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The patent badge is an abbreviated version of the USPTO patent document. The patent badge does contain a link to the full patent document.

The patent badge is an abbreviated version of the USPTO patent document. The patent badge covers the following: Patent number, Date patent was issued, Date patent was filed, Title of the patent, Applicant, Inventor, Assignee, Attorney firm, Primary examiner, Assistant examiner, CPCs, and Abstract. The patent badge does contain a link to the full patent document (in Adobe Acrobat format, aka pdf). To download or print any patent click here.

Patent No.:

US 12576979 B1

PDFFull Text
Date of Patent:
Mar. 17, 2026

Filed:

Feb. 29, 2024

Aircraft propulsion system with engine assembly, intercooler, and turbocompressor assembly

Applicant:

Pratt & Whitney Canada Corp., Longueuil, CA;

Inventors:

Nathan Tomes, Hamilton, CA;

Michel Bousquet, Longueuil, CA;

Assignee:

Pratt & Whitney Canada Corp., Longueuil, CA;

Attorney:

Getz Balich LLC

Primary Examiner:

Arfan Y Sinaki

Int. Cl.
CPC ...
B64D 27/33 (2024.01); B64D 33/08 (2006.01); B64U 10/14 (2023.01); B64U 20/94 (2023.01); B64U 20/96 (2023.01); B64U 50/12 (2023.01); B64U 50/19 (2023.01);
U.S. Cl.
CPC ...
B64D 27/33 (2024.01); B64D 33/08 (2013.01); B64U 20/94 (2023.01); B64U 20/96 (2023.01); B64U 50/12 (2023.01); B64U 50/19 (2023.01); B64U 10/14 (2023.01);
Abstract

A propulsion system for an aircraft includes an air intake, an engine assembly, a turbocompressor, an electrical assembly, and at least one propulsor. The engine assembly includes an engine. The engine includes an air inlet, an exhaust outlet, and an engine output shaft. The turbocompressor assembly includes a turbocompressor. The turbocompressor includes a turbine and a compressor. The turbine and the compressor form a rotational assembly. The rotational assembly includes a shaft, a bladed turbine rotor of the turbine, and a bladed compressor rotor of the compressor. The shaft interconnects the bladed turbine rotor and the bladed compressor rotor. The turbine includes a turbine inlet and a turbine outlet. The turbine inlet is connected in fluid communication with the exhaust outlet. The compressor includes a compressor inlet and a compressor outlet. The compressor inlet is connected in fluid communication with the air intake. The rotational assembly is mechanically independent of the engine output shaft.

Find Patent Forward Citations

Tomes, Nathan. (2026). Aircraft propulsion system with engine assembly, intercooler, and turbocompressor assembly (U.S. Patent No. 12576979). U.S. Patent and Trademark Office. https://idiyas.com/patent/badge/12576979

Data source: USPTO (United States Patent and Trademark Office) public patent records. Weekly synchronization. How IDiyas builds this profile

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