Comprehensive engine monitor and recorder

• US 4,787,053 A
• Filed: 10/04/1985
• Issued: 11/22/1988
• Est. Priority Date: 12/30/1981
• Status: Expired due to Fees

• Current Assignee: Semco Instruments Incorporated North Hollywood California
• Original Assignee: Semco Instruments, Inc. (Transdigm Group Incorporated)
• Inventors: Moore, M. Samuel
• Primary Examiner(s): Lall, Parshotam S.
• Assistant Examiner(s): Ramirez, Ellis B.
• Application Number:
  US06/784,724
• Time in Patent Office: 1,145 Days
• Field of Search: 364/442, 364/550, 364/551, 364/507, 340/945, 340/959, 340/963, 73/117.4, 360/5
• US Class Current: 701/123
• CPC Class Codes: F01D 21/00 Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
• CPC Class Codes: F02C 9/00 Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants controlling air intakes F02C7/057; controlling turbines F01D; controlling compressors F04D27/00; controlling in general G05
• CPC Class Codes: G01D 21/02 Measuring two or more variables by means not covered by a single other subclass
• CPC Class Codes: G01K 1/02 Means for indicating or recording specially adapted for thermometers
• CPC Class Codes: G07C 3/00 Registering or indicating the condition or the working of machines or other apparatus, other than vehicles

Abstract

A comprehensive turbine engine monitoring and recording system includes an electronics unit which may be engine mounted, and which contains at least a nonvolatile memory and a data-processor, for use with a remote unit suitable for either cockpit mounting or for accessing by a ground portable unit which may include an additional data-processor and display and/or printer units. Raw input data is supplied to the electronics unit, and this input information may include engine and outside air temperature, torque, engine speed, vibration, altitude and airspeed data, for examples. Exceedance data relative to the operation of the aircraft above pre-defined limits of temperature, torque and speed are recorded, with the details of each exceedance being permanently stored. In addition, over-limits levels are segregated and the total time during which the engine is operated within each of the over-limits bands is measured, and is recorded in a non-volatile, electronically alterable memory which is periodically updated during operation of the aircraft. The number of starts, and power cycles are also counted and stored, and the total running time of the engine is also recorded. Upon command from the remote unit, information is transferred from the non-volatile memory to any of a number of remote data storage, or data processing units, which may include printer and/or display units, so that the time at which the turbine has been operated at specific over-temperature levels, and other important operating data may be readily accessed. Data required for engine trend monitoring is also automatically recorded so that long term plots and interpretation of engine degradation may be accomplished.

Claims

1. A comprehensive aircraft turbine engine monitoring and recording system whereby said turbine engine has predetermined maximum normal operating parameters, said system comprising:

means for sensing the speed of rotation of said turbine engine;

means for sensing temperature of said turbine engine;

means for sensing altitude;

means for determining exceedances indicating operation of said turbine engine over the normal operating temperature and/or speed of said engine;

means for determining the air speed of said aircraft;

non-volatile storage means for permanently storing data giving the duration and magnitude of each said exceedance, and the total duration of the exceedances;

means for recording and processing data required for turbine engine trend monitoring, including means for calculating horsepower and the air density index factor, and the resultant optimum fuel flow rate, engine speed and engine temperature under these horsepower and air density conditions;

means for determining the actual fuel flow rate, engine speed and engine temperature;

means for determining the variances from the optimum for the fuel flow rate, the engine speed and the engine temperature;

means for numerically displaying selected data from said system;

means for mounting said numerical display means in the cockpit of the aircraft; and

switching means in the cockpit for actuation by the pilot for selecting any of at least ten desired sensed or calculated information or data, to be displayed, including altitude and airspeed;

whereby said display provides a backup source of instrumentation for the pilot of the aircraft, and whereby an evaluation of the engine degradation trend may be made for purposes of power assurance, engine overhaul scheduling, or the like.

2. A comprehensive turbine engine monitoring and recording system as defined in claim 1 further including means for recording the time of occurrence of each exceedance.

