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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
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.
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公开(公告)号：US10578160B2
公开(公告)日：2020-03-03
申请号：US16035866
申请日：2018-07-16
Applicant: ROLLS-ROYCE PLC
Inventor： Jonathan Masters
IPC: F16C33/12 , F01C21/02 , F16C17/10 , F16C32/06 , F16C33/10 , F16C33/14 , F04C2/18 , F01D25/16 , F16C17/22
Abstract: A gear pump bearing block has a bush formed of antifriction alloys. The bush has a cylindrical portion providing a bore adapted to receive a bearing shaft of a gear of the pump. It further has a thrust face at the end of the cylindrical portion, the thrust face being adapted to slidingly engage with a side surface of the gear. The bush has an inner component providing the bore, and an outer component forming a radially outer surface of the cylindrical portion. The inner and outer components are formed of respective lead bronze alloys, the lead bronze alloy of the outer component having a higher lead content than the lead bronze alloy of the inner component.
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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
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.
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公开(公告)号：US20200063568A1
公开(公告)日：2020-02-27
申请号：US16283287
申请日：2019-02-22
Applicant: ROLLS-ROYCE plc
Inventor： Martin N. GOODHAND , Ian M. BUNCE
IPC: F01D5/14
Abstract: A turbomachine (105) configured to compress supercritical carbon dioxide is shown. The turbomachine comprises, in fluid flow series, an inlet (201), an inducerless radial impeller (202) having a plurality of backswept blades (211,212) each of which have a blade exit angle (χ2) of from −50 to −70 degrees, and a fully vaneless diffuser (203).
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公开(公告)号：US20200056501A1
公开(公告)日：2020-02-20
申请号：US16514072
申请日：2019-07-17
Applicant: ROLLS-ROYCE plc
Inventor： Benjamin J. EASTMENT
Abstract: A method of detecting rotor blade damage on a gas turbine engine is provided comprising the steps of taking an image of a rotor blade, processing the image to produce a blade profile using an edge detection algorithm and determining a rotor blade error by comparing the blade profile with a geometric model of a corresponding blade.
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Patent Agency Ranking
公开(公告)号：US20200056486A1
公开(公告)日：2020-02-20
申请号：US16539688
申请日：2019-08-13
Applicant: Rolls-Royce Deutschland Ltd & Co KG , Rolls-Royce plc
Inventor： Sven SCHRAPE , Bernhard MÜCK , Jens NIPKAU , Thomas GIERSCH , Frank HEINICHEN , John DODDS
IPC: F01D5/14
Abstract: A blade wheel of a turbomachine, which blade wheel has a multiplicity of blades which are suitable and provided for extending radially in a flow path of the turbomachine, wherein the blades form a blade entry angle and a blade exit angle. Provision is made whereby the blade wheel forms N blocks of blades, where N≥2, wherein the blades of a block have in each case the same blade entry angle and the same blade exit angle, and the blades of at least two mutually adjacent blocks have a different blade entry angle and/or a different blade exit angle. According to a further aspect of the invention, partial gaps that the blades form in relation to an adjacent flow path boundary are varied in mutually adjacent blocks.
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公开(公告)号：US10563588B2
公开(公告)日：2020-02-18
申请号：US15402843
申请日：2017-01-10
Applicant: ROLLS-ROYCE PLC
Inventor： Ian J Toon
Abstract: A gas turbine engine fuel system including a combustor with at least one fuel injector, a fuel manifold that supplies fuel to each injector, a drain tank in fluid communication with the fuel manifold, and a vacuum generator that selectively provides below atmospheric pressure to the drain tank and includes first and second chambers separated by a flexible diaphragm. The fuel system also includes a first check valve that allows one-way flow from the fuel manifold into the fuel injector, and a second check valve that allows one-way flow from the fuel injector to the fuel manifold. The vacuum generator reduces a pressure within the second chamber causing the diaphragm to increase a volume of the first chamber and reduce a volume of the second chamber, such that expanding the first chamber causes below atmospheric pressure in the drain tank and fuel manifold, and the second check valve opens.
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公开(公告)号：US10562241B2
公开(公告)日：2020-02-18
申请号：US15472961
申请日：2017-03-29
Applicant: ROLLS-ROYCE plc
Inventor： Robert C Backhouse
IPC: B29C70/38 , F04D29/32 , F01D25/24 , F01D5/28 , F01D9/04 , B22F7/06 , F04D29/02 , F04D29/38 , F04D29/52 , F04D29/54 , B29K63/00 , B29K305/00 , B29K307/04 , B29L31/08
Abstract: The application describes methods of making composite bodies including fibre-reinforced composite material with carbon fibre reinforcement and also a metal-containing portion (4). The metal-containing portion (4) is formed by laying up metal reinforcement elements, such as tapes of titanium alloy, among the carbon fibre reinforcement tapes which make up the composite body. The proportion of metal reinforcement may increase progressively towards the surface and/or towards an edge (14) of the composite body. In an example, metal leading and trailing edges (14,15) of a fan blade (1) are integrally formed in this way.
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公开(公告)号：US20200049022A1
公开(公告)日：2020-02-13
申请号：US16507231
申请日：2019-07-10
Applicant: ROLLS-ROYCE plc
Inventor： Richard G. STRETTON , Steven A. RADOMSKI
Abstract: A gas turbine engine (10) comprises a bypass duct cowl (21), an engine core housing (22) defining an engine core inlet, a bypass fan (13) and a plurality of outlet guide vanes (24). Each outlet guide vane 24 extends between a radially inner surface of the bypass duct cowl (21) and a radially outer surface of the engine core housing (22, 23) to define an outlet guide vane span (SPANOGV). The outlet guide vanes (24) are configured to support the engine core housing (22, 23) relative to the bypass duct cowl (21). The bypass fan (13) and an engine core inlet (34) define a bypass ratio between 10 and 17, and a ratio of the outlet guide vane span (OGVSPAN) to a bypass fan radius (RFAN) is between 0.45 and 0.55.
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公开(公告)号：US10550700B1
公开(公告)日：2020-02-04
申请号：US16437356
申请日：2019-06-11
Applicant: ROLLS-ROYCE plc
Inventor： Nicholas Howarth , Gareth M Armstrong
IPC: F02C7/36 , F02C3/107 , F02K3/06 , F01D5/14 , F02C3/02 , F04D29/68 , F04D19/02 , F01D5/28 , F02C3/04 , F02C7/04 , F02K3/068
Abstract: A gas turbine engine that has improved fuel burn provides operability and/or maintenance requirements when installed on an aircraft. The gas turbine engine is provided with a core compressor that includes twelve, thirteen or fourteen rotor stages. The gas turbine engine has a ratio of a core compressor aspect ratio divided by a core compressor pressure ratio is in the range of from 0.03 to 0.09. This results in an optimum balance between installation benefits, operability, maintenance requirements and engine efficiency when the gas turbine engine is installed on an aircraft.
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