Abstract: A method and systems for engine control of a vehicle propulsion system are provided. The system includes a plurality of engine model modules executing independently and programmed to receive engine operating condition values from a plurality of sensors positioned on an engine wherein each of the plurality of engine model modules is programmed to determine an estimate of a process parameter of a location in the engine where a sensor is not available, not present at the location, has failed, or is determined to be inaccurate. The system also includes an estimate source selector configured to determine model blending factors and a model blending module configured to determine an estimated virtual sensor value using the determined estimates from at least two of the plurality of engine model modules and the model blending factors.

Abstract: A method for estimating an operating parameter of a turbine engine is provided. The method includes receiving at least one sensor input, calculating the operating parameter using at least the one sensor input, and determining whether an anomaly is present in the calculated operating parameter using a redundancy system. An estimated operating parameter is output.

Abstract: A method and systems for engine control of a vehicle propulsion system are provided. The system includes a plurality of engine model modules executing independently and programmed to receive engine operating condition values from a plurality of sensors positioned on an engine wherein each of the plurality of engine model modules is programmed to determine an estimate of a process parameter of a location in the engine where a sensor is not available, not present at the location, has failed, or is determined to be inaccurate. The system also includes an estimate source selector configured to determine model blending factors and a model blending module configured to determine an estimated virtual sensor value using the determined estimates from at least two of the plurality of engine model modules and the model blending factors.

Abstract: A method for estimating an operating parameter of a turbine engine is provided. The method includes receiving at least one sensor input, calculating the operating parameter using at least the one sensor input, and determining whether an anomaly is present in the calculated operating parameter using a redundancy system. An estimated operating parameter is output.

Abstract: A method and systems for controlling an engine are provided. The system includes an engine model programmed to receive engine operating condition values from a plurality of sensors on an engine. The engine model is programmed to determine a plurality of engine operating parameter values. The system also includes a processor configured to compare the operating parameter values to a predetermined allowable range for the operating parameter and control the operation of the engine to facilitate returning the determined operating parameter to the allowable range or maintaining the determined operating parameter within the allowable range, output the determined operating parameter values to a user, and/or generate maintenance requests based on the comparison.

Abstract: A method for planning repair of an engine is provided. The method comprises monitoring an engine having a plurality of engine modules and determining one or more module-specific health estimates for one or more of the engine modules, based on a plurality of engine parameters. The method further comprises planning repair of the engine based on one or more of the module-specific health estimates determined for one or more of the engine modules.

Abstract: A method of measuring a gas turbine engine operating parameter is provided. The method includes providing at least one engine component and a plurality of sensors, positioning each of the plurality of sensors relative to an index location, defining a periodic gas flow operating parameter distribution profile to extend across an engine component or between engine components, obtaining a gas flow operating parameter reading from each of the plurality of sensors, and determining at least one operating parameter for defining a periodic gas flow operating parameter distribution.

Abstract: A method of measuring a gas turbine engine operating parameter is provided. The method includes providing at least one engine component and a plurality of sensors, positioning each of the plurality of sensors relative to an index location, defining a periodic gas flow operating parameter distribution profile to extend across an engine component or between engine components, obtaining a gas flow operating parameter reading from each of the plurality of sensors, and determining at least one operating parameter for defining a periodic gas flow operating parameter distribution.

Abstract: Methods of increasing lifetimes of components in a gas turbine engine. Ordinarily, components are replaced after they experience a certain number of thermal cycles, or a certain operating temperature limit is exceeded. Under one form of the invention, the components are not replaced at that time, but are subjected to increased cooling, which decreases the highest temperature reached in subsequent thermal cycles. Also, many components are replaced when acceleration of an engine falls below a target. In one form of the invention, the components are not replaced, but (1) scheduled fuel flow is increased and (2) compressor stall margin also increased, in order to attain the target acceleration.

Abstract: Apparatus and methods are disclosed for increasing lifetimes of components in a gas turbine engine. Ordinarily, components are replaced after they experience a certain number of thermal cycles, or a certain operating temperature limit is exceeded. Under one form of the invention, the components are not replaced at that time, but are subjected to increased cooling, which decreases the highest temperature reached in subsequent thermal cycles. Also, many components are replaced when acceleration of an engine falls below a target. In one form of the invention, the components are not replaced, but (1) fuel schedule is increased and (2) compressor stall margin also increased, in order to attain the target acceleration.