3. A comprehensive turbine engine monitoring and recording system as defined in claim 1 further comprising means for permanently storing in nonvolatile storage the total running time of said turbine engine.

4. A comprehensive turbine engine monitoring and recording system as defined in claim 1 further comprising means for permanently recording the number of times the turbine engine has been operated at a predetermined level.

5. A comprehensive turbine engine monitoring and recording system as defined in claim 1 wherein means are provided for permanently recording the temperature exceedances in accordance with successive temperature bands above the normal maximum operating temperature of said engine.

6. A comprehensive turbine engine monitoring and recording system as defined in claim 1 further comprising means for selectively transmitting all or selected portions of the permanently stored data to a location spaced from said system, upon command.

7. A system as defined in claim 1 further comprising means for graphically displaying said exceedances and for printing out detailed information relating to each of a plurality of said exceedances.

8. A system as define in claim 1 including a remote computer and a graphics printer for displaying said data, and means for coupling said computer and printer to receive data from said system.

9. A system as defined in claim 6 further including a remote data processing apparatus and modem means for transmitting said data from said system to said remote data processing apparatus.

10. A system as defined in claim 1 further including means for sensing the output torque or power from said turbine engine, and means for determining exceedances indicating operation of said engine over the normal rated output torque capacity of said engine, and means for permanently recording information relative to such exceedances.

11. A system as defined in claim 1 further comprising means for establishing a plurality of levels or bands of engine operation relating to critical engine parameters such as temperature, engine speed, or torque, with such levels being closely related to the rated maximum operating limits of said engine, and means for recording the time of operation in each of said levels or bands.

12. A comprehensive aircraft turbine engine monitoring and recording system wherein said turbine engine has predetermined maximum normal operating parameters, said system comprising:

means for sensing the speed of rotation of said turbine engine;

means for sensing the temperature of said turbine engine;

means for sensing the output torque of said turbine engine;

means for determining exceedances indicating operation of said turbine engine over the normal operating temperature, torque and/or speed of said engine;

non-volatile storage means for permanently storing data giving the duration and approximate magnitude of each said exceedance, and the total duration of the exceedances;

means for recording and processing data required for turbine engine trend monitoring, including means for calculating horsepower and the air density index factor, and the resultant optimum fuel flow rate, engine speed and engine temperature under these horsepower and air density conditions;

means for determining the actual fuel flow rate, engine speed, engine temperature;

optimum for the fuel flow rate, the engine speed and the engine temperature;

means for numerically displaying selected data from said system;

means for mounting said numerical display means in the cockpit of the aircraft; and

switching means in the cockpit for actuation by the pilot for selecting any of at least ten desired sensed or calculated information or data, to be displayed;

whereby an evaluation of the engine degradation trend may be made for purposes of power assurance, engine overhaul scheduling, or the like.

13. A comprehensive turbine engine monitoring and recording system as defined in claim 12 further including means for recording the time of occurrence of each exceedance.

14. A comprehensive turbine engine monitoring and recording system as defined in claim 12 further comprising means for permanently storing in nonvolatile storage the total running time of said turbine engine.

15. A comprehensive turbine engine monitoring and recording system as defined in claim 12 further comprising means for permanently recording the number of times the turbine engine has been operated at a predetermined level.

16. A comprehensive turbine engine monitoring and recording system as defined in claim 12 wherein means are provided for permanently recording the temperature exceedances in accordance with successive temperature bands above the normal maximum operating temperature of said engine.

17. A system as defined in claim 12 further comprising means for establishing a plurality of levels or bands of engine operation relating to critical engine parameters such as temperature, engine speed, or torque, with such levels being closely related to the rated maximum operating limits of said engine, and means for recording the time of operation in each of said levels or bands.

18. A comprehensive turbine engine monitoring and recording system as defined in claim 12 further comprising means for selectively transmitting all or selected portions of the permanently stored data to a location spaced from said system, upon command.

