Safran Aircraft Engines Patent Portfolio Statistics

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Safran Aircraft Engines

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 Safran Aircraft Engines look like?

Assignee Art Units
Total Applications: 3,355 2,198,745
Granted Patents: 2,885 1,355,845
Grant Index 97.53% ↑ 75.51%
Abandoned/Rejected Applications: 73 (2.47%) 439,792 (24.49%)
In-Process Applications: 396 403,108
Average Grant Time: 2.89 Years ↑ 2.62 Years
Average Office Actions: 1.29 ↓ 1.49

Which Technology Area Safran Aircraft Engines is filing most patents in? (Last 10 years)

Art Unit Definition Total Applications
3745 Thermal & Combustion Technology, Motive & Fluid Power Systems 1,164
3741 Thermal & Combustion Technology, Motive & Fluid Power Systems 464
3726 Manufacturing Devices & Processes, Machine Tools & Hand Tools 146
3746 Thermal & Combustion Technology, Motive & Fluid Power Systems 138
Opap Parked GAU 111

How many patents are Safran Aircraft Engines filing every year?

Year Total Applications Predicted
2022 0* 966
2021 179* 820
2020 173 747
2019 171 171
2018 282 –
2017 232 –
2016 273 –
2015 236 –
2014 247 –
2013 209 –

*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 Safran Aircraft Engines in USPTO?

Publication number: None
Application number: 17/628,608

Abstract:
–

Publication date: –
Applicant: Safran Aircraft Engines
Inventors: Batonnet Baptiste Ren Roger

Publication number: US20220135207A1
Application number: 17/626,348

Abstract:
The invention relates to a turbomachine module (1), comprising: —a rotating housing (7-8) supporting a propeller provided with a plurality of blades (5), —a system for varying the pitch of the propeller blades (5), the system comprising a control means, and a mechanism for varying the pitch of the propeller blades, characterised in that the system is supported by the rotary housing (7-8), in that the control means comprise an annular row of rotary actuators (16), and in that the mechanism for varying the pitch of the blades comprises a synchronisation ring (11) that is driven to rotate by rotary output shafts (17) of the actuators (16), the synchronisation ring (11) being guided in rotation relative to the rotary housing (7-8) by guide means and meshed by a first toothing (13) with pinions (14) of the blades (5).

Publication date: 2022-05-05
Applicant: Safran Aircraft Engines
Inventors: Eugene Henri Regis Servant

Publication number: None
Application number: 17/620,481

Abstract:
–

Publication date: –
Applicant: Safran Aircraft Engines
Inventors: Arnaud Bernard Clment Joudareff Thomas

How are Safran Aircraft Engines’s applications performing in USPTO?

Application Number Title Status Art Unit Examiner
17/628,608 Axial Turbine Engine, And Rectifier Stage With Variable Orientation Vanes For An Axial Turbine Engine Sent to Classification contractor – –
17/626,348 Turbomachine Module For A Propeller Having Variable-Pitch Blades And Turbomachine Comprising Same Docketed New Case – Ready for Examination OPAP Central, Docket
17/620,481 Method For Determining The Density Of Fuel For Metering Fuel In A Fuel Supply Circuit Of An Aircraft Engine Docketed New Case – Ready for Examination OPAP Central, Docket
17/619,505 Method For Coating A Turbomachine Guide Vane, Associated Guide Vane Docketed New Case – Ready for Examination OPAP Central, Docket
17/596,580 Method For Acquiring Data For Detecting Damage To A Bearing Docketed New Case – Ready for Examination OPAP Central, Docket