US 12,345,212 B2
Turbine engine with auxiliary coolant injection
Jose R. Paulino, Jupiter, FL (US); and Steven W. Burd, Cheshire, CT (US)
Assigned to RTX CORPORATION, Farmington, CT (US)
Filed by RTX CORPORATION, Farmington, CT (US)
Filed on Nov. 21, 2023, as Appl. No. 18/515,400.
Prior Publication US 2025/0163856 A1, May 22, 2025
Int. Cl. F02C 9/00 (2006.01); F02C 7/18 (2006.01); F02C 9/28 (2006.01)
CPC F02C 9/28 (2013.01) [F02C 7/18 (2013.01)] 15 Claims
OG exemplary drawing
 
1. An aircraft propulsion system comprising:
a core engine including a core flow path where air is compressed in a compressor section, communicated to a combustor section, mixed with fuel, and ignited to generate a gas flow that is expanded through a turbine section;
a coolant chamber where a quantity of coolant is stored;
at least one coolant flow regulator for distributing the coolant from the coolant chamber to a location within the core flow path of the core engine;
a controller programed to operate the at least one coolant flow regulator based on a predefined operation profile, wherein the predefined operation profile includes a first operating period where no coolant is distributed from the coolant chamber followed by at least one second operating period where the coolant is supplied to the location within the core flow path, and a third operating period after the quantity of the coolant in the chamber is exhausted.