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US 12,129,804 B1Granted
Shifted bleed valve modulation detection
AssigneePratt & Whitney Canada Corp.
InventorLouis Duranleau-Hendrickx
Life of this patent
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Abstract
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.
Claims14
An aircraft engine comprising:
- a compressor section including an engine compressor;
- a bleed off valve (BOV) fluidically coupled to the compressor section;
- and
- a controller 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,
- wherein the at least one fault includes one or both of a first fault present in the BOV and a second fault present in the compressor section, the at least one real-time compressor delivery pressure includes a first real-time compressor delivery pressure (P3CLP) and a second real-time compressor delivery pressure (P3CHP) that is greater than the first real-time compressor delivery pressure, and the at least one predetermined nominal compressor delivery pressure includes a first predetermined nominal compressor delivery pressure (P3LP) and a second predetermined nominal compressor delivery pressure (P3HP) that is greater than the first predetermined nominal compressor delivery pressure (P3LP), and
- wherein the controller determines a presence of the first fault in the BOV in response to the second real-time compressor delivery pressure (P3CHP) being lower than the second predetermined nominal compressor delivery pressure (P3HP) and the first real-time compressor delivery pressure (P3CLP) being equal or greater than the first predetermined nominal compressor delivery pressure (P3LP).
3 more elements
A method of diagnosing an aircraft engine, the method comprising:
- fluidically coupled a bleed off valve (BOV) to a compressor section which includes an engine compressor of the aircraft engine;
- and
- determining, using a controller, at least one real-time compressor delivery pressure in the compressor section;
- comparing, by the controller, 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;
- determining, using the controller, whether at least one fault is present in the aircraft engine based on the comparison, the at least one fault including one or both of a first fault present in the BOV and a second fault present in the compressor section;
- determining one or both of a first fault present in the BOV and a second fault present in the compressor section;
- determining a first real-time compressor delivery pressure (P3CLP) and a second real-time compressor delivery pressure (P3CHP) that is greater than the first real-time compressor delivery pressure;
- determining a first predetermined nominal compressor delivery pressure (P3LP) and a second predetermined nominal compressor delivery pressure (P3HP) that is greater than the first predetermined nominal compressor delivery pressure (P3LP);
- and
- determining a presence of the second fault in the compressor section in response to the first real-time compressor delivery pressure (P3CLP) being lower than the first predetermined nominal compressor delivery pressure (P3LP) and the second real-time compressor delivery pressure (P3CHP) being lower than the second predetermined nominal compressor delivery pressure (P3HP).
7 more elements
Dependencies are inferred from the claim text.