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US Patent 12071903 Assisted engine start bleed system

OverviewStructured DataIssuesContributorsActivity
Is a
Patent
Patent
0
Date Filed
May 1, 2020
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Date of Patent
August 27, 2024
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Patent Applicant
Raytheon Technologies
Raytheon Technologies
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Patent Application Number
16864881
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Patent Citations
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US Patent 9611752 Compressor start bleed system for a turbine system and method of controlling a compressor start bleed system
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US Patent 9822662 Cooling system with compressor bleed and ambient air for gas turbine engine
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US Patent 10100744 Aircraft bleed air and engine starter systems and related methods
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US Patent 10125724 Start system for gas turbine engines
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US Patent 10670473 Sensor with integral vortex tube for warming
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US Patent 11067007 Gas turbine and method for operating gas turbine
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US Patent 10724443 Turbine engine and method of operating
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US Patent 7143573 Gas turbine set
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US Patent 7246482 Gas turbine engine bleed air power assist system and method
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US Patent 8099966 System and method for controlling an environment in an aircraft using a vortex cooler
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•••
Patent Inventor Names
Daniel Bernard Kupratis
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Martin Richard Amari
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Geoffrey T. Blackwell
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Patent Jurisdiction
United States Patent and Trademark Office
United States Patent and Trademark Office
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Patent Number
12071903
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Patent Primary Examiner
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Woody A Lee, Jr.
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CPC Code
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B01D 53/005
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B01D 53/24
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B01D 2259/4575
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B64D 15/04
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F05D 2240/127
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F05D 2260/209
0
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F05D 2260/606
0
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F05D 2260/85
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B01D 53/00
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F02C 9/18
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•••

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