Fluidic compressor inlet guide vane

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 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;
• an annular passage for directing an airflow from an exit of the low pressure compressor to an inlet of the high pressure compressor, wherein the plurality of injectors is disposed within the annular passage for generating the defined swirl of the combined airflow and water through the annular passage to the inlet of the high pressure compressor;
• and
• a synchronization assembly to which the plurality of injectors are attached, wherein the synchronization assembly is actuatable to vary the water injection angle and the plurality of injectors are spaced circumferentially apart about an outer radial surface of the annular passage.

An intercooling system for a turbine engine comprising:

• a condenser arranged along a core flow path and configured to extract water from an exhaust gas flow;
• a pump where water from the condenser is pressurized;
• a plurality of injectors where a pressurized water flow is injected into the core flow path within a compressor section;
• and
• at least one actuator coupled to the plurality of injectors and a controller,
• wherein the controller is configured to control the actuator to move the plurality of injectors to vary a water injection angle relative to an inlet airflow and generate a defined swirl of a combined airflow and water to an inlet of the compressor section.

A method of operating a compressor section of a turbine engine comprising:

• generating a pressurized airflow through a first compressor section;
• injecting, using at least one injector coupled to an actuator, a pressurized water flow at a first water injection angle relative to the pressurized airflow generated in the first compressor section to generate a combined pressurized air and water flow with a resultant swirl angular flow component;
• communicating the combined pressurized air and water flow to a second compressor section downstream of the first compressor section;
• and
• based upon an engine operating point, controlling the actuator to move the at least one injector to change the first water injection angle to a second water injection angle.