Icing resistance total temperature probe with integrated ejector

Patent metadata

Field	Value
Publication number	US-10436649-B2
Application number	US-201715583799-A
Country	US
Kind code	B2
Filing date	May 1, 2017
Priority date	May 1, 2017
Publication date	Oct 8, 2019
Grant date	Oct 8, 2019

Abstract

Embodiments of icing resistant total temperature probes with integrated ejectors are provided. One air data probe comprises: a base; a body having a leading and trailing edges: a first passage defining a first annulus; a temperature sensor within the first passage; a heat shield defining an exterior wall of at least part of the first passage, wherein the sensor is positioned within the shield; a second passage comprising a second annulus defined by a space between the shield and the body; an intake port having an intake aperture that opens to the first and second passages; a separate heated airflow passage, the heated airflow passage having an air input port configured to couple to an air supply source and following a path within the probe body; an integrated air ejector coupled to heated airflow passage to motivate air into the intake aperture and through the first and second air passages.

First claim

What is claimed is:

1. An air data probe, the probe comprising:
a probe base;
a probe body having a leading edge and a trailing edge and extending from the probe base along a first axis, the probe body comprising:
a first interior airflow passage defining a first annulus aligned with the first axis;
a temperature sensor positioned within the first airflow passage and aligned with the first axis;
a tubular heat shield defining an exterior wall of at least part of the first interior airflow passage, wherein the temperature sensor is positioned within the tubular heat shield;
a second interior airflow passage comprising a second annulus aligned with the first axis, wherein the second annulus is defined by a space between the tubular heat shield and an interior wall of the probe body, wherein the tubular heat shield separates the first annulus from the second annulus;
an intake port positioned at a distal end of the probe body, the intake port having a free airstream intake aperture that opens to the first interior airflow passage and the second interior airflow passage;
a heated airflow passage separate from the first interior airflow passage and the second interior airflow passage, the heated airflow passage having a forced air input port configured to couple to a pressurized air supply source, the heated airflow passage following a path that travels within the probe body;
an integrated air ejector coupled to the heated airflow passage, the integrated ejector configured to utilize an airflow from the heated airflow passage to generate a pressure differential to motivate a free stream of air into the free airstream intake aperture and through the first and second air passages to an ejector exhaust port.

2. The probe of claim 1 , wherein the ejector exhaust port is positioned at a distal surface on the distal end of the probe body.

3. The probe of claim 1 , wherein the ejector is positioned in the trailing edge of the probe body parallel to the probe axis.

4. The probe of claim 1 , wherein the tubular heat shield at the free air inlet is scarfed at a downward angle towards the trailing edge of the probe body.

5. The probe of claim 1 , the air ejector comprising:
an integrated ejector nozzle coupled to the heated airflow passage;
an ejector exhaust chamber; and
a low pressure aperture within the ejector exhaust chamber;
wherein the first interior airflow passage and the second interior airflow passage merge together within the probe body and discharge into the ejector exhaust chamber at the low pressure aperture;
wherein the integrated ejector nozzle is configured to discharge a heated air stream from the heated airflow passage into the ejector exhaust chamber generating a low pressure partial vacuum at the low pressure aperture that pulls air into the ejector exhaust chamber from the low pressure aperture.

6. The probe of claim 1 , wherein the intake port comprises a slot inset from a face of the intake port, wherein the slot traverses across at least a portion of the intake aperture.

7. The probe of claim 1 , wherein the intake aperture opens to both the first annulus and the second annulus.

8. The probe of claim 7 , wherein the first interior airflow passage and the second interior air-flow passage are concentric tubular airflow passages.

9. The probe of claim 1 , the probe further comprising:
at least one heating element positioned within the probe and configured to heat air flowing through the heated airflow passage.

10. The probe of claim 1 , wherein the intake port comprises a notched intake port that further includes a slot inset from a recessed face of the notched intake port;
wherein the flow traverses across at least a portion of the intake aperture perpendicularly to the open channel.

11. The probe of claim 1 , wherein the probe body includes one or more heat transfer elements that extend into the air flow path of the heated airflow passage.

12. The probe of claim 1 , wherein the heated airflow passage directs heated air to pass along the leading edge of the probe body prior to discharging into the integrated air ejector.

13. An on-board total air temperature data probe deicing system, the system comprising:
an on-board pressurized air source;
a total air temperature probe, the total air temperature probe comprising:
a probe base;
a probe body having a leading edge and a trailing edge and extending from the probe base along a first axis, the probe body comprising:
a first interior airflow passage defining a first annulus aligned with the first axis;
a temperature sensor positioned within the first airflow passage and aligned with the first axis;
a tubular heat shield defining an exterior wall of at least part of the first interior airflow passage, wherein the temperature sensor is positioned within the tubular heat shield;
a second interior airflow passage comprising a second annulus aligned with the first axis, wherein the second annulus is defined by a space between the tubular heat shield and an interior wall of the probe body, wherein the tubular heat shield separates the first annulus from the second annulus;
an intake port positioned at a distal end of the probe body, the intake port having a free airstream intake aperture that opens to the first interior airflow passage and the second interior airflow passage;
a heated airflow passage separate from the first interior airflow passage and the second interior airflow passage, the heated airflow passage having a forced air input port configured to couple to the pressurized air source, the heated airflow passage following a path that travels within the probe body;
an integrated air ejector coupled to the heated airflow passage, the integrated ejector configured to utilize an airflow from the heated airflow passage to generate a pressure differential to motivate a free stream of air into the free airstream intake aperture and through the first and second air passages to an ejector exhaust port.

14. The system of claim 13 , wherein the probe base is mounted to an aircraft surface such that the probe is exposed to the free stream total temperature.

15. The system of claim 13 wherein the probe base is mounted upstream of an engine inside of the engine inlet.

16. The system of claim 13 , wherein the on-board pressurized air source comprises a bleed air source from an aircraft engine compressor.

17. The system of claim 13 , further comprising at least one heating element configured to heat air supplied to the forced air input port.

18. The system of claim 13 , wherein the ejector exhaust port is positioned at a distal surface on the distal end of the probe body.

19. The system of claim 13 , wherein the tubular heat shield at the free air inlet is scarfed at a downward angle towards the trailing edge of the probe body.

20. The system of claim 13 , the air ejector comprising:
an integrated ejector nozzle coupled to the heated airflow passage;
an ejector exhaust chamber; and
a low pressure aperture within the ejector exhaust chamber;
wherein the first interior airflow passage and the second interior airflow passage merge together within the probe body and discharge into the ejector exhaust chamber at the low pressure aperture;
wherein the integrated ejector nozzle is configured to discharge a heated air stream from the heated airflow passage into the ejector exhaust chamber generating a low pressure partial vacuum at the low pressure aperture that pulls air into the ejector exhaust chamber from the low pressure aperture.

Assignees

• Honeywell Int Inc

Inventors

• Anderson Morris G
• Price Zachary
• Hollingshead Doug

Classifications

• G01K1/20 Primary

  Compensating for effects of temperature changes other than those to be measured, e.g. changes in ambient temperature · CPC title

• G01K2205/02

  for measuring inlet gas temperature · CPC title

• G01K13/02 Primary

  for measuring temperature of moving fluids or granular materials capable of flow · CPC title

• G01K13/028 Primary

  for use in total air temperature [TAT] probes · CPC title

• G01K1/08

  Protective devices, e.g. casings · CPC title