Gas turbine combustor having a plurality of angled vanes circumferentially spaced within the combustor

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United States of America Patent

PATENT NO 11434831
SERIAL NO

16295542

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Abstract

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A gas turbine engine includes: a compressor section including a compressor mean radius; a combustor section fluidly coupled downstream of the compressor section and include a combustor mean radius; and a turbine section fluidly coupled downstream of the combustor section and a turbine mid-span radius. The combustor mean radius is greater than each of the compressor mean radius and the turbine mid-span radius.

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Patent Owner(s)

Patent OwnerAddress
GENERAL ELECTRIC COMPANY1 NEUMANN WAY MAIL DROP F16 EVENDALE OH 45215-6301

International Classification(s)

Inventor(s)

Inventor Name Address # of filed Patents Total Citations
Silkowski, Peter Daniel Scotia, US 9 18

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