US Patent 8666632 Distributed aircraft engine fuel system
Patent 8666632 was granted and assigned to Hamilton Sundstrand on March, 2014 by the United States Patent and Trademark Office.
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Patent abstract
A gas turbine engine includes a plurality of fuel injectors grouped operatively by stages in a multistage combustor. A fuel system for the gas turbine engine includes at least one fuel metering module per stage of the multistage combustor. Each fuel metering module includes a pump, a flow meter, a pressure sensor, a controller, and a motor, which work together to control fuel output.
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US Patent 08666632 Distributed aircraft engine fuel system US Patent 8666632 Distributed aircraft engine fuel system
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Patent Number
0866663200
Patent Number
866663200
Edits on 22 Apr, 2023
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Current Assignee
Patent Jurisdiction
Patent Number
086666320
Date of Patent
March 4, 2014
0Patent Application Number
130904120
Date Filed
April 20, 2011
0Official Website
Patent Primary Examiner
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Is a
Current Assignee
Patent Jurisdiction
Patent Number
086666320
Date of Patent
March 4, 2014
0Patent Application Number
130904120
Date Filed
April 20, 2011
0Official Website
Patent Primary Examiner
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US Patent 08666632 Distributed aircraft engine fuel system
Infobox
Is a
Current assignee
Patent jurisdiction
Patent number
08666632
Date of patent
March 4, 2014
Patent application number
13090412
Date Filed
April 20, 2011
Patent primary examiner
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