An abnormality diagnosing method includes a model generation step of generating a simulation model of a monitoring target, an operation start step of starting an operation of the monitoring target, a measurement step of measuring an internal state quantity in the operating state of the monitoring target and extracting a measured value, a prediction step of inputting into the simulation model same control input value used in the operating state of the monitoring target and calculating a predicted value of the internal state quantity of the monitoring target, a Mahalanobis distance calculation step of calculating a Mahalanobis distance from a difference between the measured value and the predicted value, and an abnormality diagnosis step of diagnosing whether the operating state of the monitoring target is abnormal based on the Mahalanobis distance.

An abnormality diagnosing method includes a model generation step of generating a simulation model of a monitoring target, an operation start step of starting an operation of the monitoring target, a measurement step of measuring an internal state quantity in the operating state of the monitoring target and extracting a measured value, a prediction step of inputting into the simulation model same control input value used in the operating state of the monitoring target and calculating a predicted value of the internal state quantity of the monitoring target, a Mahalanobis distance calculation step of calculating a Mahalanobis distance from a difference between the measured value and the predicted value, and an abnormality diagnosis step of diagnosing whether the operating state of the monitoring target is abnormal based on the Mahalanobis distance.

An engine piston is provided. A first sealing structure, including a first sealing rubber ring and a first annular groove, is provided at a head of the engine piston. The first sealing rubber ring has a U-shaped section with a reserved space at the top of the first sealing rubber ring, and a gap for circulating hydraulic oil is provided between a ring bank, above the first sealing rubber ring, of the engine piston and a simulated cylinder liner of a fatigue testing apparatus for an engine piston. In a case that the hydraulic oil is introduced into the fatigue testing apparatus for the engine piston to simulate pressure loading under a high-explosion pressure, when the hydraulic oil enters into the reserved space from the gap for circulating the hydraulic oil, an inner wall of the reserved space is squeezed and the first sealing rubber ring is deformed.

An engine piston is provided. A first sealing structure, including a first sealing rubber ring and a first annular groove, is provided at a head of the engine piston. The first sealing rubber ring has a U-shaped section with a reserved space at the top of the first sealing rubber ring, and a gap for circulating hydraulic oil is provided between a ring bank, above the first sealing rubber ring, of the engine piston and a simulated cylinder liner of a fatigue testing apparatus for an engine piston. In a case that the hydraulic oil is introduced into the fatigue testing apparatus for the engine piston to simulate pressure loading under a high-explosion pressure, when the hydraulic oil enters into the reserved space from the gap for circulating the hydraulic oil, an inner wall of the reserved space is squeezed and the first sealing rubber ring is deformed.

The present disclosure provides a vibration exciting system and an apparatus for testing an aero-engine rotor, relating to the field of aero-engines, to improve the universality of the vibration exciting system. The vibration exciting system comprises a mounting ring, fixing parts, holders, guide rails, and nozzle assemblies. The mounting ring is configured to be annular; one ends of the fixing parts are fixedly connected to the mounting ring; the holders are slidably mounted at the other ends of the fixing parts, the plurality of holders being arranged circumferentially of the mounting ring; each guide rail connects two adjacent holders, connection positions of the guide rail and the holders being adjustable; and the nozzle assemblies are mounted on the holders. The radius size of a spraying area enclosed by the nozzle assemblies is adjusted by adjusting the positions of the holders on the fixing parts.

The present disclosure provides a vibration exciting system and an apparatus for testing an aero-engine rotor, relating to the field of aero-engines, to improve the universality of the vibration exciting system. The vibration exciting system comprises a mounting ring, fixing parts, holders, guide rails, and nozzle assemblies. The mounting ring is configured to be annular; one ends of the fixing parts are fixedly connected to the mounting ring; the holders are slidably mounted at the other ends of the fixing parts, the plurality of holders being arranged circumferentially of the mounting ring; each guide rail connects two adjacent holders, connection positions of the guide rail and the holders being adjustable; and the nozzle assemblies are mounted on the holders. The radius size of a spraying area enclosed by the nozzle assemblies is adjusted by adjusting the positions of the holders on the fixing parts.

The present invention provides a testing device testing a multi-cylinder engine including a plurality of ports including an intake port and an exhaust port in a pseudo driving state. The device includes a plurality of pressure inspection units and at least one opening/closing mechanism. Each of the plurality of pressure inspection units includes a pipeline connected to one of the plurality of ports, a sensor for detecting a pressure in the pipeline and a valve for opening/closing the pipeline. The opening/closing mechanism includes one actuator and a transmission mechanism connected to the actuator and transmitting a driving force of the actuator to an operation unit of each of the plurality of valves to open and close the plurality of valves.

Disclosed are systems and methods for testing aircraft engine that are not currently associated with a functional aircraft or systems. For testing, systems on the engine being tested are connected with the reciprocating systems (e.g., engine electronic controls, main and motive fuel) on a fully functional aircraft using conduits that have been extended to lengths enabling the connection.

Disclosed are systems and methods for testing aircraft engine that are not currently associated with a functional aircraft or systems. For testing, systems on the engine being tested are connected with the reciprocating systems (e.g., engine electronic controls, main and motive fuel) on a fully functional aircraft using conduits that have been extended to lengths enabling the connection.

To improve diagnostic accuracy in diagnosing for abnormality of a machine, it is necessary to adjust a parameter regarding diagnosis such as the number of clusters. In such an adjustment operation, each time a diagnostic parameter is modified, a checking operation by an analysis operator is required to see whether a diagnosis result has been improved. The present invention assists in the checking operation to see whether diagnostic accuracy has been improved by comparing diagnosis results before and after parameter modification. If there are many items of sensor data for diagnosis, many items of abnormality degree data arise as analysis result. Many items of data pose a problem that comparing diagnosis results takes time. In the data display system, abnormality degree data that has changed largely before and after parameter modification is automatically found and displayed to the analysis operator. How much an abnormality degree has changed is determined as an abnormality degree change rate, i.e., a ratio between “abnormality degree difference due to change” and “modified parameter value difference”. Only abnormality degree data with a large change rate is displayed to the analysis operator. Additionally, a more suited parameter that was hidden, if found during a parameter modifying operation, is displayed and presented to the analysis operator.