Rolls-Royce Plc Patent Portfolio Statistics

Publication number: US20220090541A1
Application number: 17/544,660

Abstract:
An engine core including a turbine, compressor, and a core shaft connecting the turbine and compressor; a fan located upstream of the engine core including a plurality of fan blades; and a gearbox. The gearbox is arranged to receive an input from the core shaft and to output drive to the fan to drive the fan at a lower rotational speed than the core shaft. The gearbox is an epicyclic gearbox and includes a sun gear, a plurality of planet gears, ring gear, and planet carrier to the mounted planet gears. The planet carrier has an effective linear torsional stiffness and the gearbox has a gear mesh stiffness between the planet gears and the ring gear. A carrier to ring mesh ratio of:the⁢⁢effective⁢⁢linear⁢⁢torsionalstiffness⁢⁢of⁢⁢the⁢⁢planet⁢⁢carrier⁢gear⁢⁢mesh⁢⁢stiffness⁢⁢between⁢⁢the⁢⁢planet⁢⁢gears⁢⁢and⁢⁢the⁢⁢ring⁢⁢gearis greater than or equal to 0.2.

Publication date: 2022-03-24
Applicant: Rolls-Royce Plc
Inventors: Mark Spruce

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Publication number: US20220162964A1
Application number: 17/528,882

Abstract:
A support assembly for a gas turbine engine is provided. The support assembly includes an outer casing, an inner structure, a strut and a mechanical fastener. The outer casing defines a longitudinal central axis. The inner structure includes a platform and a support portion disposed around the platform. The platform defines an aperture therethrough and the support portion defines a slot therethrough adjacent to the platform. The slot at least partially surrounds the platform and extends axially towards the aperture by an axial slot length along the longitudinal central axis. The strut extends generally radially from the inner structure to the outer casing. The mechanical fastener is received through the aperture of the platform.

Publication date: 2022-05-26
Applicant: Rolls-Royce Plc
Inventors: Kuziemko Wojciech

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Publication number: US20220155179A1
Application number: 17/454,703

Abstract:
A method of inspecting a surface of a component, e.g. a turbine or compressor blade of a gas turbine engine. The method comprises (a) providing a probe for inspecting the component surface; (b) defining a reference surface that is offset from the component surface; (c) moving the probe so as to contact a plurality of discrete spaced apart inspection points on the component surface, each contact of the probe with an inspection point comprising a first movement of the probe from the reference surface to the inspection point; (d) retracting the probe from the component surface after each contact with an inspection point; and (e) inspecting the component surface each time the probe contacts an inspection point.

Publication date: 2022-05-19
Applicant: Rolls-Royce Plc
Inventors: Alejandro Jeketo

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