US 12,392,307 B2
High-speed shaft rating for turbine engines
Bhaskar Nanda Mondal, Bengaluru (IN); Narayanan Payyoor, Bengaluru (IN); and Pranav Kamat, Bengaluru (IN)
Assigned to GENERAL ELECTRIC COMPANY, Evendale, OH (US)
Filed by General Electric Company, Schenectady, NY (US)
Filed on Jun. 6, 2023, as Appl. No. 18/330,155.
Claims priority of application No. 202311020971 (IN), filed on Mar. 24, 2023.
Prior Publication US 2024/0318614 A1, Sep. 26, 2024
Int. Cl. F02K 3/075 (2006.01); F02C 3/06 (2006.01)
CPC F02K 3/075 (2013.01) [F02C 3/06 (2013.01)] 30 Claims
OG exemplary drawing
 
24. A turbomachine engine comprising:
an engine core including a high-pressure compressor, a high-pressure turbine, and a combustion chamber in flow communication with the high-pressure compressor and the high-pressure turbine, the engine core including a core forward bearing and a core aft bearing, the core forward bearing being positioned forward of a stage of the high-pressure compressor and the core aft bearing being positioned aft of a stage of the high-pressure turbine, the engine core having a length (LCORE) defined from the core forward bearing to the core aft bearing, and the high-pressure compressor having an exit stage diameter (DCORE), wherein a number of stages in the high-pressure compressor is one of eight stages, nine stages, ten stages, or eleven stages, and the high-pressure turbine includes one stage or two stages; and
a high-pressure shaft coupled to the high-pressure compressor and the high-pressure turbine, the high-pressure shaft characterized by a high-speed shaft rating (HSR) from 1.5 to 6.2, and a ratio of LCORE/DCORE is greater than or equal to 2.1 and less than

OG Complex Work Unit Math
wherein HSR is given by:

OG Complex Work Unit Math
where N2R/L is a redline speed of the high-pressure shaft, and k is a constant with a value of 106 inch-RPM,
wherein HSPX is given by:

OG Complex Work Unit Math
where NStg is the number of stages in the high-pressure compressor, AEX is an area of an exit stage of the high-pressure compressor, PSTD is standard pressure, OPRT/O is an overall pressure ratio of the turbomachine engine at takeoff flight conditions corresponding to a maximum thrust rating for an engine core configuration, and FNT/O is a sea-level static thrust of the turbomachine engine at takeoff flight conditions corresponding to the maximum thrust rating for the engine core configuration.