A method of detecting damage to a gas turbine engine, the method including observing a thermal response of the engine during a thermal transition occurring when the engine transitions between an elevated temperature and a lesser temperature; determining potential damage to the gas turbine engine based on the observed thermal response of the gas turbine engine; and generating an action in response to the determined potential damage to the gas turbine engine.

A redundant control system includes a plurality of channels each including a processing system configured to execute a control application for a controlled system. The redundant control system also includes a switchover artificial intelligence control operable to evaluate a state of the channels of the redundant control system, monitor a plurality of input/output data and communication data of the channels, and apply a fault model to determine one or more component faults and system faults of the channels based on the state, the input/output data, and the communication data. The switchover artificial intelligence control is further operable to command a switchover of a control function from one of the channels having a lower health status to one of the channels having a higher health status based on the component faults and system faults of the channels.

The present disclosure provides a method of multi-objective and multi-dimensional online joint monitoring for a nuclear turbine. The method includes: obtaining first temperature monitoring data of the nuclear turbine by performing online thermal monitoring on a rotor, a valve cage and a cylinder of the nuclear turbine under quick starting-up; obtaining second temperature monitoring data of tightness of a flange association plane of the cylinder of the nuclear turbine by performing online thermal monitoring on the tightness of the flange association plane; obtaining operation monitoring data of a shafting vibration of a rotor and bearing system of the nuclear turbine by performing online safety monitoring on the shafting vibration of the rotor and bearing system; and optimizing operation and maintenance control of the nuclear turbine according to at least one type of monitoring data among the first temperature monitoring data, the second temperature monitoring data and the operation monitoring data.

The present disclosure provides a method of multi-objective and multi-dimensional online joint monitoring for a nuclear turbine. The method includes: obtaining first temperature monitoring data of the nuclear turbine by performing online thermal monitoring on a rotor, a valve cage and a cylinder of the nuclear turbine under quick starting-up; obtaining second temperature monitoring data of tightness of a flange association plane of the cylinder of the nuclear turbine by performing online thermal monitoring on the tightness of the flange association plane; obtaining operation monitoring data of a shafting vibration of a rotor and bearing system of the nuclear turbine by performing online safety monitoring on the shafting vibration of the rotor and bearing system; and optimizing operation and maintenance control of the nuclear turbine according to at least one type of monitoring data among the first temperature monitoring data, the second temperature monitoring data and the operation monitoring data.

A steam turbine includes an outer casing (19) that is provided with a first steam outlet port (54), through which exhaust steam flowing through the entire length of a flow path (21) defined between an inner casing main body (45) and an outer casing main body (51) in a direction along an axis (O.sub.1) is discharged to the outside of the outer casing (19), and a second steam outlet port (55), which is provided in the outer casing main body (51) and through which the exhaust steam passing through a portion of the flow path (21) or the exhaust steam not passing through the flow path (21) is discharged to the outside of the outer casing (19); a first valve (28) that adjusts opening of the first steam outlet port (54); and a second valve (32) that adjusts opening of the second steam outlet port (55).

A steam turbine includes an outer casing (19) that is provided with a first steam outlet port (54), through which exhaust steam flowing through the entire length of a flow path (21) defined between an inner casing main body (45) and an outer casing main body (51) in a direction along an axis (O.sub.1) is discharged to the outside of the outer casing (19), and a second steam outlet port (55), which is provided in the outer casing main body (51) and through which the exhaust steam passing through a portion of the flow path (21) or the exhaust steam not passing through the flow path (21) is discharged to the outside of the outer casing (19); a first valve (28) that adjusts opening of the first steam outlet port (54); and a second valve (32) that adjusts opening of the second steam outlet port (55).

The present disclosure provides methods and systems for determining a synthesized engine parameter of a gas turbine engine. An initial model parameter is obtained from an onboard model associated with the gas turbine engine. A correction factor for the onboard model is determined by modifying a difference between the onboard model and an aero-thermal model of the gas turbine engine using first and second engine parameters and first and second operating conditions, wherein the first and second engine parameters are independent from one another over an operating envelope of the gas turbine engine. The initial model parameter is scaled by applying the correction factor thereto to obtain a corrected model parameter. The corrected model parameter is output as the synthesized engine parameter.

The present disclosure provides methods and systems for determining a synthesized engine parameter of a gas turbine engine. An initial model parameter is obtained from an onboard model associated with the gas turbine engine. A correction factor for the onboard model is determined by modifying a difference between the onboard model and an aero-thermal model of the gas turbine engine using first and second engine parameters and first and second operating conditions, wherein the first and second engine parameters are independent from one another over an operating envelope of the gas turbine engine. The initial model parameter is scaled by applying the correction factor thereto to obtain a corrected model parameter. The corrected model parameter is output as the synthesized engine parameter.

A bonding probe is used for bonding a cover sheet to a core to form or repair a dual wall structure. The bonding probe includes a body, an attachment end at a distal end of the body, a head at an opposite end of the body, a tip extending from the head, and a cooling passageway. The attachment end couples the body to a resistance welder. The tip extends to form a proximate end of the body. The tip includes a contacting area having a predetermined three dimensional contoured surface. The contacting area aligns with a predetermined area of a three dimensional outer surface of a cover sheet of a dual walled structure. The cooling passageway provides a passageway for a flow of cooling fluid. The cooling passageway extends through the head, and into the tip.

A minimum creep life location (MCLL) on a blade for a turbine blade design is received. A temperature at the MCLL on the blade is monitored. When the temperature at the MCLL exceeds a predetermined threshold, a cooling air supply is adjusted to lower the temperature below the threshold during engine operation.