Invention Grant
- Patent Title: Gas turbine engine with ultra high pressure compressor
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Application No.: US15900891Application Date: 2018-02-21
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Publication No.: US11231043B2Publication Date: 2022-01-25
- Inventor: Veeraraju Vanapalli , Bhaskar Nanda Mondal , Jagata Laxmi Narasimharao , Tsuguji Nakano , Subramanian Narayanan
- Applicant: General Electric Company
- Applicant Address: US NY Schenectady
- Assignee: General Electric Company
- Current Assignee: General Electric Company
- Current Assignee Address: US NY Schenectady
- Agency: Dority & Manning, P.A.
- Main IPC: F04D29/32
- IPC: F04D29/32 ; F01D5/06 ; F01D25/24 ; F04D19/02 ; F01D5/14 ; F02C3/04
Abstract:
The present disclosure is directed to a gas turbine engine including a compressor rotor. The compressor rotor includes a first stage compressor airfoil defined at an upstream-most stage of the compressor rotor. The first stage compressor airfoil defines a first stage pressure ratio of at least approximately 1.7 during operation of the gas turbine engine at a tip speed of at least approximately 472 meters per second.
Public/Granted literature
- US20190257318A1 Gas Turbine Engine With Ultra High Pressure Compressor Public/Granted day:2019-08-22
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