US Patent 12129804 Shifted bleed valve modulation detection

An aircraft engine includes a compressor section including an engine compressor and a bleed off valve (BOV) fluidically coupled to the compressor section. A controller is configured to determine at least one real-time compressor delivery pressure in the compressor section and to determine whether at least one fault is present in the aircraft engine based on a comparison between the at least one real-time compressor delivery pressure and at least one predetermined nominal compressor delivery pressure resulting from a non-faulty BOV valve and a non-faulty compressor.