Honeywell International Inc.

Yufei Xiong

Scot Coffey

Dave Faymon

John Rushinsky

Dave Looper

Gregory J Chapman

Craig E Thompson

Ronnie Haugland

David K Faymon

Ernest Kurschat

Ron Haugland

Darrell C Mays

Scot Coffee

A system and method for detecting a shaft break in a turbofan gas turbine engine includes sensing fan rotational speed and sensing turbine engine rotational speed. A rate of change of rotational speed difference between the sensed fan rotational speed and the sensed turbine engine rotational speed is determined in a processor, and a determination that a shaft break has occurred is made in the processor based at least in part on the rate of change of the rotational speed difference.

Turbofan gas turbine engine shaft break detection system and method

Embodiments of a single lever turboprop control method and system are provided, which utilize torque-based and/or power-based scheduling to achieve a desired (e.g., substantially proportional) relationship between control lever position and the power output of a turboprop engine. In one embodiment, the method includes the step or process of monitoring, at an Engine Control Unit (ECU), for receipt of a Power Lever Angle (PLA) signal from a single lever control device. When a PLA control signal received at the ECU, a target torque or power output is established as a function of at least the PLA control signal. A first engine setpoint, such as a blade angle setpoint or an engine rotational speed setpoint, is determined utilizing the target torque output. An operational parameter of the turboprop engine is then adjusted in accordance with the first engine setpoint.

Single lever turboprop control systems and methods utilizing torque-based and power-based scheduling

A system and method of accommodating an uncontrolled high thrust condition in a turbofan gas turbine engine includes processing engine data from the turbofan gas turbine engine to determine when a potential for an uncontrolled high thrust condition exists. When the potential for an uncontrolled high thrust condition exists, the engine data are processed to determine whether corrective action for the uncontrolled high thrust condition should be implemented by varying turbofan gas turbine engine effective geometry to (i) increase turbofan gas turbine engine rotational speed or (ii) decrease turbofan gas turbine engine rotational speed. The determined corrective action is automatically implemented.

Gas turbine engine uncontrolled high thrust accommodation system and method

Single lever turboprop control systems and methods utilizing torque-based and power based scheduling

A system and method of detecting an uncontrolled high thrust (UHT) condition in a turbofan gas turbine engine includes processing data to determine when a current commanded fan speed value is greater than a predetermined speed value. A current UHT commanded fan speed value is processed to determine if it will cause a target fan speed value to increase, remain steady, or decrease. The target fan speed value is set equal to the current UHT commanded fan speed value when the current UHT commanded fan speed value will cause the target fan speed value to increase or remain steady, and to a deceleration threshold value when the current UHT commanded fan speed value will cause the target fan speed value to decrease. An uncontrolled high thrust alert signal is generated when actual engine fan speed exceeds the target fan speed value by a predetermined amount for a preset time period.

Gas turbine engine uncontrolled high thrust detection system and method

A control system for an aircraft gas turbine propulsion engine includes an engine control that is adapted to receive at least engine inlet temperature data and aircraft altitude data. The engine control is configured to determine the availability of the engine inlet temperature data and implements a measured temperature engine thrust setting schedule when the engine inlet temperature data is available, and a default temperature engine thrust setting schedule when the engine inlet temperature data is unavailable. The default temperature engine thrust setting schedule ensures that the gas turbine propulsion engine will generate at least 90% of rated engine thrust at all actual engine inlet temperatures at the sensed aircraft altitude.

Aircraft gas turbine propulsion engine control without aircraft total air temperature sensors

An engine system for starting a gas turbine engine includes a starter coupled to the gas turbine engine and configured to provide torque to the gas turbine engine; and a controller coupled to the starter and configured to evaluate an engine system parameter and to select from a plurality of start modes for starting the gas turbine engine based on the engine system parameter.

Engine systems with enhanced start control schedules

A method and a system is provided, useable in electrical control sensors for shaft speed signal frequency change rate tests, detecting intermittent or 'in-range'failures. The method estimates a short-term variance of the measured signal or signal rate of change, using the equation: Var[x]=E[x]&#x2212;E[x], where E[x] is an estimated average of the squared measured signal or rate of change over the short term, and E[x] is a squared estimated average of the measured signal or rate of change over the short term. The estimated variance is compared with a predefined variance limit for a predefined amount of time, and if the estimated variance exceeds the predefined variance limit for the predefined amount of time, the measured signal is deemed invalid. A latching counter is used for timing, and its time out rate is preferably proportional to the time period the measured input is true. The step for estimating a short-term variance of the measured signal uses several filters performing averaging function.

Speed signal variance detection fault system and method

A method and system for surge detection within a gas turbine engine, comprises: measuring the compressor discharge pressure (CDP) of the gas turbine over a period of time; determining a time derivative (CDP ) of the measured (CDP) correcting the CDP for altitude, (CDP ); estimating a short-term average of CDP ; estimating a short-term average of CDP ; and determining a short-term variance of corrected CDP rate of change (CDP ) based upon the short-term average of CDP and the short-term average of CDP . The method and system then compares the short-term variance of corrected CDP rate of change with a pre-determined threshold (CDP ) and signals an output when CDP >CDP . The method and system provides a signal of a surge within the gas turbine engine when CDP remains>CDP for pre-determined period of time.

Method and system for turbomachinery surge detection

A method and a system is provided, useable in electrical control sensors for shaft speed signal frequency change rate tests, detecting intermittent or &ldquo;in-range&rdquo; failures. The method estimates a short-term variance (standard deviation) of the measured signal or signal rate of change, using the equation: Var&lsqb;x&rsqb;&equals;E&lsqb;x &rsqb;&minus;E &lsqb;x&rsqb;, where E&lsqb;x &rsqb; is an estimated average of the squared measured signal or rate of change over the short term, and E &lsqb;x&rsqb; is a squared estimated average of the measured signal or rate of change over the short term. The estimated variance is compared with a predefined variance limit for a predefined amount of time, and if the estimated variance exceeds the predefined variance limit for the predefined amount of time, the measured signal is deemed invalid. A latching counter is used for timing, and its time out rate is preferably proportional to the time period the measured input is true. The step for estimating a short-term variance of the measured signal uses several filters performing averaging function.

Improved methods and systems are provided for detecting surge bleed valve faults and analyzing the performance of surge bleed valves in gas turbines. The method includes monitoring the rates of rotation of an engine fan and an engine gas generator in a gas turbine engine. While so doing, a valve status change signal is transmitted to a surge bleed valve in the gas turbine engine. The difference between the two monitored rates of rotation is determined. A surge bleed valve fault signal is generated if the difference between the two monitored rates of rotation does not change by at least a predetermined amount immediately following transmission of the valve status change signal to the surge bleed valve.

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Phoenix, AZ, United States of America

Yufei Xiong