Pratt & Whitney Canada Corp Patent Portfolio Statistics

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Pratt & Whitney Canada Corp.

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 Pratt & Whitney Canada Corp. look like?

Assignee Art Units
Total Applications: 2,313 2,296,846
Granted Patents: 1,763 1,463,622
Grant Index 90.09% ↑ 77.23%
Abandoned/Rejected Applications: 194 (9.91%) 431,616 (22.77%)
In-Process Applications: 346 401,608
Average Grant Time: 3.01 Years ↑ 2.59 Years
Average Office Actions: 1.59 ↑ 1.46

Which Technology Area Pratt & Whitney Canada Corp. is filing most patents in? (Last 10 years)

Art Unit Definition Total Applications
3741 Thermal & Combustion Technology, Motive & Fluid Power Systems 522
3745 Thermal & Combustion Technology, Motive & Fluid Power Systems 520
3746 Thermal & Combustion Technology, Motive & Fluid Power Systems 193
3748 Thermal & Combustion Technology, Motive & Fluid Power Systems 94
3726 Manufacturing Devices & Processes, Machine Tools & Hand Tools 80

How many patents are Pratt & Whitney Canada Corp. filing every year?

Year Total Applications Predicted
2022 0* 825
2021 36* 698
2020 180 557
2019 342 342
2018 171 –
2017 157 –
2016 151 –
2015 110 –
2014 113 –
2013 107 –

*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 Pratt & Whitney Canada Corp. in USPTO?

Publication number: US20220106032A1
Application number: 17/644,101

Abstract:
There is disclosed an aircraft engine assembly including an engine having an engine shaft; an output shaft; a clutch in driving engagement between the engine shaft and the output shaft. The clutch has a first component in driving engagement with the engine shaft and a second component. The clutch is operable between first and second configurations. In the first configuration, the first component is rotatable relative to the second component and the engine shaft is rotatable relative to the output shaft. In the second configuration, the first and second components are engaged with one another and the engine shaft rotates with the output shaft. A mechanical lock is operable between first and second positions. In the first position, the mechanical lock is disengaged from the first component. In the second position, the first and second components are secured for joint rotation one relative to the other.

Publication date: 2022-04-07
Applicant: Pratt & Whitney Canada Corp.
Inventors: Berube Stephane

Publication number: US20220098990A1
Application number: 17/545,415

Abstract:
A single-crystal turbine blade and a method of making such single-crystal turbine blade are disclosed. During manufacturing, a secondary crystallographic orientation of the material of the single-crystal turbine blade is controlled based on a parameter of a root fillet between an airfoil of the single-crystal turbine blade and a platform of the single-crystal turbine blade. The parameter can be a location of peak stress in the root fillet expected during use of the turbine blade.

Publication date: 2022-03-31
Applicant: Pratt & Whitney Canada Corp.
Inventors: Huszar Robert

Publication number: US20220089273A1
Application number: 17/538,298

Abstract:
There is provided a pitch control assembly for a rotor of an aircraft, the rotor rotatable about a longitudinal axis and having blades each rotatable about a span-wise axis to adjust a blade pitch angle thereof, the assembly comprising a plurality of position markers spaced circumferentially around the longitudinal axis and having lengths along the longitudinal axis which vary monotonically and incrementally, at least one sensor configured for producing at least one sensor signal in response to detecting a relative movement between the plurality of position markers and the at least one sensor, and a control unit communicatively coupled to the at least one sensor and configured to generate a feedback signal indicative of the blade pitch angle in response to the at least one sensor signal received from the at least one sensor.

Publication date: 2022-03-24
Applicant: Pratt & Whitney Canada Corp.
Inventors: Dana Tomescu

How are Pratt & Whitney Canada Corp.’s applications performing in USPTO?

Application Number Title Status Art Unit Examiner
17/644,101 Aircraft Engine With Clutch And Mechanical Lock Docketed New Case – Ready for Examination OPAP Central, Docket
17/545,415 Method Of Making A Single-Crystal Turbine Blade Docketed New Case – Ready for Examination OPAP Central, Docket
17/538,298 Pitch Control Assembly For An Aircraft-Bladed Rotor Docketed New Case – Ready for Examination OPAP Central, Docket
17/517,176 Fixture For Holding A Rod Guide Assembly Of A Fuel Control Unit Of An Aircraft Engine During Welding – 3726 Averick, Lawrence
17/517,123 Method Of Repairing A Rod Guide Assembly Of A Fuel Control Unit Non Final Action Mailed 3726 Averick, Lawrence