Method of detecting a fault with the means for de-icing a probe for measuring a physical parameter

• US 8,994,392 B2
• Filed: 06/22/2011
• Issued: 03/31/2015
• Est. Priority Date: 06/25/2010
• Status: Active Grant

• Current Assignee: Safran Aircraft Engine Company
• Original Assignee: Snecma (Safran SA)
• Inventors: Biraud, Benoit, Godel, Franck
• Primary Examiner(s): PATEL, PARESH H
• Application Number:
  US13/805,147
• Publication Number:
  US 20130088249A1
• Time in Patent Office: 1,378 Days
• Field of Search: None
• US Class Current: 324/750.3
• CPC Class Codes: B64D 15/20 Means for detecting icing or initiating de-icing
• CPC Class Codes: F01D 17/08 responsive to condition of working-fluid, e.g. pressure
• CPC Class Codes: F05D 2260/80 Diagnostics
• CPC Class Codes: F05D 2260/85 Starting
• CPC Class Codes: G01D 3/08 with provision for safeguarding the apparatus, e.g. against abnormal operation, against breakdown
• CPC Class Codes: G01K 15/00 Testing or calibrating of thermometers
• CPC Class Codes: G01K 15/007 Testing
• CPC Class Codes: G01R 31/2829 Testing of circuits in sensor or actuator systems testing of apparatus for measuring electric or magnetic variables G01R35/00; testing of indicating or recording apparatus G01D; in airbag systems B60R21/0173; checking gas analysers G01N33/007; monitoring or fail-safe circuits for electromagnets H01F7/1844

Abstract

A method of detecting a fault in a de-icer probe for measuring a physical parameter on an airplane engine, the method including: prior to starting an engine, measuring a first value of the physical parameter with help of the probe; activating the probe de-icer; at an end of a determined duration from a start of de-icing, measuring a second value of the parameter with help of the probe; and comparing the first and second values and generating a fault signal if the difference between the first and second values is less than a determined threshold.

Claims

1. A method of detecting a fault in a de-icer means of a probe for measuring a physical parameter on an airplane engine, the method comprising:

prior to starting an engine, measuring a first value of the physical parameter with help of the probe;

activating the probe de-icer means;

at an end of a determined duration from a start of de-icing, measuring a second value of the parameter with help of the probe; and

comparing the first and second values and generating a fault signal if the difference between the first and second values is less than a determined threshold.

2. A method according to claim 1, wherein the parameter measured with help of the probe is temperature.

3. A method according to claim 1, wherein the parameter measured with help of the probe is pressure.

4. A method according to claim 1, wherein the second value of the parameter is measured with help of the probe after a duration lying in a range of 10 seconds to 1 minute from the start of de-icing.

5. A method according to claim 1, wherein the second value of the parameter is measured with help of the probe after a duration equal to about 20 seconds.