FLUID PRESSURE BASED ICING DETECTION FOR A TURBINE ENGINE

• US 20130099944A1
• Filed: 10/19/2011
• Published: 04/25/2013
• Est. Priority Date: 10/19/2011
• Status: Abandoned Application

• Current Assignee: Honeywell International Inc.
• Original Assignee: Honeywell International Inc.
• Inventors: Dischinger, Dave, Repp, John, Hanson, David Richard, Goodwin, Ronald
• Application Number:
  US13/277,002
• Publication Number:
  US 20130099944A1
• Time in Patent Office: Days
• US Class Current: 340/962
• CPC Class Codes: F01D 21/10 responsive to unwanted deposits on blades, in working-fluid conduits or the like
• CPC Class Codes: F01D 25/02 De-icing means for engines having icing phenomena

Abstract

An icing detection subsystem for an aircraft turbine engine is presented. The icing detection subsystem includes a plurality of air pressure sampling ports formed within structure that surrounds a rotating component of the aircraft turbine engine. The subsystem also includes a pressure sensor arrangement coupled to the plurality of air pressure sampling ports to obtain air pressure measurements for the plurality of air pressure sampling ports. A processing module is coupled to the pressure sensor arrangement to analyze the air pressure measurements over time during operation of the aircraft turbine engine, and to generate an alert when at least one characteristic of the air pressure measurements over time is indicative of the presence of ice in the aircraft turbine engine.

Claims

1. A method for detecting icing in an aircraft turbine engine, the method comprising:

measuring air pressure at a port located near a rotating component of the aircraft turbine engine to obtain air pressure measurements; and

warning of a potential icing condition when at least one characteristic of the air pressure measurements over time is indicative of the presence of ice covering the port.

2. The method of claim 1, wherein the port is located aft of the rotating component.

3. The method of claim 1, wherein the rotating component is a fan of the aircraft turbine engine.

4. The method of claim 1, wherein the rotating component is a compressor rotor of the aircraft turbine engine.

5. The method of claim 1, wherein the warning step indicates the potential icing condition when an amount of variation in magnitude of the air pressure measurements is less than a threshold magnitude value.

6. The method of claim 1, wherein the warning step indicates the potential icing condition when frequency of the air pressure measurements over time is less than a threshold frequency value.

7. The method of claim 1, further comprising:

generating a flight crew alert in response to the warning.

8. The method of claim 1, wherein:

the aircraft turbine engine comprises a plurality of air pressure sampling ports, including the port located near the rotating component;

the method further comprises measuring air pressure at the plurality of air pressure sampling ports to obtain respective air pressure measurements for each of the plurality of air pressure sampling ports; and

warning of the potential icing condition when at least one characteristic of any of the respective air pressure measurements over time is indicative of the presence of ice.

9. A turbine engine comprising:

a rotating component;

structure associated with the rotating component, wherein the rotating component rotates within the structure when the turbine engine is operating;

an air pressure sampling port formed within the structure and exposed to airspace defined within the structure;

a pressure sensor fluidly coupled to the air pressure sampling port to obtain air pressure measurements for the air pressure sampling port; and

a processing module coupled to the pressure sensor to analyze the air pressure measurements over time and to determine when at least one characteristic of the air pressure measurements over time is indicative of the presence of ice at the air pressure sampling port.

10. The turbine engine of claim 9, wherein the air pressure sampling port is positioned at a location aft of the rotating component.

11. The turbine engine of claim 9, wherein the rotating component is a fan of the turbine engine.

12. The turbine engine of claim 9, wherein the rotating component is a compressor rotor of the turbine engine.

13. The turbine engine of claim 9, wherein the processing module analyzes an amount of variation in magnitude of the fluid pressure measurements over time, and indicates a potential icing condition when the amount of variation in magnitude is less than a threshold magnitude value.

14. The turbine engine of claim 9, wherein the processing module analyzes frequency content of the fluid pressure measurements over time, and indicates a potential icing condition when the frequency content is less than a threshold frequency value.

15. The turbine engine of claim 9, wherein the structure comprises a flowpath shroud.

16. The turbine engine of claim 9, further comprising a conduit coupled between the air pressure sampling port and the pressure sensor.

17. An icing detection subsystem for an aircraft turbine engine, the icing detection subsystem comprising:

a plurality of air pressure sampling ports formed within structure that surrounds a rotating component of the aircraft turbine engine;

a pressure sensor arrangement coupled to the plurality of air pressure sampling ports to obtain air pressure measurements for the plurality of air pressure sampling ports; and

a processing module coupled to the pressure sensor arrangement to analyze the air pressure measurements over time during operation of the aircraft turbine engine, and to generate an alert when at least one characteristic of the air pressure measurements over time is indicative of the presence of ice in the aircraft turbine engine.

18. The icing detection subsystem of claim 17, wherein the pressure sensor arrangement comprises a plurality of different pressure sensors.

19. The icing detection subsystem of claim 17, wherein the pressure sensor arrangement comprises a shared pressure sensor that obtains air pressure measurements for at least two different ones of the plurality of air pressure sampling ports.

20. The icing detection subsystem of claim 17, wherein:

under normal operating conditions the air pressure measurements exhibit variation in magnitude at a frequency corresponding to movement of the rotating component near the plurality of air pressure sampling ports;

under icing conditions the air pressure measurements exhibit attenuated variation in magnitude when ice covers at least some of the plurality of air pressure sampling ports; and

the processing module generates an alert when the attenuated variation in magnitude is detected.