Aircraft engine control during icing of temperature probe
First Claim
1. A method for controlling an aircraft turbofan engine, the method performed by a data processor of a digital engine controller and comprising:
- receiving one or more signals representative of temperature from a heated temperature probe;
using the one or more signals representative of temperature received from the heated temperature probe to generate one or more control signals for use in controlling the engine;
using the one or more signals representative of temperature received from the heated temperature probe, determining that an icing condition associated with the probe exists based at least partly on a rise in temperature at the heated temperature probe;
using data representing one or more substitute signals in place of the one or more signals representative of temperature received from the heated temperature probe to generate the one or more control signals for use in controlling the engine; and
causing the deactivation of a heating element associated with the probe.
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Accused Products
Abstract
Methods for controlling an aircraft turbofan engine during icing of a temperature probe and devices for carrying out such methods are described. The methods may comprise: using one or more signals representative of temperature received from a heated temperature probe to generate one or more control signals for use in controlling the engine; determining that an icing condition associated with the probe exists; and using data representing one or more substitute signals in place of signals representative of temperature received from the heated temperature probe to generate the one or more control signals for use in controlling the engine.
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Citations
18 Claims
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1. A method for controlling an aircraft turbofan engine, the method performed by a data processor of a digital engine controller and comprising:
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receiving one or more signals representative of temperature from a heated temperature probe; using the one or more signals representative of temperature received from the heated temperature probe to generate one or more control signals for use in controlling the engine; using the one or more signals representative of temperature received from the heated temperature probe, determining that an icing condition associated with the probe exists based at least partly on a rise in temperature at the heated temperature probe; using data representing one or more substitute signals in place of the one or more signals representative of temperature received from the heated temperature probe to generate the one or more control signals for use in controlling the engine; and causing the deactivation of a heating element associated with the probe. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9)
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10. A method for generating a signal useful in controlling an aircraft engine having an engine controller, the method comprising:
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receiving a first signal representative of a total temperature of inlet air from a heated temperature probe; using the first signal as a control parameter for generating a second signal useful in controlling the engine; detecting, based on the first signal, a rise in temperature indicative of an icing condition of the probe; using a substitute signal instead of the first signal as the control parameter for generating the second signal useful in controlling the engine; deactivating a heating element associated with the probe; and resuming to using the first signal as the control parameter for generating the second signal useful in controlling the engine. - View Dependent Claims (11, 12, 13, 14)
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15. A device useful in controlling an aircraft turbine engine, the device comprising:
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at least one digital processor configured to receive a first signal representative of a total temperature of inlet air using a heated temperature probe and use the first signal as a control parameter to generate a second signal useful in controlling the engine; memory containing machine-readable instructions for execution by the at least one processor, the machine-readable instructions causing the at least one processor to; detect, based on the first signal, a rise in temperature indicative of an icing condition of the probe; use a substitute signal instead of the first signal as the control parameter for producing the second signal useful in controlling the engine; and cause deactivation of a heater associated with the probe. - View Dependent Claims (16, 17, 18)
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Specification