US 12,486,819 B1
High-speed shaft rating for turbine engines
Bhaskar Nanda Mondal, Bengaluru (IN); Narayanan Payyoor, Thrissur (IN); and Pranav Kamat, Bengaluru (IN)
Assigned to GENERAL ELECTRIC COMPANY, Evendale, OH (US)
Filed by General Electric Company, Evendale, OH (US)
Filed on Feb. 21, 2025, as Appl. No. 19/060,252.
Application 19/060,252 is a continuation of application No. 18/330,155, filed on Jun. 6, 2023.
Claims priority of application No. 202311020971 (IN), filed on Mar. 24, 2023.
Int. Cl. F02K 3/075 (2006.01); F02C 3/06 (2006.01); F02K 3/06 (2006.01)
CPC F02K 3/075 (2013.01) [F02C 3/06 (2013.01); F02K 3/06 (2013.01); F05D 2200/13 (2013.01); F05D 2200/14 (2013.01); F05D 2200/211 (2013.01); F05D 2200/221 (2013.01)] 28 Claims
OG exemplary drawing
 
16. 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, wherein the engine core further includes 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, and a length (LCORE) of the engine core is defined from the core forward bearing to the core aft bearing, and a diameter (DCORE) of the engine core is an exit stage diameter of the high-pressure compressor;
a power turbine in flow communication with the high-pressure turbine;
a low-pressure shaft coupled to the power turbine; 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 wherein the high-pressure shaft is further characterized by an exit rim speed high-speed shaft rating (HSP_URIM,R/L) is greater than or equal to 0.09 in−2/3(ft/s/° R)−3 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,
HSP_URIM,R/L is given by:

OG Complex Work Unit Math
where Nstg is a number of stages of the high-pressure compressor, T3T/O is a temperature at an exit of the high-pressure compressor at takeoff flight conditions, AF,IN is a frontal area of the high-pressure compressor, and URIM,R/L is an exit rim speed of the high-pressure compressor at redline speeds of the high-pressure shaft, and
HSPX is given by:

OG Complex Work Unit Math
where 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.