Gas turbine engine arrangement with ultra high pressure compressor

Number of patents in Portfolio can not be more than 2000

United States of America Patent

PATENT NO 10823191
APP PUB NO 20190285082A1
SERIAL NO

15922153

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ATTORNEY / AGENT: (SPONSORED)

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Abstract

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The present disclosure is directed to a gas turbine engine including a first frame comprising a first bearing assembly, a second frame comprising a second bearing assembly, and a compressor rotor. A first stage compressor airfoil is defined at an upstream-most stage of the compressor rotor. The compressor rotor is rotatable via the first bearing assembly and the second bearing assembly. The first stage compressor airfoil is disposed between the first bearing assembly and the second bearing assembly.

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Patent Owner(s)

Patent OwnerAddress
GENERAL ELECTRIC COMPANY1 RIVER ROAD SCHENECTADY NY 12345

International Classification(s)

Inventor(s)

Inventor Name Address # of filed Patents Total Citations
Kollam, Ramana Reddy Bangalore, IN 3 6
Mondal, Bhaskar Nanda Bangalore, IN 60 299
Vanapalli, Veeraraju Bangalore, IN 19 33
Wankhade, Rajendra Mahadeorao Bangalore, IN 10 15

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