[특허]Aircraft engine control during icing of temperature probe

Aircraft engine control during icing of temperature probe 원문보기

IPC분류정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	B64D-031/06 F01D-025/02 F02C-007/047 F02C-009/28 F02D-009/00 G07C-003/00 G01K-013/02
출원번호	US-0025995 (2013-09-13)
등록번호	US-9114885 (2015-08-25)
발명자 / 주소	Calandra, Salvatore Giroux, Frederic Iacobacci, Mark Chabot, Martin Hartropp, Simon Syed, Yusuf Chmiel, Dariusz Bajaj, Adrienne
출원인 / 주소	Pratt & Whitney Canada Corp.
대리인 / 주소	Norton Rose Fulbright Canada LLP
인용정보	피인용 횟수 : 0 인용 특허 : 32

초록 ▼

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.

대표청구항 ▼

1. A method for controlling an aircraft turbofan engine, the method performed by a data processor of a digital engine controller and comprising: receiving a signal representative of temperature received from a heated temperature probe and using the received signal to control the engine;based on the signal representative of temperature received from the heated temperature probe, determining that an icing condition associated with the probe exists;using data representing a substitute temperature instead of the signal representative of temperature received from the heated temperature probe to control the engine;deactivating a heating element associated with the probe following the determination of the icing condition; andwith the heating element deactivated, resuming to use the signal representative of temperature received from the temperature probe to control the engine instead of the data representing the substitute temperature. 2. The method as defined in claim 1, wherein the determining that the icing condition exists is based at least partly on a rise in temperature at the heated temperature probe. 3. The method as defined in claim 2, wherein the rise in temperature includes the temperature rising at or exceeding a threshold rate. 4. The method as defined in claim 2, wherein the rise in temperature includes the temperature increasing by a threshold amount at or exceeding a threshold rate. 5. The method as defined in claim 1, wherein the substitute temperature comprises a temperature at or prior to the determination of the icing condition. 6. The method as defined in claim 1, wherein the deactivating of the heating element occurs after a confirmation process in which the temperature associated with the heated temperature probe is determined to have stabilized at a temperature higher than an actual temperature. 7. The method as defined in claim 1, wherein resuming to use the signal representative of temperature received from the temperature probe to control the engine with the heating element deactivated follows a determination that the temperature of the temperature probe has reached at a temperature approximating an actual temperature. 8. The method as defined in claim 7, comprising transitioning a magnitude of the substitute temperature towards a magnitude of the temperature received from the temperature probe. 9. A device useful in controlling an aircraft turbine engine, the device comprising: 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, an icing condition of the probe;use a substitute signal representing a substitute temperature as the control parameter instead of the first signal for producing the second signal useful in controlling the engine;cause deactivation of a heating element associated with the probe following the detection of the icing condition; andcause the at least one digital processor to resume the use of the first signal as the control parameter for producing the second signal useful in controlling the engine after the deactivation of the heating element. 10. The device as defined in claim 9, wherein the substitute signal is representative of the temperature from the first signal at or prior to a rise in temperature indicative of the icing condition. 11. The device as defined in claim 9, wherein the determining of the icing condition is based on a rise in temperature at the probe. 12. The device as defined in claim 11, wherein the rise in temperature includes the temperature rising at or exceeding a threshold rate. 13. The device as defined in claim 11, wherein the rise in temperature includes the temperature increasing by a threshold amount at or exceeding a threshold rate. 14. The device as defined in claim 9, wherein causing to deactivate the heating element occurs after a confirmation process in which the temperature associated with the probe is determined to have stabilized at a temperature higher than an actual temperature. 15. The device as defined in claim 9, wherein causing to resume the use of the first signal as the control parameter for producing the second signal useful in controlling the engine after the deactivation of the heating element follows a determination that the temperature of the probe has reached a temperature approximating an actual temperature. 16. The device as defined in claim 9, wherein the machine-readable instructions are configured to cause the at least one processor to transition a magnitude of the substitute signal towards a magnitude of the first signal before resuming the use of the first signal as the control parameter.

이 특허에 인용된 특허 (32)

Layland, Michael John; Brown, Keith Towers; Hubert, Claude Marc; Christy, Daniel P., Acoustic nacelle inlet lip having composite construction and an integral electric ice protection heater disposed therein.
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Paul A. Ice ; Charles R. Willcox, Active heater control circuit and method used for aerospace probes.
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Calandra, Salvatore; Giroux, Frederic; Iacobacci, Mark; Chabot, Martin; Hartropp, Simon; Syed, Yusuf; Chmiel, Dariusz; Bajaj, Adrienne, Aircraft engine control during icing of temperature probe.
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Itoh Takane (Yokohama JA), Control circuit for gas turbine engine.
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Kerr Walter B. (West Palm Beach FL), Control for gas turbine engine.
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Euvino, Jr., Frank J.; Vinciquerra, Anthony J., Electrothermal inlet ice protection system.
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Lockwood, Clive, Engine arrangement.
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Shah,Anil D.; Gupta,Alankar, Method and apparatus for detecting conditions conducive to ice formation.
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IPC	Description
A	생활필수품
A62	인명구조; 소방(사다리 E06C)
A62B	인명구조용의 기구, 장치 또는 방법(특히 의료용에 사용되는 밸브 A61M 39/00; 특히 물에서 쓰이는 인명구조 장치 또는 방법 B63C 9/00; 잠수장비 B63C 11/00; 특히 항공기에 쓰는 것, 예. 낙하산, 투출좌석 B64D; 특히 광산에서 쓰이는 구조장치 E21F 11/00)
A62B-1/08	.. 윈치 또는 풀리에 제동기구가 있는 것

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Aircraft engine control during icing of temperature probe 원문보기

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Aircraft engine control during icing of temperature probe 원문보기

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