US 12,134,984 B1
Fluidic compressor inlet guide vanes
Simon W. Evans, Farmington, CT (US); and Christopher J. Hanlon, Sturbridge, MA (US)
Assigned to RTX CORPORATION, Farmington, CT (US)
Filed by RTX CORPORATION, Farmington, CT (US)
Filed on Nov. 17, 2023, as Appl. No. 18/512,433.
Int. Cl. F02C 7/143 (2006.01); B64D 33/08 (2006.01)
CPC F02C 7/1435 (2013.01) [B64D 33/08 (2013.01); F05D 2260/211 (2013.01)] 17 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;
an intercooling system configured to inject water into the compressor section to reduce a temperature of a core airflow within the core flow path, the intercooling system including a plurality of injectors for injecting an intercooling waterflow into a portion of a compressor passage, wherein the plurality of injectors are spaced apart about the compressor passage and the injection of the intercooling water flow is varied between the plurality of injectors to influence flow communicated to the high pressure compressor; and
a controller programmed to determine a distortion profile of a combined pressurized air and water flow, and control injection of waterflow through the plurality of injectors to generate the determined distortion profile by varying at least one of a volume and pressure of the intercooling water flow between the plurality of injectors based on the determined distortion profile within a compressor passage between the low pressure compressor and the high pressure compressor.