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US Patent 11041443 Multi-spool gas turbine engine architecture

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Patent abstract

A multi-spool gas turbine engine comprises a low pressure (LP) spool and a high pressure (HP) spool independently rotatable about a central axis extending through an accessory gear box (AGB). The LP spool has an LP compressor, which is axially positioned between the HP compressor of the HP spool and the AGB. A tower shaft drivingly connects the HP spool to the AGB.

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Patent Inventor Names
Eric Durocher0
Jean Dubreuil0
Keith Morgan0
Lazar Mitrovic0
Martin Poulin0
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Patent Citations Received
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US Patent 11668253 System and method for providing in-flight reverse thrust for an aircraft
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Official Website
https://pdfpiw.uspto.gov/.piw?Docid=110414430
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Infobox
Is a
Patent
Patent
0
Patent Jurisdiction
United States Patent and Trademark Office
United States Patent and Trademark Office
0
Patent Number
110414430
Date of Patent
June 22, 2021
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Patent Application Number
165838960
Date Filed
September 26, 2019
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Official Website
https://pdfpiw.uspto.gov/.piw?Docid=110414430
Patent Citations
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US Patent 10054001 V-shaped gearbox for driving turbomachine equipment
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US Patent 10072570 Reverse flow gas turbine engine core
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US Patent 10082080 Fan rotor for a turbo machine such as a multiple flow turbojet engine driven by a reduction gear
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US Patent 10087761 Devices and methods for balancing a high-pressure spool of a gas turbine engine
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US Patent 10094295 Gas turbine engine with transmission
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US Patent 10113482 Gearbox for gas turbine engine
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US Patent 10125722 Turbine engine with a turbo-compressor
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Patent Primary Examiner
Ehud Halberstam
Ehud Halberstam
0
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Website URL
https://pdfpiw.uspto.gov/.piw?Docid=11041443
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 US Patent 11041443 Multi-spool gas turbine engine architecture

Infobox
Is a
Patent
Patent
Patent jurisdiction
United States Patent and Trademark Office
United States Patent and Trademark Office
Patent number
11041443
Date of patent
June 22, 2021
Patent application number
16583896
Date Filed
September 26, 2019
Patent citations
‌
US Patent 10054001 V-shaped gearbox for driving turbomachine equipment
‌
US Patent 10072570 Reverse flow gas turbine engine core
‌
US Patent 10082080 Fan rotor for a turbo machine such as a multiple flow turbojet engine driven by a reduction gear
‌
US Patent 10087761 Devices and methods for balancing a high-pressure spool of a gas turbine engine
‌
US Patent 10094295 Gas turbine engine with transmission
‌
US Patent 10113482 Gearbox for gas turbine engine
‌
US Patent 10125722 Turbine engine with a turbo-compressor
Patent primary examiner
Ehud Halberstam
Ehud Halberstam

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