Method of informing pilot of aircraft of spark detected in gas turbine engine
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F02P-017/00
G01R-031/00
출원번호
US-0775864
(2004-02-10)
등록번호
US-7375531
(2008-05-20)
발명자
/ 주소
Ponziani,Robert Louis
Earwood,Roy Dale
출원인 / 주소
General Electric Company
대리인 / 주소
Andes,William Scott
인용정보
피인용 횟수 :
8인용 특허 :
12
초록▼
A system for detecting spark in an igniter for a gas turbine engine. An igniter generates a plasma, or spark, somewhat similar to an automotive spark plug. In the invention, an inductive pick-up is positioned adjacent the igniter, to detect current pulses in the igniter, to thereby infer the presenc
A system for detecting spark in an igniter for a gas turbine engine. An igniter generates a plasma, or spark, somewhat similar to an automotive spark plug. In the invention, an inductive pick-up is positioned adjacent the igniter, to detect current pulses in the igniter, to thereby infer the presence of spark. A detection system detects the spark, and informs the pilot of the aircraft of the detected spark. Thus, if the pilot encounters a problem in starting the engine, the pilot can rapidly determine whether the igniter is involved in the problem.
대표청구항▼
The invention claimed is: 1. In an aircraft powered by a gas turbine engine containing an igniter which is fed by a power cable which is surrounded by a conductive shield connected to a system ground, a method comprising: a) detecting current pulses in the shield; and b) in response to detected cur
The invention claimed is: 1. In an aircraft powered by a gas turbine engine containing an igniter which is fed by a power cable which is surrounded by a conductive shield connected to a system ground, a method comprising: a) detecting current pulses in the shield; and b) in response to detected current pulses, issuing to a pilot station in the aircraft a signal indicating presence of spark in the igniter. 2. Method according to claim 1, further including a conductive shielding surrounding the igniter and the conductive shielding including the shield surrounding the power cable, the method further comprising: a) maintaining a coil outside the shielding; and b) the detecting current pulses includes detecting induced current in the coil. 3. Method according to claim 2, wherein no components involved in detecting the current pulses penetrate the conductive shielding. 4. Method according to claim 2, wherein the current pulses have a duration D and a frequency F, and wherein detecting the current pulses comprises: i) maintaining a series RLC circuit, comprising inductor L, resistor R, and capacitor C, wherein A) the inductor L comprises the coil, and B) the RLC circuit amplifies signals induced by the pulses. 5. Method according to claim 2, wherein (1) the current pulses generate voltage pulses in the coil, (2) the coil has an inductance L, and (3) detecting the current pulses comprises: i) connecting the coil to a circuit containing a resistance R and a capacitance C; and ii) using a value of capacitance C which causes amplification of the voltage pulses. 6. Method according to claim 5, wherein the amplification of the voltage pulses causes a voltage signal to appear across the capacitance C which is greater than voltage appearing across the coil in the absence of the circuit. 7. In an aircraft powered by a gas turbine engine containing an igniter which is fed by a power cable which is surrounded by a conductive shield connected to a system ground, a apparatus comprising: a) a detector for detecting current pulses in the shield; and b) an annunciator for issuing a signal indicating presence of spark in the igniter to a pilot station in the aircraft. 8. Apparatus according to claim 7, wherein the signal is issued based on the current pulses. 9. In an aircraft powered by a gas turbine engine containing an igniter which is fed by a power cable, the igniter and power cable being surrounded by conductive shielding, apparatus comprising: a) a coil outside the shielding; b) a detector for detecting current pulses in the coil; and c) an annunciator for issuing a signal indicating presence of spark in the igniter to a pilot station in the aircraft, in response to the detected current pulses. 10. Apparatus according to claim 9, wherein no components involved in detecting the current pulses penetrates the conductive shielding. 11. Apparatus according to claim 9, wherein the current pulses have a duration D and a frequency F, and further comprising: i) a series RLC circuit, comprising inductor L, resistor R, and capacitor C, wherein A) the inductor L comprises the coil, and B) the RLC circuit is resonant at a steady-state sinusoidal frequency F(res), wherein F(res) lies within the range (0.8) (1/D) to (1.2) (1/D). 12. Apparatus according to claim 9, wherein (1) the current pulses generate voltage pulses in the coil, (2) the coil has an inductance L, and further comprising: i) a connection between the coil and a circuit containing a resistance R and a capacitance C, wherein the value of capacitance C which causes amplification of the voltage pulses. 13. Apparatus according to claim 12, wherein the amplification of the voltage pulses causes a voltage signal to appear across the capacitance C which is greater than voltage appearing across the coil in the absence of the circuit. 14. A method of operating a gas turbine engine which powers an aircraft, comprising: a) maintaining an igniter which is i) surrounded by a housing, and ii) fed by a power cable which is surrounded by a conductive shield which is connected to the housing; and b) detecting current in the shield, housing, power cable, or a combination thereof, but without electrically contacting the power cable, and, in response to detected current, actuating an annunciator at a pilot station in the aircraft, informing the pilot of the detected spark. 15. Method according to claim 14, wherein the process of detecting current comprises: c) maintaining a coil adjacent the shield; d) inducing currents in the coil by currents in the shield; e) detecting induced currents in the coil; and f) issuing the signal in response to detection of the induced current.
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이 특허에 인용된 특허 (12)
McQueeney, Kenneth A.; Bryant, Robert R., Coil on plug inductive sampling method.
Burke, Daniel S.; Stewart, Jeffrey Taylor; Causey, Jim; Hackenberg, Michael; Harrar, Bruce, Igniter event conductor for conducting igniter events from a combustion chamber to a sensor.
Brunschwig, Anya R.; Nordmark, Amy R.; Donovan, Bryan P.; Ruestow, Andrew D.; Kacprzynski, Gregory J.; Pelosi, Charles, Use of SS data trends in fault resolution process.
Brunschwig, Anya R.; Grace, Amy Rose; Donovan, Bryan P.; Ruestow, Andrew D.; Kacprzynski, Gregory J.; Pelosi, Charles, Use of ss data trends in fault resolution process.
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