Honeywell International Inc.

Kevin Moeckly

Richard Ling

Jan Goericke

Andy Stramiello

Grant A Gordon

Christopher Gill

Michael David James

Dale Mukavetz

Robert Sandoval

Chuck Royalty

John K Harvell

Alfred E Carstens

Larry McLeister

Larry Yee

Ammon Hancock

Curtis Vedder

Larry Lee

David Morris

A method for self-generating an engine-specific model in an engine health monitoring system is provided. The method comprises generating a generic engine model including a generic physics-based model for each of a plurality of engine components in the specific engine; capturing a plurality of observed engine component parameters for each of the plurality of engine components and a plurality of observed environmental parameters during one or more pre-planned training missions; and training an engine-specific model using the plurality of observed engine component parameters and the plurality of environmental parameters captured during the one or more pre-planned training missions, wherein the engine-specific model includes an engine-specific physics-based model for each of the plurality of engine components in the specific engine. Each engine-specific physics-based model for an engine component is configured for use in predicting one or more engine component parameters using a second plurality of observed environmental parameters captured during an operational mission.

Self-generating engine-specific health monitoring model from generic model base

A system and method for providing bleed air compensation for a continuous power assurance analysis of a gas turbine engine includes estimating bleed air flow rate from the gas turbine engine, estimating a shift in power turbine inlet temperature based on the estimated bleed air flow rate, and applying the estimated shift in power turbine inlet temperature to the continuous power assurance analysis of the gas turbine engine.

Bleed air compensated continuous power assurance analysis system and method

A system and method for translating performance characteristics of a system from one system condition to another system condition includes sensing, at a current system condition, a first system performance parameter and a second system performance parameter. The first and second system performance parameters correspond to a measured performance characteristic value of the system. A first reference performance datum associated with the first and second system performance parameters at the current system condition, and a second reference performance datum associated with the first and second system performance parameters at a selected reference system condition are both retrieved from a memory. A difference between the first and second reference performance data is calculated to generate a translation value. The measured performance characteristic value of the system is then translated an amount equal to the data translation value, whereby a corrected performance characteristic value at the selected reference system condition is generated.

System and method for continuous performance analysis of systems that exhibit variable performance characteristics at different operating conditions

A real-time diagnostic and fault detection system and method for a gas turbine engine under test in a test cell is disclosed. Sensor data from instrumentation coupled to the gas turbine engine are processed, using a physics-based component level aero-thermal model, to calculate a plurality of engine parameters at a plurality of non-instrumented locations within the gas turbine engine. The plurality of engine parameters are processed to detect when a fault exists and, when a fault does exist, an image is rendered that indicates at least a mostly likely cause for the fault and one or more corrective actions that can be taken to correct the fault. The model is also used to generate projections of engine performance at one or more selected test conditions, and to prognosticate, based on the projections, as to whether the gas turbine engine will actually pass at the one or more selected test conditions.

Gas turbine engine and test cell real-time diagnostic fault detection and corrective action system and method

A system method for predicting vehicle mission capability for a vehicle that is propelled by an engine includes collecting engine degradation data for the engine. Location independent engine degradation data are generated from the collected engine degradation data. The location independent engine degradation data are representative of engine degradation that is independent of locations associated with the mission. Predictions of location dependent engine degradation are calculated from the collected engine degradation data and the location independent engine degradation data. The location dependent engine degradation is representative of engine degradation due to movement through locations associated with the mission.

Vehicle mission capability prediction system and method

An emergency landing control system for an aircraft includes a landing site data source, a performance margin data source, an engine health data source, an aircraft health data source, and a processor. The landing site data source determines, continuously and in real-time, available landing sites. The performance margin data source conducts, continuously and in real-time, continuous performance analysis of an engine. The engine health data source determines, continuously and in real-time, available engine power as a function of time. The aircraft health data source determines, continuously and in real-time, available aircraft life as a function of time. The processor receives data from these data sources and, based on these data, continuously generates landing paths to one or more of the available landing sites, and selectively and continuously adjusts maximum available engine power up to emergency power limits, as needed, during execution of a landing maneuver to a landing site.

Rotary-wing aircraft emergency landing control

A system and method of adaptively synchronizing the performance margin of a multi-engine system includes continuously, and in real-time, determining the performance margin of a first engine and the performance margin of the second engine. A difference between the performance margins of the first and second engines is calculated, and the first and second engines are controlled to attain a predetermined difference between the performance margins of the first and second engines.

