Electricity: electrical systems and devices – Igniting systems – For electric spark ignition
Reexamination Certificate
1998-06-02
2001-02-27
Fleming, Fritz (Department: 2836)
Electricity: electrical systems and devices
Igniting systems
For electric spark ignition
C361S247000
Reexamination Certificate
active
06195247
ABSTRACT:
BACKGROUND OF THE INVENTION
1. Field of the Invention
The present invention is addressed to an exciter circuit used as part of an engine ignition system, and in particular, an exciter circuit controlled by a full authority digital engine control, or FADEC.
2. Description of the Prior Art
Conventional ignition systems are well known in the art and typically include an exciter circuit having an energy storage device such as a capacitor and a circuit for charging the capacitor. The system will also include one or more igniter plugs in the circuit and a switching mechanism as part of a discharge circuit connected between the capacitor and the igniter. In aerospace applications, the switching mechanism has commonly been a spark gap, although more recently, solid state switching systems utilizing semiconductors have been employed in place of the older spark gap switching.
Because of the numerous electronic inputs and controls that must be exercised over a modern gas turbine engine, a system known as a Full Authority Digital Engine Control, or “FADEC”, has evolved to assist an aircraft pilot in managing these various inputs and controls. The FADEC is essentially a multiple channel computer that receives a limited number of information inputs from the aircraft pilot, as well as continuous input from the various sensors, switches, and drivers that are placed throughout the engine system. The FADEC analyzes the various inputs from these devices and sends control signals back to these devices to manage their operation. The FADEC system is known in the art, and was first disclosed in U.S. Pat. No. 4,718,229 to Riley issued on Jan. 12, 1988.
SUMMARY OF THE INVENTION
To date, no known attempt has been made to link the exciter system described above to a FADEC system. Because the exciter system components are vulnerable to failure as a result of uncontrolled use, such as when a continuous ignition start up is attempted, the introduction of the FADEC to control the exciter system offers the possibility of carefully controlling exciter usage and extending the service life of both the exciter as well as the associated igniters. The use of the FADEC also permits an automated detection of exciter failure, and an ability to switch to working exciters in the event of such a failure. This permits the aircraft to safely remain in flight service despite the failure of some of the exciters, thus reducing the overall down time of the aircraft. The use of the FADEC to control the exciter also opens up the possibility of overriding a communications failure with the exciter. The ability of a FADEC to switch communications channels when it detects a communications failure with a component assures constant control and management by the FADEC, and improves overall flight safety.
It is a feature of the present invention to provide a control system to an engine exciter system which controls and manages the usage of the exciter system.
It is another feature of the present invention to permit automated detection of an exciter failure, and automatic switching to a working exciter upon the detection of such a failure.
It is a further feature of the present invention to detect a communications equipment failure with the exciter, and override the failed communications equipment by automatically switching to the communication equipment of another channel.
According to the above features, from a broad aspect, the invention comprises an engine control system for controlling an exciter circuit. The control system has a processor with first and second channels. Each of the channels includes first and second communication ports. The system communicates with an exciter having first and second channels, with each of the channels including first and second communication ports. The system further includes power sources connected to both the processor and the exciter, as well as channel connections between the processor and the exciter for permitting each of the channels of the processor to communicate with each of the channels of the exciter.
According to the above features, from a second broad aspect, the invention provides a method of controlling a set of exciters in an ignition system. The exciters linked to a processor for receiving inputs from the exciters and sending control signals back to the exciters in response to said inputs. The method includes the steps of: (1) detecting a failure of one of the exciters; and (2) directing the processor to send control signals to another of the exciters.
According to the above features from a third broad aspect, the invention provides another method of controlling a set of exciters in an ignition system. The exciters are linked to a processor having first and second channels for receiving inputs from the exciter and sending control signals back to the exciter in response to the inputs. The method comprises the steps of: (1) detecting a communications failure in a first channel of the processor; and (2) directing the processor to send control signals from a second channel of the processor to the exciters.
These and other aspects and advantages of the present invention will be readily understood and appreciated by those skilled in the art from the following detailed description of the preferred embodiments with the best mode contemplated for practicing the invention in view of the accompanying drawings.
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PCT International Search Report, Aug. 31, 1999, European Patent Office.
Cote Pierre
Nobre Antonio Hernani
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