COMBUSTOR SIZE RATING FOR A GAS TURBINE ENGINE USING HYDROGEN FUEL
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United States of America Patent
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Issued Date -
Sep 5, 2024
app pub date -
May 10, 2024
filing date -
Dec 3, 2021
priority date (Note) -
Published
status (Latency Note)
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Importance

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Abstract
A gas turbine engine includes a hydrogen fuel delivery assembly configured to deliver a hydrogen fuel flow, a compressor section configured to compress air flowing therethrough to provide a compressed air flow, and a combustor including a combustion chamber having a burner length and a burner dome height. The combustion chamber is configured to combust a mixture of the hydrogen fuel flow and the compressed air flow. The combustion chamber can be characterized by a combustor size rating between one inch and seven inches. In more detail, the combustion chamber can be characterized by the combustor size rating between one inch and seven inches at a core air flow parameter between two and one half kN and sixty kN, in which the combustor size rating is a function of the core air flow parameter.
First Claim
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Family

- 15 United States
- 10 France
- 8 Japan
- 7 China
- 5 Korea
- 2 Other
Patent Owner(s)
Patent Owner | Address | |
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GENERAL ELECTRIC COMPANY | A CORP OF NEW YORK |
International Classification(s)

- 2024 Application Filing Year
- F23R Class
- 111 Applications Filed
- 9 Patents Issued To-Date
- 8.11 % Issued To-Date
Inventor(s)
Inventor Name | Address | # of filed Patents | Total Citations |
---|---|---|---|
Benjamin, Michael A | Cincinnati, US | 116 | 710 |
# of filed Patents : 116 Total Citations : 710 | |||
Giridharan, Manampathy G | Mason, US | 51 | 773 |
# of filed Patents : 51 Total Citations : 773 |
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Patent Citation Ranking
- 0 Citation Count
- F23R Class
- 0 % this patent is cited more than
- 1 Age
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