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US Patent 10583932 Aero engine flow rate

Patent 10583932 was granted and assigned to Rolls-Royce on March, 2020 by the United States Patent and Trademark Office.

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US Patent 12104530 Gas turbine engine

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Edits on 18 Sep, 2024

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US Patent 12092037 Gas turbine engine with electric machines

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edited on 18 Sep, 2024

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US Patent 12092030 Gas turbine engine

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US Patent 12006055 Gas turbine engine with electric machines

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US Patent 11993387 Gas turbine engine

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US Patent 11994067 Gas turbine engine

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US Patent 11988169 Fan arrangement for a gas turbine engine

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US Patent 11920540 Gas turbine engine with a defined fan axis angle between a fan tip axis and a centerline

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edited on 11 Dec, 2023

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Patent abstract

A gas turbine engine of an aircraft includes: an engine core having a turbine including a lowest pressure rotor stage, a turbine diameter, a fan including a plurality of fan blades extending from a hub, an annular fan face at a leading edge of the fan; wherein a downstream blockage ratio is:

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US Patent 11761380 Turbofan gas turbine engine

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US Patent 11359549 Aircraft engine

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US Patent 11339713 Large-scale bypass fan configuration for turbine engine core and bypass flows

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Patent Citations Received

US Patent 10844721 Gas turbine engine for an aircraft

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edited on 22 Mar, 2023

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Is a

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Patent Applicant

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Current Assignee

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Patent Jurisdiction

United States Patent and Trademark Office

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Patent Number

105839320

Date of Patent

March 10, 2020

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Patent Application Number

163989090

Date Filed

April 30, 2019

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Patent Citations Received

US Patent 10844721 Gas turbine engine for an aircraft

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US Patent 11053947 Turbine engine

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US Patent 11339713 Large-scale bypass fan configuration for turbine engine core and bypass flows

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US Patent 11352958 Aircraft gas turbine engine with improved response to rotor unbalance

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US Patent 11359549 Aircraft engine

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Patent Primary Examiner

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Edits on 26 Sep, 2022

"update citations for inverse infoboxes"

edited on 26 Sep, 2022

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Patent Citations Received

US Patent 11352958 Aircraft gas turbine engine with improved response to rotor unbalance

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"update citations for inverse infoboxes"

edited on 26 Sep, 2022

Infobox

Patent Citations Received

US Patent 11053947 Turbine engine

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"update citations for inverse infoboxes"

edited on 26 Sep, 2022

Infobox

Patent Citations Received

US Patent 10844721 Gas turbine engine for an aircraft

0

Edits on 26 Sep, 2022

"Entity importer update"

edited on 26 Sep, 2022

Infobox

Is a

0

Patent Applicant

0

Current Assignee

0

Patent Jurisdiction

United States Patent and Trademark Office

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Patent Number

105839320

Date of Patent

March 10, 2020

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Patent Application Number

163989090

Date Filed

April 30, 2019

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Patent Citations Received

US Patent 10844721 Gas turbine engine for an aircraft

0

US Patent 11053947 Turbine engine

0

US Patent 11339713 Large-scale bypass fan configuration for turbine engine core and bypass flows

0

US Patent 11352958 Aircraft gas turbine engine with improved response to rotor unbalance

0

US Patent 11359549 Aircraft engine

0

Patent Primary Examiner

0

Edits on 23 Sep, 2022

"update citations for inverse infoboxes"

edited on 23 Sep, 2022

Infobox

Patent Citations Received

US Patent 11339713 Large-scale bypass fan configuration for turbine engine core and bypass flows

0

Edits on 23 Sep, 2022

"update citations for inverse infoboxes"

edited on 23 Sep, 2022

Infobox

Patent Citations Received

US Patent 11359549 Aircraft engine

0

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