US 12,460,574 B2
Gas turbine engine having cooling systems
Jeffrey Douglas Rambo, Mason, OH (US)
Assigned to General Electric Company, Evendale, OH (US)
Filed by General Electric Company, Schenectady, NY (US)
Filed on Apr. 24, 2024, as Appl. No. 18/644,332.
Prior Publication US 2025/0334071 A1, Oct. 30, 2025
Int. Cl. F02C 6/08 (2006.01); F02C 7/18 (2006.01); F02C 9/18 (2006.01)
CPC F02C 6/08 (2013.01) [F02C 7/18 (2013.01); F02C 9/18 (2013.01)] 17 Claims
OG exemplary drawing
 
17. A gas turbine engine, comprising:
an accessory system; and
a turbomachine comprising a compressor section, a combustion section defining a compressor discharge cavity, and a turbine section collectively defining in part a working gas flowpath, the compressor section comprising a low pressure compressor and a high pressure compressor, the turbomachine further comprising:
a reverse bleed system comprising a reverse bleed duct and an RBS blower in fluid communication with the reverse bleed duct, the reverse bleed duct in fluid communication with the working gas flowpath through an outlet of the reverse bleed duct, wherein the reverse bleed duct is further in fluid communication with a cold location of the gas turbine engine as an airflow source for the reverse bleed system; and
an accessory cooling system comprising a cooling duct defining an inlet in fluid communication with the reverse bleed duct, the cooling duct comprising a cooling tip oriented towards the accessory system to provide an airflow onto the accessory system;
wherein the turbomachine comprises an operability bleed assembly comprising an operability bleed duct extending between an inlet of the operability bleed duct in fluid communication with the working gas flowpath at a location between the low pressure compressor and the high pressure compressor and an outlet of the operability bleed duct, wherein an inlet of the reverse bleed system is in fluid communication with the operability bleed duct.