Aircraft exhaust gas temperature monitor

• US 8,103,393 B2
• Filed: 10/19/2007
• Issued: 01/24/2012
• Est. Priority Date: 12/19/2005
• Status: Active Grant

• Current Assignee: Astronics Advanced Electronic Systems Corporation (Astronics Corporation)
• Original Assignee: Vertical Power, Inc. (Astronics Corporation)
• Inventors: Ausman, Marc, DeVries, Kevin
• Primary Examiner(s): Keith, Jack W
• Assistant Examiner(s): Khatib, Rami
• Application Number:
  US11/875,818
• Publication Number:
  US 20090306837A1
• Time in Patent Office: 1,558 Days
• Field of Search: 701/1, 701/3, 701 8- 11, 701/14, 701 99-104, 701108-109, 701/115, 340/945, 340/963, 340/964, 340/952, 340/953, 340/971, 244/75.1, 244/76.R, 244/194, 244/196, 244/197, 244/220, 244/99, 123434-435, 123672-676
• US Class Current: 701/14
• CPC Class Codes: F05D 2260/80 Diagnostics
• CPC Class Codes: F05D 2270/0831 indirectly, at the exhaust
• CPC Class Codes: G01D 2207/10 Displays which are primarily used in aircraft or display aircraft-specific information
• CPC Class Codes: G01D 7/00 Indicating measured values
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A computer-implemented function monitors and displays exhaust gas temperatures (EGT) in a plurality of cylinders in an engine. The invention provides an easy way to read exhaust gas temperature on a specific cylinder, and to provide a means for leaning the engine while in a climb. Efficient leaning in a climb reduces fuel consumption and reduces the chance of harmful conditions that can lead to engine failure.

Claims

1. A method for communicating engine status of an aircraft during climb to a pilot, comprising:

a) accepting from a human a designation of a target range of exhaust gas temperature and a designation of a reference cylinder of the engine;

b) sensing the exhaust gas temperature of the reference cylinder while the aircraft is climbing;

c) communicating to the pilot the sensed exhaust gas temperature and its relation to the target range of exhaust gas temperature.

2. A method of communicating exhaust gas temperature to a pilot of an aircraft, comprising:

a) accepting an indication of a temperature display range, where the temperature display range is within a predetermined range comprising a high temperature alert limit and a low temperature alert limit;

b) accepting from a human a designation of a reference cylinder;

c) sensing the exhaust gas temperature of the reference cylinder while the aircraft is climbing; and

d) displaying to the pilot an indication of the sensed temperature relative to the display range.

3. A method as in claim 2, further comprising sensing the exhaust gas temperature in at least one cylinder other than the reference cylinder, and displaying to the pilot an indication of the exhaust gas temperature in the other cylinder relative to the display range.

4. A method as in claim 2, further comprising providing an alert to the pilot if the sensed temperature is not within predetermined limits.

5. A method as in claim 2, wherein the display to the pilot is activated upon an input from the pilot requesting an exhaust gas temperature display.

6. A method as in claim 2, wherein the display to the pilot is activated upon determination that the aircraft is in climb mode where monitoring of exhaust gas temperature is desired.

7. A method as in claim 2, wherein accepting an indication of a temperature display range further comprises accepting an indication of a target temperature.

8. A method as in claim 2, wherein the temperature display range is less than 40% of a total possible exhaust gas temperature range.

9. A method as in claim 8, wherein the temperature display range is less than 20% of the total possible exhaust gas temperature range.

10. A method as in claim 9, wherein the temperature display range is less than 10% of the total possible exhaust gas temperature range.

11. An apparatus for the communication of exhaust gas temperature to a pilot of an aircraft, comprising:

a) a plurality of exhaust gas sensors, each mounted with an engine of the aircraft such that the sensor provides a signal representative of exhaust gas temperature corresponding to a cylinder of the engine;

b) a display;

c) a pilot input system, configured to accept a request for an exhaust gas temperature display and a designation of;

(i) a reference cylinder, and (ii) a target exhaust gas temperature; and

d) a controller, configured to use the display to present to the pilot the exhaust gas temperatures provided by the sensors while the aircraft is climbing relative to a predetermined range of temperatures, where the predetermined range comprises a high temperature alert limit and a low temperature alert limit.

12. An apparatus as in claim 11, wherein the pilot input system is configured to accept the predetermined range of temperatures from the pilot.

13. An apparatus as in claim 11, wherein the pilot input system is configured to accept designation of a reference cylinder from the pilot, and wherein the controller highlights the display of the exhaust gas temperature in the reference cylinder.