US 12,421,905 B2
Thermal energy system to minimize or eliminate rotor bow
Govindaraj Kalyanasamy, Indianapolis, IN (US); and Peter Schenk, Indianapolis, IN (US)
Assigned to Rolls-Royce North American Technologies, Inc., Indianapolis, IN (US); and Rolls-Royce Corporation, Indianapolis, IN (US)
Filed by Rolls-Royce North American Technologies, Inc., Indianapolis, IN (US); and Rolls-Royce Corporation, Indianapolis, IN (US)
Filed on Apr. 20, 2023, as Appl. No. 18/304,129.
Prior Publication US 2024/0352895 A1, Oct. 24, 2024
Int. Cl. F01D 25/10 (2006.01); F01D 25/08 (2006.01); F02C 9/00 (2006.01); F02C 9/18 (2006.01)
CPC F02C 9/00 (2013.01) [F01D 25/08 (2013.01); F01D 25/10 (2013.01); F02C 9/18 (2013.01); F05D 2260/20 (2013.01)] 12 Claims
OG exemplary drawing
 
1. A system comprising:
a thermal energy system configured to transport thermal energy harvested from a first portion of a gas turbine engine positioned above an engine centerline to a second portion of the gas turbine engine positioned below the engine centerline after the gas turbine engine was in operation, wherein the transported thermal energy minimizes or prevents undesired contact or seizing of a rotor with another component of the gas turbine engine due to warping of the rotor due to uneven cooling of the gas turbine engine after the operation,
wherein the thermal energy system includes a cavity defined by a jacket surrounding an axial segment of a core case surrounding an axial segment of a core case of the gas turbine engine and configured to flow a fluid, the fluid comprising oil or a refrigerant, wherein the fluid is configured to transport thermal energy from the first portion to the second portion,
a pump fluidically connected to the cavity; and
a controller operable to control the pump and receive signals indicative of a sensed temperature in the first portion of the gas turbine engine and the second portion of the gas turbine engine, wherein the controller is configured to:
cause the pump to circulate the fluid to transport thermal energy from the first portion to the second portion of the gas turbine engine until the temperature in the second portion of the gas turbine engine matches the sensed temperature in the first portion of the gas turbine engine.