US 12,421,918 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. 19/060,234.
Application 19/060,234 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)] 27 Claims
OG exemplary drawing
 
13. 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 the length (LCORE) of the engine core is defined from the core forward bearing to the core aft bearing, and the 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 inlet area high-speed shaft rating parameter (HSP_AIN) that is greater than or equal to 1,038 in2 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_AIN is given by:

OG Complex Work Unit Math
 wherein AIN is an area at an inlet of the high-pressure compressor, RHUB,IN is a radius of a hub at the inlet of the high-pressure compressor, RTIP,IN is a radius of a tip of a high-pressure compressor blade at the inlet of the high-pressure compressor, and RTIP,EX is a radius of a tip of a high-pressure compressor blade at an exit stage of the high-pressure compressor, and
HSPX1 is a high-speed shaft operating parameter and is given by:

OG Complex Work Unit Math
 where NStg is a number of stages in the high-pressure compressor, AEX is an area of an exit stage of the high-pressure compressor, 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.