Control system for gas turbine aeroengine

• US 20070055435A1
• Filed: 05/11/2006
• Published: 03/08/2007
• Est. Priority Date: 05/16/2005
• Status: Active Grant

• Current Assignee: Honda Motor Co., Ltd. (Honda Motor Company)
• Original Assignee: Honda Motor Co., Ltd. (Honda Motor Company)
• Inventors: Tezuka, Makoto, Muramatsu, Hironori, Hattori, Yuichi
• Granted Patent: US 7,840,336 B2
• Time in Patent Office: Days
• US Class Current: 701/100
• CPC Class Codes: F02C 7/22 Fuel supply systems
• CPC Class Codes: F02C 9/263 by means of fuel metering valves
• CPC Class Codes: F02C 9/28 Regulating systems responsive to plant or ambient parameters, e.g. temperature, pressure, rotor speed F02C9/30 - F02C9/38, F02C9/44 take precedence
• CPC Class Codes: F05D 2260/80 Diagnostics
• CPC Class Codes: F05D 2270/094 by using back-up controls
• CPC Class Codes: F05D 2270/301 Pressure
• CPC Class Codes: F05D 2270/3011 Inlet pressure
• CPC Class Codes: F05D 2270/303 Temperature
• CPC Class Codes: F05D 2270/304 Spool rotational speed

Abstract

In a gas turbine aeroengine control system, in Ch-A (first control channel), a first CPU monitors the operation of a second CPU and the second CPU monitors the operation of the first CPU; in Ch-B (second control channel), third and fourth CPUs similarly monitor each other, and when the operation of at least one of the first and second CPUs in Ch-A is found not to be normal, the output sent to an FCU (fuel control unit) is switched from the output of one or the other of the first and second CPUs of Ch-A to the output of one or the other of the third and fourth CPUs of Ch-B, thereby achieving improved CPU failure detection and realizing high redundancy and high reliability.

Claims

1. A system for controlling operation of a gas turbine aeroengine having a turbine, comprising:

a speed sensor for producing an output indicative of a speed of the turbine;

a throttle lever angle sensor for producing an output indicative of an angle of a throttle lever, operated by a pilot, that represents a pilot-desired output of the engine;

a first control channel having at least a first CPU and a second CPU each inputting the outputs of the speed sensor and the throttle lever angle sensor, at least one of the first CPU and the second CPU acting as a first fuel supply command value calculator to calculate a fuel supply command value to be supplied to the engine such that the speed of the turbine becomes equal to a predetermined speed and to generate a first command output indicative of the fuel supply command value, the first CPU monitoring operation of the second CPU, while the second CPU monitoring operation of the first CPU;

a second control channel having at least a third CPU and a fourth CPU each inputting the outputs of the speed sensor and the throttle lever angle sensor, at least one of the third CPU and the fourth CPU acting as a second fuel supply command value calculator to calculate the fuel supply command value to be supplied to the engine such that the speed of the turbine becomes equal to the predetermined speed and to generate a second command output indicative of the fuel supply command value, the third CPU monitoring operation of the fourth CPU, while the fourth CPU monitoring operation of the third CPU;

a fuel control unit inputting at least the first command output of the first fuel supply command value calculator and supplying fuel to the engine based on the first command output of the first fuel supply command value calculator; and

a switch for switching the output to be inputted in the fuel control unit from the first command output to the second command output, when at least one of the first CPU and the second CPU of the first control channel is monitored to be not operating normally.

2. The system according to claim 1, wherein the first to the fourth CPUs monitor whether the detected speed of the turbine exceeds the predetermined speed and generate an overspeed signal when the detected speed of the turbine exceeds the predetermined speed.

3. The system according to claim 2, further including:

a discrimination circuit discriminating that the engine is overspeeding when at least two of the first to the fourth CPUs generate the overspeed signal.

