2563results about "Jet-propulsion engine testing" patented technology

Systems and methods for performing module-based diagnostics are described. In an exemplary embodiment, sensor values from an actual engine plant are input to an engine component quality estimator which generates performance estimates of major rotating components. Estimated performance differences are generating by comparing the generated performance estimates to a nominal quality engine. The estimated performance differences, which are indicative of component quality, are continuously updated and input to a real-time model of the engine. The model receives operating conditional data and the quality estimates are used to adjust the nominal values in the model to more closely match the model values to the actual plant. Outputs from the engine model are virtual parameters, such as stall margins, specific fuel consumption, and fan / compressor / turbine efficiencies. The virtual parameters are combined with the sensor values from the actual engine plant in a fault detection and isolation classifier to identify abnormal conditions and / or specific fault classes, and output a diagnosis.

In an embodiment, a method includes performing a turbine combustor diagnostic routine including operating a first turbine combustor of a plurality of turbine combustors at a substantially steady state of combustion; adjusting an operational parameter of the first turbine combustor to cause a change in combustion products produced by the first turbine combustor; identifying a first sensor response of a first subset of a plurality of sensors disposed within or downstream from a turbine fluidly coupled to the turbine combustor, the first sensor response being indicative of the change in the combustion products, and wherein the first subset comprises one or more first sensors; correlating the first subset of sensors with the first turbine combustor; and diagnosing a condition of the first subset of the plurality of sensors, the first turbine combustor, or a combination thereof, based on the first sensor response.

A system and related methods for evaluating a component using a reference feature and a replicate of the reference feature. The component has an exterior surface with a reference feature thereon. The method includes determining an initial condition of the reference feature, subjecting the component to at least one duty cycle after determining the initial condition, determining a subsequent condition of the reference feature after the at least one duty cycle while the component is in a service position, and forming a replicate of the reference feature while the reference feature is in one of the initial condition or the subsequent condition. One of the initial condition or the subsequent condition may be determined based on the replicate of the reference feature.

Internal components of power generation machinery, such as gas and steam turbines are inspected with an optical camera inspection system that is capable of automatically positioning the camera field of view (FOV) to an area of interest within the machinery along a pre-designated navigation path and capturing images without human intervention. Automatic camera positioning and image capture can be initiated automatically or after receipt of operator permission. The pre-designated navigation path can be defined by operator manual positioning of an inspection scope within the power machine or a similar one of the same type and recording of positioning steps for future replication. The navigation path can also be defined by virtual simulation. The inspection system includes an articulated multi-axis inspection scope.

A test facility provides high temperature, high pressure and high mass flow fluid to a test object to form a relatively large thermal gradient on the object. Energy in the fluid is recuperated to drive system components, such as a heat exchanger and a turbocharger compressor. A test chamber housing the test object can be arranged to conform to a contour of the test object. A control system permits independent variation of pressure, temperature, cooling fluid and fluid velocity, as well as mechanical loading on the test object. Noncontact, optical inspection measurement techniques can be employed to measure test chamber and / or test object parameters. The test object can be configured to direct cooling airflow to permit various temperature or pressure gradients to be implemented. The test facility is relatively inexpensive to operate and provides a significant cost advantage over testing conducted in a full gas turbine engine.

A machine learning device which learns fault prediction of one of a main shaft of a machine tool and a motor driving the main shaft, including a state observation unit observing a state variable including at least one of data output from a motor controller controlling the motor, data output from a detector detecting a state of the motor, and data output from a measuring device measuring a state of the one of the main shaft and the motor; a determination data obtaining unit obtaining determination data upon determining one of whether a fault has occurred in the one of the main shaft and the motor and a degree of fault; and a learning unit learning the fault prediction of the one of the main shaft and the motor in accordance with a data set generated based on a combination of the state variable and the determination data.

A profile map of parameter values in a region is determined based on average values along linear paths through the region. In one example, a temperature map of a region of a gas turbine engine is created based on time-of-flight measurements from acoustic transceiver pairs arranged circumferentially around the region. A speed of sound for each transceiver pair is determined based on the time-of-flight measurements. An average temperature along each path is estimated from the time of flight, and the profile map is computed from the average temperatures. The profile map may be computed using a polynomial approximation technique, a grid optimization technique or a basis function technique.

These objects are achieved by a method of acoustically inspecting a one-piece bladed wheel in which the wheel is driven in rotation; each blade of the wheel is subjected to mechanical excitation; its acoustic response is picked up and a corresponding electrical signal is generated; its frequency response is determined by computing a FFT; the electrical signal and the associated frequency response are stored; the characteristic frequencies of each blade of the wheel are identified; and a wheel is rejected or accepted depending on whether or not the frequency distribution obtained in this way matches a predetermined set of forbidden frequency distributions. Advantageously, an additional step is provided in which the defects of a blade are determined by comparing its frequency response with predetermined frequency responses that are characteristic of various types of defect.

A tachometer for a downhole motor includes: a tubular housing having a coupling for connection to a housing of the motor; and a probe. The probe: has a coupling for connection to a rotor of the motor, is movable relative to the tachometer housing, and has at least a portion disposed in a bore of the tachometer housing. The tachometer further includes electronics disposed in the tachometer housing and including: a battery; one or more proximity sensors for tracking an orbit of the probe; and a programmable logic controller (PLC). The PLC is operable: to receive the tracked orbit, and at least one of: to determine an angular speed of the probe using the tracked orbit, and to forecast a remaining lifespan of the motor using the tracked orbit.

The present invention relates to a system for detecting aerodynamic instabilities in a jet turbine engine having a pressure transducer mounted in the engine. The pressure transducer, welded to a circuit in signal communication with a controller, is adapted to send measured pressure readings from air in a combustion chamber to the controller. The controller, located in spaced apart relation from the engine, is adapted by software to detect pressure patterns from the pressure signals generated by the transducer that are indicative of a stall or surge. A series of fuel and air valves located with compression and combustion chambers of the engine are in signal communication with the controller. The controller in response to detecting pressure signals indicating a stall or surge is operative to signals in the valves to change the air flow, air angle, fuel flow or speed to reduce the possibility of a stall or surge.