Supercritical total air temperature sensors

Patent metadata

Field	Value
Publication number	US-9488534-B2
Application number	US-201414189885-A
Country	US
Kind code	B2
Filing date	Feb 25, 2014
Priority date	Sep 5, 2013
Publication date	Nov 8, 2016
Grant date	Nov 8, 2016

Abstract

A total air temperature sensor includes a supercritical airfoil body extending from an airfoil base to an opposed airfoil tip along a longitudinal axis. The supercritical airfoil body defines an interior flow passage with an inlet for fluid communication of fluid into the interior flow passage and an outlet for exhausting fluid out from the interior flow passage. A temperature probe is mounted within the interior flow passage for measuring temperature of flow through the interior flow passage to determine total air temperature.

First claim

What is claimed is:

1. A total air temperature sensor comprising:
a supercritical airfoil body extending from an airfoil base to an opposed airfoil tip along a longitudinal axis, wherein the supercritical airfoil body defines an interior flow passage with an inlet for fluid communication of fluid into the interior flow passage and an outlet for exhausting fluid out from the interior flow passage; and
a temperature probe mounted within the interior flow passage for measuring temperature of flow through the interior flow passage to determine total air temperature.

2. A total air temperature sensor as recited in claim 1 , wherein the supercritical airfoil body defines a supercritical airfoil with a characteristic normal shock location downstream of the inlet and outlet of the interior flow passage.

3. A total air temperature sensor as recited in claim 2 , wherein the supercritical airfoil extends from a leading edge to a trailing edge that extends downstream of the characteristic normal shock location.

4. A total air temperature sensor as recited in claim 2 , wherein the supercritical airfoil extends from a leading edge to a truncated trailing edge that terminates upstream of the characteristic normal shock location.

5. A total air temperature sensor as recited in claim 1 , wherein the supercritical airfoil body defines a high pressure surface and an opposed low pressure surface each extending longitudinally from the airfoil base to the airfoil tip, wherein each of the high and low pressure surfaces extends downstream from a leading edge to a trailing edge of the supercritical airfoil body, and wherein the inlet of the interior flow passage is defined in the high pressure surface.

6. A total air temperature sensor as recited in claim 5 , wherein the outlet of the interior flow passage is defined in the low pressure surface.

7. A total air temperature sensor as recited in claim 1 , wherein the inlet of the interior flow passage is defined axially in the airfoil tip.

8. A total air temperature sensor as recited in claim 7 , wherein the supercritical airfoil body defines a high pressure surface and an opposed low pressure surface each extending longitudinally from the airfoil base to the airfoil tip, wherein each of the high and low pressure surfaces extends downstream from a leading edge to a trailing edge of the supercritical airfoil body, and wherein the outlet of the interior flow passage is defined in one or more of the high and low pressure surfaces.

9. A total air temperature sensor as recited in claim 1 , wherein the inlet of the interior flow passage defines an elongate aperture extending axially along an exterior longitudinal surface of the supercritical airfoil body.

10. A total air temperature sensor as recited in claim 1 , wherein the outlet of the interior flow passage defines an elongate aperture extending axially along an exterior longitudinal surface of the supercritical airfoil body.

11. A total air temperature sensor as recited in claim 1 , wherein the outlet of the interior flow passage defines a pair of elongate apertures each extending axially along a respective one of two opposing exterior longitudinal surfaces of the supercritical airfoil body.

12. A total air temperature sensor comprising:
a supercritical airfoil body extending from an airfoil base to an opposed airfoil tip along a longitudinal axis, wherein the supercritical airfoil body defines an interior flow passage with an inlet for fluid communication of fluid into the interior flow passage and an outlet for exhausting fluid out from the interior flow passage; and
a temperature probe mounted within the interior flow passage for measuring temperature of flow through the interior flow passage to determine total air temperature, wherein the inlet of the interior flow passage is defined axially in the airfoil tip, and wherein the outlet of the interior flow passage defines a pair of elongate apertures each extending axially along a respective one of two opposing exterior longitudinal surfaces of the supercritical airfoil body.

13. A total air temperature sensor as recited in claim 12 , wherein the supercritical airfoil body defines a supercritical airfoil with a characteristic normal shock location downstream of the inlet and outlet of the interior flow passage.

14. A total air temperature sensor as recited in claim 13 , wherein the supercritical airfoil extends from a leading edge to a trailing edge that extends downstream of the characteristic normal shock location.

15. A total air temperature sensor as recited in claim 13 , wherein the supercritical airfoil extends from a leading edge to a truncated trailing edge that terminates upstream of the characteristic normal shock location.

Assignees

• Rosemount Aerospace Inc

Inventors

• Wigen Scott
• Gmach Matthew J T
• Sable Robert E
• Otto John T

Classifications

• G01K13/028 Primary

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