4. The system according to claim 3, wherein the discrimination circuit includes:

a first OR circuit connected to the first CPU in the first control channel and the third and fourth CPUs in the second control channel, and generating an H level signal when at least one of the three CPUs generates the overspeed signal;

a second OR circuit connected to the third CPU in the second control channel and the first and second CPUs in the first control channel, and generating an H level signal when at least one of the three CPUs generates the overspeed signal;

a first AND circuit connected to the second CPU and the first OR circuit, and generating an H level signal when the second CPU generates the overspeed signal and the first OR circuit generates the H level signal; and

a second AND circuit connected to the fourth CPU and the second OR circuit, and generating an H level signal when the fourth CPU generates the overspeed signal and the second OR circuit generates the H level signal;

and discriminates that the engine is overspeeding when at least one of the first and second AND circuits generates the H level signal.

5. The system according to claim 1, wherein at least one of sensors, except for the speed sensor and the throttle lever angle sensor, is constituted as a single-system comprising at least one unit whose output is inputted to only one of the first and second control channels.

6. The system according to claim 5, wherein the at least one of the sensors comprises one from among a sensor producing an output indicative of a condition of atmosphere that can be sent from an onboard-computer.

7. A system for controlling operation of a gas turbine aeroengine having a low-pressure turbine and a high-pressure turbine, comprising:

a speed sensor for producing an output indicative of a speed of the low-pressure turbine;

a throttle lever angle sensor for producing an output indicative of an angle of a throttle lever, operated by a pilot, that represents a pilot-desired output of the engine;

a first control channel having at least a first CPU and a second CPU each inputting the outputs of the speed sensor and the throttle lever angle sensor, at least one of the first CPU and the second CPU acting as a first fuel supply command value calculator to calculate a fuel supply command value to be supplied to the engine such that the speed of the low-pressure turbine becomes equal to a predetermined speed and to generate a first command output indicative of the fuel supply command value, the first CPU monitoring operation of the second CPU, while the second CPU monitoring operation of the first CPU;

a second control channel having at least a third CPU and a fourth CPU each inputting the outputs of the speed sensor and the throttle lever angle sensor, at least one of the third CPU and the fourth CPU acting as a second fuel supply command value calculator to calculate the fuel supply command value to be supplied to the engine such that the speed of the low-pressure turbine becomes equal to the predetermined speed and to generate a second command output indicative of the fuel supply command value, the third CPU monitoring operation of the fourth CPU, while the fourth CPU monitoring operation of the third CPU;

a fuel control unit inputting at least the first command output of the first fuel supply command value calculator and supplying fuel to the engine based on the first command output of the first fuel supply command value calculator; and

a switch for switching the output to be inputted in the fuel control unit from the first command output to the second command output, when at least one of the first CPU and the second CPU of the first control channel is monitored to be not operating normally.

8. The system according to claim 7, further including:

a second speed sensor for producing an output indicative of a speed of the high-pressure turbine;

and the first to the fourth CPUs monitor whether the detected speed of the high-pressure turbine exceeds a predetermined speed and generate an overspeed signal when the detected speed of the high-pressure turbine exceeds the predetermined speed.

9. The system according to claim 8, further including:

a discrimination circuit discriminating that the engine is overspeeding when at least two of the first to the fourth CPUs generate the overspeed signal.

10. The system according to claim 9, wherein the discrimination circuit includes:

a first OR circuit connected to the first CPU in the first control channel and the third and fourth CPUs in the second control channels, and generating an H level signal when at least one of the three CPUs generates the overspeed signal;

a second OR circuit connected to the third CPU in the second control channel and the first and second CPUs in the first control channel, and generating an H level signal when at least one of the three CPUs generates the overspeed signal;

a first AND circuit connected to the second CPU and the first OR circuit, and generating an H level signal when the second CPU generates the overspeed signal and the first OR circuit generates the H level signal; and

a second AND circuit connected to the fourth CPU and the second OR circuit, and generating an H level signal when the fourth CPU generates the overspeed signal and the second OR circuit generates the H level signal;

and discriminates that the engine is overspeeding when at least one of the first and second AND circuits generates the H level signal.

11. The system according to claim 7, wherein at least one of sensors, except for the speed sensor and the throttle lever angle sensor, is constituted as a single-system comprising at least one unit whose output is inputted to only one of the first and second control channels.

12. The system according to claim 11, wherein the at least one of the sensors comprises one from among a sensor producing an output indicative of a condition of atmosphere that can be sent from an onboard-computer.