Rolls-Royce Plc Patent Portfolio Statistics

Rolls-Royce Plc

Profile Summary

This article summarizes the perfomance of the assignee in the recent years. The overall statistics for this portfolio help to analyze the areas where the assignee is performing well. The filing trend, perfomance across the tech centers and the perfomance of the recent applications has been mentioned below. All the stats are calculated based on the perfomance in USPTO.

How does the overall patent portfolio of Rolls-Royce Plc look like?

Assignee Art Units
Total Applications: 3,970 2,232,823
Granted Patents: 2,840 1,408,837
Grant Index 77.89% 76.77%
Abandoned/Rejected Applications: 806 (22.11%) 426,374 (23.23%)
In-Process Applications: 322 397,612
Average Grant Time: 2.92 Years 2.55 Years
Average Office Actions: 1.44 1.44

Which Technology Area Rolls-Royce Plc is filing most patents in? (Last 10 years)

Art Unit Definition Total Applications
3745 Thermal & Combustion Technology, Motive & Fluid Power Systems 990
3741 Thermal & Combustion Technology, Motive & Fluid Power Systems 601
3746 Thermal & Combustion Technology, Motive & Fluid Power Systems 142
3726 Manufacturing Devices & Processes, Machine Tools & Hand Tools 119
2856 Printing/Measuring and Testing 73

How many patents are Rolls-Royce Plc filing every year?

Year Total Applications Predicted
2022 0* 798
2021 63* 765
2020 218 666
2019 426 426
2018 252
2017 226
2016 256
2015 265
2014 193
2013 148

*The drop in the number of applications filed in last two years compared to previous years is because applications can take up to 18 months to get published

Recently filed patent applications of Rolls-Royce Plc in USPTO?

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

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

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

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

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

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

How are Rolls-Royce Plc’s applications performing in USPTO?

Application Number Title Status Art Unit Examiner
17/544,660 Reliable Gearbox For Gas Turbine Engine Docketed New Case – Ready for Examination 3745 Wong, Elton K
17/528,882 Support Assembly For Gas Turbine Engine OPAP Central, Docket
17/454,703 Method Of Inspecting A Component Docketed New Case – Ready for Examination OPAP Central, Docket
17/520,126 Turbine Engine Docketed New Case – Ready for Examination 3745 Peters, Brian O
17/453,501 Aircraft Engine Docketed New Case – Ready for Examination 3745 Christensen, Danielle M