Abstract: Apparatus and methods are disclosed for increasing lifetimes of components in a gas turbine engine. Ordinarily, components are replaced after they experience a certain number of thermal cycles, or a certain operating temperature limit is exceeded. Under one form of the invention, the components are not replaced at that time, but are subjected to increased cooling, which decreases the highest temperature reached in subsequent thermal cycles. Also, many components are replaced when acceleration of an engine falls below a target. In one form of the invention, the components are not replaced, but (1) fuel schedule is increased and (2) compressor stall margin also increased, in order to attain the target acceleration.

Abstract: Methods of increasing lifetimes of components in a gas turbine engine. Ordinarily, components are replaced after they experience a certain number of thermal cycles, or a certain operating temperature limit is exceeded. Under one form of the invention, the components are not replaced at that time, but are subjected to increased cooling, which decreases the highest temperature reached in subsequent thermal cycles. Also, many components are replaced when acceleration of an engine falls below a target. In one form of the invention, the components are not replaced, but (1) scheduled fuel flow is increased and (2) compressor stall margin also increased, in order to attain the target acceleration.

Abstract: 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.

Abstract: Methods of increasing lifetimes of components in a gas turbine engine. Ordinarily, components are replaced after they experience a certain number of thermal cycles, or a certain operating temperature limit is exceeded. Under one form of the invention, the components are not replaced at that time, but are subjected to increased cooling, which decreases the highest temperature reached in subsequent thermal cycles. Also, many components are replaced when acceleration of an engine falls below a target. In one form of the invention, the components are not replaced, but (1) scheduled fuel flow is increased and (2) compressor stall margin also increased, in order to attain the target acceleration.

Abstract: Methods of increasing lifetimes of components in a gas turbine engine. Ordinarily, components are replaced after they experience a certain number of thermal cycles, or a certain operating temperature limit is exceeded. Under one form of the invention, the components are not replaced at that time, but are subjected to increased cooling, which decreases the highest temperature reached in subsequent thermal cycles. Also, many components are replaced when acceleration of an engine falls below a target. In one form of the invention, the components are not replaced, but (1) scheduled fuel flow is increased and (2) compressor stall margin also increased, in order to attain the target acceleration.

Abstract: Methods of increasing lifetimes of components in a gas turbine engine. Ordinarily, components are replaced after they experience a certain number of thermal cycles, or a certain operating temperature limit is exceeded. Under one form of the invention, the components are not replaced at that time, but are subjected to increased cooling, which decreases the highest temperature reached in subsequent thermal cycles. Also, many components are replaced when acceleration of an engine falls below a target. In one form of the invention, the components are not replaced, but (1) scheduled fuel flow is increased and (2) compressor stall margin also increased, in order to attain the target acceleration.

Abstract: Methods of increasing lifetimes of components in a gas turbine engine. Ordinarily, components are replaced after they experience a certain number of thermal cycles, or a certain operating temperature limit is exceeded. Under one form of the invention, the components are not replaced at that time, but are subjected to increased cooling, which decreases the highest temperature reached in subsequent thermal cycles. Also, many components are replaced when acceleration of an engine falls below a target. In one form of the invention, the components are not replaced, but (1) scheduled fuel flow is increased and (2) compressor stall margin also increased, in order to attain the target acceleration.

Abstract: A sensor in an engineering system can be tested to detect, isolate and accommodate faults. Initially, a modeled sensor value of each actual sensor value is generated as a function of a plurality of other sensors. An absolute value of a difference between the actual sensor value and the modeled sensor value is then computed and compared to a predetermined threshold. A sensor fault is detected if the difference is greater than the predetermined threshold. Once a sensor fault is detected, it is isolated using hypothesis testing and maximum wins strategies. After the fault is isolated, the fault is accommodated by substituting the modeled sensor value for the actual sensor value.

Abstract: Methods and systems for reducing or removing the effect of measurement error so that an actual engine operates closer to optimum are described. In an exemplary embodiment, the method includes the steps of identifying an engine operation (e.g., acceleration) that is less than optimal, estimating the measurement error associated with the less than optimal operation, adjusting the engine control logic based on the measurement error estimate, and reassessing the engine operation. The method is implemented, in one form, in an engine controller by programming a control processor to execute the above described method.

Abstract: An engine tracking filter system that obtains information from two or more operating conditions to estimate health parameters P, performance parameters Yp, and sensor estimates Ys, is described. Such multipoint estimation of engine health enables estimation of all engine health parameters rather than only a few engine health parameters for use in engine component diagnostics, trending, and fault detection and isolation. In addition, such estimation is believed to provide improved estimates of sensed parameters for use in sensor redundancy management and sensor elimination, and also is believed to provide improved estimates of performance parameters for use in model based control to reduce required temperature, stall, and other margins.