US Patent 9958161 Combustor for gas turbine engine
Patent 9958161 was granted and assigned to Pratt & Whitney Canada on May, 2018 by the United States Patent and Trademark Office.
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Patent abstract
A gas turbine engine comprises an annular combustor chamber formed between an inner liner and an outer liner. An annular upstream zone is adapted to receive fuel and air from an annular nozzle. An annular mixing zone is located downstream of the upstream zone. The mixing zone has a reduced radial height relative a downstream combustion zone of the combustion chamber, the mixing zone defined by straight wall sections.
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US Patent 09958161 Combustor for gas turbine engine US Patent 9958161 Combustor for gas turbine engine
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Patent Number
0995816100
Patent Number
995816100
Edits on 22 Mar, 2023
Golden AI
Infobox
Is a
Patent Applicant
Current Assignee
Patent Jurisdiction
Patent Number
099581610
Date of Patent
May 1, 2018
0Patent Application Number
137950820
Date Filed
March 12, 2013
0Patent Primary Examiner
Edits on 28 Sep, 2022
Golden AI
Infobox
Is a
Patent Applicant
Current Assignee
Patent Jurisdiction
Patent Number
099581610
Date of Patent
May 1, 2018
0Patent Application Number
137950820
Date Filed
March 12, 2013
0Patent Primary Examiner
Edits on 20 Jan, 2022
Golden AI
Edits made to:
Infobox (+9 properties)
US Patent 09958161 Combustor for gas turbine engine
Infobox
Is a
Patent applicant
Current assignee
Patent jurisdiction
Patent number
09958161
Date of patent
May 1, 2018
Patent application number
13795082
Date Filed
March 12, 2013
Patent primary examiner
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