US 12,215,624 B1
Fluidic compressor inlet guide vane
Simon W. Evans, Farmington, CT (US); and Brandon M. Evans, San Antonio, TX (US)
Assigned to RTX CORPORATION, Farmington, CT (US)
Filed by RTX CORPORATION, Farmington, CT (US)
Filed on Nov. 17, 2023, as Appl. No. 18/512,388.
Int. Cl. F02C 7/16 (2006.01); F02C 3/06 (2006.01); F02C 3/30 (2006.01)
CPC F02C 7/16 (2013.01) [F02C 3/06 (2013.01); F02C 3/30 (2013.01); F05D 2220/323 (2013.01); F05D 2260/212 (2013.01); F05D 2270/08 (2013.01)] 19 Claims
OG exemplary drawing
 
1. A propulsion system for an aircraft 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 high energy gas flow that is expanded through a turbine section, wherein the compressor section includes a low pressure compressor upstream of a high pressure compressor and an annular passage for directing an airflow from an exit of the low pressure compressor to an inlet of the high pressure compressor; and
an intercooling system configured to inject water into the compressor section to reduce a temperature of a core airflow within the core flow path, wherein the intercooling system includes a plurality of injectors for injecting water at a water injection angle relative to an airflow to generate a defined swirl of a combined airflow and water to the compressor section and an actuator, coupled to at least one of the plurality of injectors, configured to move the one injector to change the water injection angle of the one at least one injector.