US 11,933,232 B1
Hybrid-electric gas turbine engine and method of operating
Timothy L. Schelfaut, Lebanon, OH (US); Timothy M. Kasberg, Liberty Township, OH (US); Tyler F. Hooper, Amesbury, MA (US); Massimo Rufo, Woburn, MA (US); Kevin Graziano, Liberty Township, OH (US); and Brendon Leeker, Cincinnati, OH (US)
Assigned to General Electric Company, Schenectady, NY (US)
Filed by GENERAL ELECTRIC COMPANY, Schenectady, NY (US)
Filed on Feb. 21, 2023, as Appl. No. 18/171,942.
Int. Cl. F01D 11/18 (2006.01); F02C 6/00 (2006.01); F02C 7/36 (2006.01); F02C 9/56 (2006.01)
CPC F02C 9/56 (2013.01) [F02C 6/00 (2013.01); F02C 7/36 (2013.01); F05D 2220/32 (2013.01); F05D 2220/70 (2013.01); F05D 2270/05 (2013.01); F05D 2270/13 (2013.01)] 20 Claims
OG exemplary drawing
 
13. A hybrid-electric gas turbine engine, comprising:
a core including a casing enclosing a compressor, combustor, and turbine, with at least first and second spools, the first spool defined by a first set of compressor blades and a first set of turbine blades coupled to a rotatable first shaft, a first electric machine rotatably coupled to the rotatable first shaft, and the second spool defined by a second set of compressor blades and a second set of turbine blades coupled to a rotatable second shaft; and
a control system including a control module having one or more processors and one or more memory devices, the one or more memory devices storing instructions that when executed by the one or more processors cause the one or more processors to perform operations, in performing the operations, the one or more processors are configured to:
receive an input indicative of a change in a thrust demand to the gas turbine engine;
determine a first rate of change of thrust attributable to combustion in the combustor and a second rate of change of thrust attributable to the first electric machine to cooperatively satisfy the change in thrust demand;
determine a current first clearance between the casing and at least one of the first set of turbine blades and the first set of compressor blades;
determine that operation of the combustor in accordance with the first rate of change of thrust and the first electric machine in accordance with the second rate of change of thrust will cause the current first clearance to exceed a predetermined first differential threshold;
determine a third rate of change of thrust attributable to the first electric machine to satisfy the change in thrust demand in cooperation with the first rate of change of thrust, that will satisfy the change in thrust demand and not exceed the first differential threshold; and
operate the combustor according to the first rate of change of thrust and operate the first electric machine according to the third rate of change of thrust.