Multi-engine performance margin synchronization adaptive control system and method

An operations support system is provided for an engine. The system includes a diagnostics module configured to receive engine data from the engine and to generate diagnostics data based on the engine data using a thermodynamic model, the thermodynamic model being based on component maps associated with the engine; an acoustics module coupled to the diagnostics module and comprising an acoustics calculation unit, the acoustics calculation unit configured to receive the diagnostics data and to determine an acoustics level for the engine based on the diagnostics data; and a graphical user interface coupled to the acoustics module and configured to display the acoustics level.

Operations support systems and methods with acoustics evaluation and control

An operations support system is provided for an engine with a turbine having a turbine inlet. The system includes a diagnostic engine model unit configured to receive engine data from the engine and to generate diagnostics data based on the engine data, the diagnostics data including scalars. The system further includes an engine-specific model unit coupled to the diagnostic engine model unit and configured to receive the scalars from the diagnostic engine model unit and configured to generate turbine inlet temperature information for the engine using a thermodynamic model. The thermodynamic model is based on component maps associated with the engine. The system further includes a storage unit coupled to the engine-specific model unit and configured to store the turbine inlet temperature information.

Operations support systems and methods for calculating and evaluating turbine temperatures and health

In accordance with an exemplary embodiment, an operations support system for an engine is provided. A diagnostics unit is configured to receive engine data from the engine and to generate condition indicators based on the engine data using a thermodynamic model, the thermodynamic model being based on component maps associated with the engine. An emissions calculation unit is coupled to the diagnostic unit and configured to calculate emissions information for the engine based on the condition indicators. A graphical user interface is coupled to the emissions calculation unit and configured to display the emissions information.

Operations support systems and methods for calculating and evaluating engine emissions

An operations support system is provided for an engine receiving fuel. The system includes a diagnostic engine model unit configured to receive engine data from the engine and to generate diagnostics data based on the engine data, the diagnostics data including scalars. The system further includes an engine-specific model unit coupled to the diagnostic engine model unit and configured to receive the scalars and the engine data. The engine-specific model unit includes a fuel flow calculation module configured to determine a current fuel flow for the engine and a set point module configured to generate set point information for the engine using a thermodynamic model that reduces the current fuel flow to the engine, the thermodynamic model being based on component maps associated with the engine. The system further includes a data storage unit coupled to the engine-specific model unit and configured to store the set point information.

Engine operations support systems and methods for reducing fuel flow

Methods and apparatus are provided for selectively controlling the rotational speed of a gas turbine engine that drives a load compressor having movable inlet guide vanes and that is coupled to receive fuel at a fuel flow rate up to a maximum fuel flow rate. The rotational speed of the gas turbine engine, and the fuel flow rate to the gas turbine engine, are both sensed. If the sensed rotational speed of the gas turbine engine is less than a predetermined value and the sensed fuel flow rate to the gas turbine engine equals or exceeds the maximum fuel flow rate, the position of the inlet guide vanes is controlled to reduce load compressor mechanical load on the gas turbine engine.

Gas turbine engine speed control system and method during maximum fuel flow

A power management system includes a data fusion unit configured to receive first health indicators from an engine diagnostics module and second health indicators from a power assurance module. The data fusion unit is configured to data fuse the first and second health indicators. A power assessment and decision support unit is coupled to the data fusion unit and configured to generate power available based on the fused first and second health indicators. A system diagnostic reasoner unit is coupled to the data fusion unit, and configured to provide a system level fault diagnosis based on the fused first and second health indicators. A graphical user interface is coupled to the power assessment and decision support unit and the system diagnostic reasoned unit. The graphical user interface is configured to display the system level fault diagnosis and the power available.

Operations support systems and methods with power management

An operations support system for an engine includes an engine prediction unit configured to receive an engine rating condition and scalars associated with the engine, and to generate condition indicators based on the engine rating condition and the scalars; and a power assurance algorithm unit coupled to the engine prediction unit and configured to generate health indicators based on the condition indicators. The health indicators include a power assurance number.

Operations support systems and methods with power assurance

A system and method of conducting a continuous performance analysis for a system includes collecting transient performance data for a first parameter of the system and a second parameter of the system. Transfer functions are applied to the transient performance data for at least one of the first and second parameters to thereby generate phase compensated performance data representative of a steady state relationship between the first and second parameter. For each phase compensated performance datum, an estimate of the first parameter is calculated at a predetermined value of the second parameter using the phase compensated performance datum and a previously stored performance characteristic curve representative of the steady state relationship between the first and second parameters in a deterioration model extrapolation method. A very efficient binning method is used for storing phase compensated performance data and converting them into steady state performance characteristic curves of any non-linear shape.

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Chandler, AZ, United States of America

Kevin Moeckly