19. A system as defined in claim 18 further comprising means for displaying selected data transmitted from said system.

20. A comprehensive aircraft monitoring and recording system for a turbine engine wherein the engine manufacturer has established certain normal maximum temperature and torque levels for said engine, said unit comprising:

means for measuring turbine engine temperature;

means for measuring turbine engine speed;

means for measuring turbine engine torque;

means for measuring turbine engine fuel flow;

means for measuring the number of times said turbine engine is operated;

means for measuring the total operating time of said turbine engine;

data processing circuit means for periodically sampling all of the foregoing measured quantities, and for determining when the temperature and/or torque exceeds the manufacturer'"'"'s normal maximum rated temperature and/or torque figures;

means for recording the duration and approximate maximum exceedance level for each time that the turbine engine is operated beyond the manufacturer'"'"'s normal rated maximum torque and/or temperature;

means for permanently storing data on (1) each exceedance, (2) engine run time, (3) the number of times the engine has been operated, and (4) total exceedance time;

means for transmitting all of selected portions of said permanently stored data to a location spaced from said unit, upon command;

means for numerically displaying selected data from said system;

means for mounting said numerical display means in the cockpit of the aircraft; and

switching means in the cockpit for actuation by the pilot for selecting any of at least ten desired sensed or calculated information or data, to be displayed.

21. A comprehensive turbine engine monitoring and recording system as defined in claim 20 further including means for recording the time of occurrence of each exceedance.

22. A system as defined in claim 20 further comprising means for establishing a plurality of levels of bands of engine operation relating to critical engine parameters such as temperature, engine speed, or torque, with such levels being closely related to the rated maximum operating limits of said engine, and means for recording the time of operation in each of said levels of bands.

23. A comprehensive aircraft turbine engine monitoring and recording system whereby said turbine engine has predetermined maximum normal operating parameters, said system comprising:

means for establishing at least three levels or bands of engine operation relating to critical engine parameters such as temperature, engine speed or torque, with such levels being closely related to the rated maximum operating limits of said engine,

means for recording the time of operation of said engine in each of said levels or bands;

non-volatile storage means for permanently storing data giving the duration and magnitude of exceedances when the engine is operated above said limits, and the total duration of the exceedances;

means for recording and processing data required for turbine engine trend monitoring, including means for calculating horsepower and the air density index factor, and the resultant optimum fuel flow rate, engine speed and engine temperature under these horsepower and air density conditions;

means for determining the actual fuel flow rate, engine speed and engine temperature; and

means for determining the variances from the optimum for the fuel flow rate, the engine speed and the engine temperature;

means for numerically displaying selected data from said system;

means for mounting said numerical display means in the cockpit of the aircraft; and

switching means in the cockpit for actuation by the pilot for selecting any of at least ten desired sensed or calculated information or data, to be displayed;

whereby an evaluation of the engine degradation trend may be made for purposes of power assurance, engine overhaul scheduling, or the like.

24. A comprehensive turbine engine monitoring and recording system as defined in claim 23 further including means for recording the time of occurrence of each exceedance.

26. A system as defined in claim 23 including a remote computer and a graphics printer for displaying said data, and means for coupling said computer and printer to receive data from said system.

27. A comprehensive turbine engine monitoring and recording system as defined in claim 23 further comprising means for selectively transmitting all or selected portions of the permanently stored data to a location spaced from said system, upon command.

28. A system as defined in claim 27 further comprising means for displaying selected data transmitted from said system.

25. A comprehensive turbine engine monitoring and recording system as defined in 23 further comprising means for permanently storing in nonvolatile storage the total running time of said turbine engine.

29. A comprehensive aircraft turbine monitoring and recording system, comprising:

an electronic data processing unit including a permanent non-volatile memory;

means for supplying to said data processing unit substantially all of the major aircraft operational data and the turbine operating parameters, for storage of this information by said data processing unit;

a cockpit mounted display unit coupled to said data processing unit, and including switch means for selecting any of at least ten desired aircraft operational data or turbine operating parameters and for displaying the selected data;

whereby detailed aircraft turbine engine data is available for display, as well as altitude and other aircraft operating data which may be selectively obtained for standby or check purposes in the event of cockpit instrumentation failure.