Pressure and temperature sensors and methods of removing ice from pressure and temperature sensors

Patent metadata

Field	Value
Publication number	US-11879345-B2
Application number	US-202016805456-A
Country	US
Kind code	B2
Filing date	Feb 28, 2020
Priority date	Feb 28, 2020
Publication date	Jan 23, 2024
Grant date	Jan 23, 2024

Abstract

A sensor includes a mount arranged along a sensor axis, an airfoil body fixed to the mount and having a first face and second face extending along the sensor axis, a heater element, and a temperature probe. The heater element and the temperature probe are positioned within the airfoil body and extend axially along the airfoil body. The airfoil body defines within its interior a pressure channel having an inlet segment extending between the heater element and the first face of the airfoil body to prevent ice formation and/or melt ice entrained within air traversing the pressure channel. Gas turbine engines, methods of removing ice or preventing ice formation, and methods of making sensors are also described.

First claim

What is claimed is:

1. A sensor, comprising:
a mount arranged along a sensor axis;
an airfoil body fixed to the mount, the airfoil body having a first face and second face extending along the sensor axis; and
a heater element positioned within the airfoil body and extending axially through the airfoil body,
wherein the airfoil body defines therein a pressure channel having an inlet segment extending between the heater element and the first face of the airfoil body to prevent ice formation and/or melt ice entrained within air traversing the pressure channel, wherein the pressure channel includes an expansion chamber fluidly coupling the inlet segment to the mount;
wherein the inlet segment of the pressure channel traces an arcuate path between the first face and the second face of the airfoil body.

2. The sensor of claim 1 , wherein the inlet segment of the pressure channel is orthogonal relative to the heater element.

3. The sensor of claim 1 , wherein the airfoil body has a pressure inlet on a leading edge of the airfoil body and in fluid communication with the inlet segment.

4. The sensor of claim 1 , wherein the inlet segment has an inlet segment flow area, wherein the expansion chamber has an expansion chamber flow area, and wherein the expansion chamber flow area is larger than the inlet segment flow area.

5. The sensor of claim 1 , wherein the expansion chamber extends axially between the inlet segment of the pressure channel and the mount.

6. The sensor of claim 1 , wherein the inlet segment is orthogonal relative to the expansion chamber.

7. The sensor of claim 1 , wherein the pressure channel includes an outlet segment fluidly coupling the expansion chamber to the mount.

8. The sensor of claim 7 , wherein the outlet segment has an outlet segment flow area, wherein the expansion chamber has an expansion chamber flow area, and wherein the outlet segment flow area is smaller than the expansion chamber flow area.

9. The sensor of claim 7 , further comprising a pressure conduit extending through the mount and seated within the outlet segment of the pressure channel.

10. A sensor, comprising:
a mount arranged along a sensor axis;
an airfoil body fixed to the mount, the airfoil body having a first face and second face extending along the sensor axis;
a heater element positioned within the airfoil body and extending axially through the airfoil body,
wherein the airfoil body defines therein a pressure channel having an inlet segment extending between the heater element and the first face of the airfoil body to prevent ice formation and/or melt ice entrained within air traversing the pressure channel;
a temperature probe seated within the airfoil body, and wherein the pressure channel includes an expansion chamber extending axially within the airfoil body and chordwise separating the heater element from the temperature probe.

11. The sensor of claim 10 , wherein the temperature probe extends axially along the airfoil body and is electrically connected to the mount.

12. The sensor of claim 10 , wherein the airfoil body defines an insulating cavity at a location chordwise between the expansion chamber and the temperature probe.

13. A gas turbine engine, comprising:
a compressor section with an inlet;
a combustor section in fluid communication with the compressor section;
a turbine section in fluid communication with the combustor section; and
the sensor as recited in claim 1 , wherein the sensor is supported within the compressor section inlet of the gas turbine engine to measure pressure and temperature of air ingested by the compressor section.

14. The gas turbine engine of claim 13 , further comprising a temperature probe seated within the airfoil body, wherein the temperature probe extends axially along the airfoil body and is electrically connected to the mount, wherein the airfoil body defines an insulating cavity at a location chordwise between the expansion chamber and the temperature probe.

15. The gas turbine engine of claim 13 , wherein the expansion chamber has an expansion chamber flow area, pressure channel includes an outlet segment fluidly coupling the expansion chamber to the mount, wherein the outlet segment has an outlet segment flow area, and wherein the outlet segment flow area is smaller than the expansion chamber flow area.

16. A gas turbine engine, comprising:
a compressor section with an inlet;
a combustor section in fluid communication with the compressor section;
a turbine section in fluid communication with the combustor section; and
the sensor as recited in claim 12 , wherein the sensor is supported within the compressor section inlet of the gas turbine engine to measure pressure and temperature of air ingested by the compressor section.

17. The gas turbine engine of claim 16 , wherein the temperature probe extends axially along the airfoil body and is electrically connected to the mount, wherein the airfoil body defines an insulating cavity at a location chordwise between the expansion chamber and the temperature probe.

18. The gas turbine engine of claim 16 , wherein the expansion chamber has an expansion chamber flow area, pressure channel includes an outlet segment fluidly coupling the expansion chamber to the mount, wherein the outlet segment has an outlet segment flow area, and wherein the outlet segment flow area is smaller than the expansion chamber flow area.

Assignees

• Rosemount Aerospace Inc

Inventors

• Holl Andrew
• Wigen Scott
• Sable Robert Edward
• Isebrand Scott D
• Boyd Brian

Classifications

• F01D25/02 Primary

  De-icing means for engines having icing phenomena · CPC title

• F01D21/12

  responsive to temperature · CPC title

• G01K13/02

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

• F01D17/085

  to temperature · CPC title

• F01D21/003

  Arrangements for testing or measuring (for measuring vibrations G01H) · CPC title