 ,  F01D25/24

Abstract: A joint assembly includes a first end portion of a first hollow component, a second end portion of a second hollow component, and a first and second resilient connection member. First end portion interconnects with second end portion. First end portion includes a first and second location feature on an outwardly facing surface and axially distally facing surface respectively. Second end portion includes a third and fourth location feature on an inwardly facing surface and axially distally facing surface respectively. First end portion is slidably received inwardly of second end portion, with first location feature being aligned with third location feature to form a first annular cavity, and second location feature being aligned with fourth location feature to form a second annular cavity. First connection member is receivable within first annular cavity, and second connection member is receivable within second annular cavity, to interlock first component to second component.

公开(公告)号：US09903229B2

公开(公告)日：2018-02-27

申请号：US14955906

申请日：2015-12-01

Applicant: ROLLS-ROYCE plc

Inventor： Christopher Benson

IPC: F01D25/24 ,  F16B5/00 ,  F16L37/14

CPC classification number: F01D25/243 ,  F05D2220/32 ,  F05D2230/60 ,  F05D2260/36 ,  F05D2300/501 ,  F16B5/0004 ,  F16L37/148 ,  Y02T50/672

Abstract: A joint assembly has first to third end portions of first to third components and an elongate resilient connection member. The first end portion interconnects with the second in a castellated arrangement. The first and second end portions have repeating arrays of first and second, and third and fourth connection portions. The first connection portion is received inward the third, and its first location feature being aligned with a third location feature of the third forming a first cavity portion, and the second connection portion axially distal surface abutting against that of the fourth, with a second location feature of the second connection portion being aligned with a fourth location feature of the fourth connection portion forming a second cavity portion. The first and second cavity portions are aligned forming an annular cavity, with the connection member being receivable within the annular cavity interlocking the first component to the second.

公开(公告)号：US10174625B2

公开(公告)日：2019-01-08

申请号：US14954355

申请日：2015-11-30

Applicant: ROLLS-ROYCE plc

Inventor： Christopher Benson

IPC: F01D5/14 ,  F01D5/28 ,  F01D21/04 ,  F02C7/05

Abstract: A turbomachine blade comprising a metallic leading edge having a region having varying fracture resistance in a spanwise direction so as to increase energy absorption by the leading edge in the event of the blade being released from a turbomachine and impacting a casing of the turbomachine.

公开(公告)号：US10107136B2

公开(公告)日：2018-10-23

申请号：US14954087

申请日：2015-11-30

Applicant: ROLLS-ROYCE plc

Inventor： Christopher Benson

IPC: F01D5/14 ,  F01D21/04 ,  F01D5/28 ,  F02C7/05

Abstract: A turbomachine blade comprising a metallic leading edge having a weakened region extending in a spanwise direction; and a crack initiator for selectively initiating cracking of the metallic leading edge along the weakened region.

公开(公告)号：US10030522B2

公开(公告)日：2018-07-24

申请号：US14954221

申请日：2015-11-30

Applicant: ROLLS-ROYCE plc

Inventor： Christopher Benson

IPC: F01D5/28 ,  F01D5/14 ,  F01D21/04 ,  F02C7/05

Abstract: A turbomachine blade comprising a blade tip and a metallic leading edge having a plurality of shear zones angled to the blade tip, wherein the shear strength of the shear zones is less than the shear strength of the remainder of the leading edge, such that in the event of an impact shear is initially initiated at the shear zones.

公开(公告)号：US11181042B2

公开(公告)日：2021-11-23

申请号：US16411347

申请日：2019-05-14

Applicant: ROLLS-ROYCE plc

Inventor： Michael O Hales ,  Craig W Bemment ,  Stephane M M Baralon ,  Benjamin J Sellers ,  Christopher Benson ,  Benedict R Phelps ,  Mark J Wilson

IPC: F02C3/073 ,  F02C7/36

Abstract: A gas turbine engine has a cycle operability parameter β in a defined range to achieve improved overall performance, taking into account fan operability and/or bird strike requirements as well as engine efficiency. The defined range of cycle operability parameter β may be particularly beneficial for gas turbine engines in which the fan is driven by a turbine through a gearbox.

公开(公告)号：US10436035B1

公开(公告)日：2019-10-08

申请号：US16399102

申请日：2019-04-30

Applicant: ROLLS-ROYCE plc

Inventor： Stephane M M Baralon ,  Christopher Benson ,  Benedict R Phelps

IPC: F01D5/14 ,  F04D29/38 ,  F01D5/28 ,  F04D29/32

Abstract: A gas turbine engine has a fan tip air angle and/or a fan blade tip air angle in a defined range to achieve improved over all performance, taking into account fan operability and/or bird strike requirements as well as engine efficiency. The defined ranges of fan tip air angle and/or a fan blade tip air angle may be particularly beneficial for gas turbine engines in which the fan is driven by a turbine through a gearbox.

公开(公告)号：US10221705B2

公开(公告)日：2019-03-05

申请号：US14856958

申请日：2015-09-17

Applicant: ROLLS-ROYCE PLC

Inventor： Christopher Benson

IPC: F01D5/32 ,  F01D5/30

Abstract: A slider for chocking a dovetail root of a blade of a gas turbine engine in a corresponding axially-extending slot in the rim of a disc. The slider, in use, is slidingly inserted in an axially-extending cavity formed in the base of the root and in the disc at the base of the slot to urge the blade radially outwardly and thereby mate flanks of the root to flanks of the slot. The slider is arc-shaped and the cavity is correspondingly arc-shaped. The normal to the plane of the arc of the arc-shaped cavity is substantially perpendicular to the engine axis such that, when inserted in the cavity, the slider also retains the root axially in the slot.