Icing resistance total temperature probe with integrated ejector

Patent metadata

Field	Value
Publication number	US-2018313698-A1
Application number	US-201715583799-A
Country	US
Kind code	A1
Filing date	May 1, 2017
Priority date	May 1, 2017
Publication date	Nov 1, 2018
Grant date	—

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 heated airflow passage, the integrated ejector configured 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 heated airflow passage, the integrated ejector configured 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

• G01K2205/02

  for measuring inlet gas temperature · CPC title

• G01K13/028 Primary

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

• G01K1/08

  Protective devices, e.g. casings · CPC title

• G01K13/02 Primary

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

• G01K1/14

  Supports; Fastening devices; Arrangements for mounting thermometers in particular locations · CPC title