Gas turbine aeroengine control system

• US 6,353,790 B1
• Filed: 08/11/2000
• Issued: 03/05/2002
• Est. Priority Date: 10/05/1999
• Status: Expired due to Term

• Current Assignee: Honda Giken Kogyo Kabushiki Kaisha (Honda Motor Company)
• Original Assignee: Honda Giken Kogyo Kabushiki Kaisha (Honda Motor Company)
• Inventors: Tsuzuki, Sadachika
• Primary Examiner(s): Cuchlinski, Jr., William A.
• Assistant Examiner(s): To, Tuan C
• Application Number:
  US09/636,751
• Time in Patent Office: 571 Days
• Field of Search: 701/100, 701/14, 701/11, 701/12, 714/49, 714/51, 602/04, 602/36, 602/42, 602/35, 602/34, 602/39
• US Class Current: 701/100
• CPC Class Codes: F02C 9/263 by means of fuel metering valves
• CPC Class Codes: F05D 2260/84 Redundancy
• CPC Class Codes: F05D 2270/54 by electronic means, e.g. electronic tubes, transistors or IC's within an electronic circuit
• CPC Class Codes: G05B 9/02 electric

Abstract

In a control system for a gas turbine aero engine, the control system (ECU) is configured as a dual control system comprising two channels, Ch-A and Ch-B. Ch-A has two CPUs which conduct calculations separately based on the sensor outputs and one of the CPUs compares the results and if they coincide, the CPU sends the result of the other CPU to the FCU. If not, one of the CPUs determines that an abnormality arises in Ch-A and sends a result to Ch-B. Ch-B is constituted as a standby channel having only one CPU whose operation is monitored by a simple watchdog timer circuit. This enhances CPU failure detection with a relatively simple configuration, and eliminates the need for provision of an overspeed protector.

Claims

1. A system for controlling a gas turbine aeroengine having at least a turbine which is rotated by gas produced by the engine to rotate a rotor that sucks in air, having:

a first control system including;

a speed sensor for detecting a rotational speed of the turbine;

operator desired power output detecting means for detecting a desired power output of the engine specified by an operator;

first command value calculating means for calculating a first command value based at least on the detected rotational speed of the turbine and the desired power output such that a fuel flow rate to be supplied to the engine is brought to a prescribed value in at least a case when the detected rotational speed of the turbine exceeds a predetermined value, and for calculating the first command value at a fuel flow rate needed to bring the detected rotational speed of the turbine to a speed corresponding to the desired power output in at least a case when the detected rotational speed of the turbine does not exceed the predetermined value;

fuel supplying means for supplying fuel to the engine based on the calculated command value; and

first monitor means for monitoring whether operation of the first command value calculating means is normal;

wherein the improvement comprises;

the first monitor means including;

second command value calculating means for calculating a second command value based at least on the detected rotational speed of the turbine and the desired power output such that the fuel flow rate to be supplied to the engine is brought to the prescribed value in at least the case when the detected rotational speed of the turbine exceeds the predetermined value, and for calculating the second command value at the fuel flow rate needed to bring the detected rotational speed of the turbine to the speed corresponding to the desired power output in at least the case when the detected rotational speed of the turbine does not exceed the predetermined value; and

command value comparing means for comparing the first command value and the second command value with each other and for sending the first command value to the fuel supplying means when the first command value and the second command value coincide completely or at least substantially,

the second control system, provided parallel with the first control system, the second control system including;

third command value calculating means for calculating a third command value based at least on the detected rotational speed of the turbine and the desired power output such that the fuel flow rate to be supplied to the engine is brought to the prescribed value in at least the case when the detected rotational speed of the turbine exceeds the predetermined value, and for calculating the third command value at the fuel flow rate based on the desired power output in at least the case when the detected rotational speed of the turbine does not exceed the predetermined value; and

second monitor means for monitoring whether operation of the third command value calculating means is normal and for generating a command value such that the fuel flow rate to be supplied to the engine is brought to the prescribed value when the operation of the third command value calculating means is monitored to be not normal;

and the first monitoring means sends the third command value to the fuel supplying means when the operation of the first command value calculating means is monitored to be not normal.

2. A system according to claim 1, wherein the first command value calculating means calculates the first command value such that the fuel flow rate to be supplied to the engine is brought to zero or a minimum value in at least the case when the detected rotational speed of the turbine exceeds the predetermined value.

3. A system according to claim 1, wherein the second command value calculating means calculates the first command value such that the fuel flow rate to be supplied to the engine is brought to zero or a minimum value in at least the case when the detected rotational speed of the turbine exceeds the predetermined value.

4. A system according to claim 1, wherein the third command value calculating means calculates the first command value such that the fuel flow rate to be supplied to the engine is brought to zero or a minimum value in at least the case when the detected rotational speed of the turbine exceeds the predetermined value.

5. A system for controlling a gas turbine aeroengine having at least a turbine which is rotated by gas produced by the engine to rotate a rotor that sucks in air, having:

a first control system including;

a speed sensor for detecting a rotational speed of the turbine;

operator desired power output detecting means for detecting a desired power output of the engine specified by an operator;

first command value calculating means for calculating a first command value based at least on the detected rotational speed of the turbine and the desired power output such that a fuel flow rate to be supplied to the engine is brought to a prescribed value in at least a case when the detected rotational speed of the turbine exceeds a predetermined value, and for calculating the first command value at a fuel flow rate needed to bring the detected rotational speed of the turbine to a speed corresponding to the desired power output in at least the case when the detected rotational speed of the turbine does not exceed the predetermined value;

fuel supplying means for supplying fuel to the engine based on the calculated command value; and

first monitor means for monitoring whether operation of the first command value calculating means is normal;

wherein the improvement comprises;

the first monitor means including;

second command value calculating means for calculating a second command value based at least on the detected rotational speed of the turbine and the desired power output such that the fuel flow rate to be supplied to the engine is brought to the prescribed value in at least the case when the detected rotational speed of the turbine exceeds the predetermined value, and for calculating the second command value at the fuel flow rate needed to bring the detected rotational speed of the turbine to the speed corresponding to the desired power output in at least the case when the detected rotational speed of the turbine does not exceed the predetermined value; and

command value comparing means for comparing the first command value and the second command value with each other and for sending the first command value to the fuel supplying means when the first command value and the second command value coincide completely or at least substantially,

the second control system, provided parallel with the first control system, the second control system including;

third command value calculating means for calculating a third command value based at least on the detected rotational speed of the turbine and the desired power output such that the fuel flow rate to be supplied to the engine is brought to the prescribed value in at least the case when the detected rotational speed of the turbine exceeds the predetermined value, and for calculating the third command value at the fuel flow rate based on the desired power output in at least the case when the detected rotational speed of the turbine does not exceed the predetermined value;

and wherein the first control system monitors whether operation of the third command value calculating means is normal and for informing the operator when the operation of the third command value calculating means is monitored to be not normal.

6. A system according to claim 5, wherein the first command value calculating means calculates the first command value such that the fuel flow rate to be supplied to the engine is brought to zero or a minimum value in at least the case when the detected rotational speed of the turbine exceeds the predetermined value.

7. A system according to claim 5, wherein the second command value calculating means calculates the first command value such that the fuel flow rate to be supplied to the engine is brought to zero or a minimum value in at least the case when the detected rotational speed of the turbine exceeds the predetermined value.

8. A system according to claim 5, wherein the third command value calculating means calculates the first command value such that the fuel flow rate to be supplied to the engine is brought to zero or a minimum value in at least the case when the detected rotational speed of the turbine exceeds the predetermined value.