Pressure and temperature sensors and methods of controlling ice accretion on pressure and temperature sensors

Patent metadata

Field	Value
Publication number	US-12209505-B2
Application number	US-202318455193-A
Country	US
Kind code	B2
Filing date	Aug 24, 2023
Priority date	Feb 28, 2020
Publication date	Jan 28, 2025
Grant date	Jan 28, 2025

Abstract

A sensor includes an airfoil body, a heater element, and a temperature probe. The airfoil body defines a sensor axis and having a leading edge, a trailing edge, and an ice accretion feature. The heater element extends axially through the airfoil body between the leading edge and the trailing edge of the airfoil body. The temperature probe extends axially through the airfoil body between the heater element and the trailing edge of the airfoil body. The heater element is axially overlapped by the ice accretion feature to accrete ice chordwise forward of a tip surface aperture. Gas turbine engines, methods of making sensors, and methods of accreting ice on sensors are also described.

First claim

What is claimed is:

1. A method of making a sensor, comprising:
forming, using an additive manufacturing technique, an airfoil body defining a sensor axis and having a leading edge, a trailing edge, an ice accretion feature and a tip surface extending from the ice accretion feature to the trailing edge;
wherein forming the airfoil with the additive manufacturing technique includes defining a heater element seat extending axially through the airfoil body between the leading edge and the trailing edge of the airfoil body;
wherein forming the airfoil body with the additive manufacturing technique includes defining a temperature probe seat extending axially through the airfoil body between the heater element seat and the trailing edge of the airfoil body such that the ice accretion feature axially overlaps the heater element seat;
wherein forming the airfold body with the additive manufacturing technique includes forming the ice accretion feature such that the ice accretion feature extends from the leading edge of the airfoil body to an ice accretion feature terminus that is located chordwise between the heater element seat and the temperature probe seat;
positioning a heater element within the heater element seat; and
positioning a temperature probe within the temperature probe seat.

2. The method of claim 1 , wherein the airfoil body is formed such that the airfoil body has a first face and a second face defining therebetween an airfoil width, and wherein the ice accretion feature has an ice accretion feature width that is smaller than the airfoil width.

3. The method of claim 1 , wherein the airfoil body is formed such that the airfoil body defines therethrough an insulating cavity extending axially through the airfoil body between the temperature probe and the heater element.

4. The method of claim 3 , wherein the airfoil body is formed such that the airfoil body has a first face defining a first face outlet vent, the first face outlet vent in fluid communication with the insulating cavity.

5. The method of claim 4 , wherein the airfoil body is formed such that the airfoil body has a second face defining a second face outlet vent, the second face outlet vent in fluid communication with the insulating cavity and in registration with the first face outlet vent.

6. The method of claim 1 , wherein the airfoil body is formed such that the airfoil body has a tip surface extending from the ice accretion feature to the trailing edge of the airfoil body, the tip surface defining an insulating cavity inlet that is located chordwise between the ice accretion feature and the temperature probe.

7. The method of claim 6 , wherein the airfoil body is formed such that the airfoil body has a first face with a first face outlet vent and defines therethrough an insulating cavity, the insulating cavity fluidly coupling the insulating cavity inlet with the first face outlet vent.

8. The method of claim 7 , wherein the airfoil body is formed such that the airfoil body has a second face with a second face outlet vent, wherein the insulating cavity inlet is fluidly coupled to the second face outlet vent by the insulating cavity.

9. The method of claim 1 , wherein the airfoil body is formed such that the airfoil body defines a temperature sense chamber that is located chordwise between the trailing edge of the airfoil body and the heater element, wherein the temperature probe extends at least partially through the temperature sense chamber.

10. The method of the claim 9 , wherein the airfoil body is formed such that the airfoil body has a first face extending between the leading edge and the trailing edge of the airfoil body, the first face defining therethrough a first face aperture, wherein the temperature sense chamber is fluidly coupled to an environment external to the airfoil body by the first face aperture.

11. The method of claim 10 , wherein the airfoil body is formed such that the airfoil body has a second face extending between the leading edge and the trailing edge of the airfoil body, the second face defining therethrough a second face aperture, wherein the second face aperture is in registration with the first face aperture.

12. The method of claim 11 , wherein the temperature sense chamber is fluidly coupled to the environment external to the airfoil body by the second face aperture.

13. The method of claim 1 , wherein the sensor is a P2T2 sensor or a P25T25 sensor fixed to a gas turbine engine.

14. A method of making a sensor, comprising:
forming, using an additive manufacturing technique, an airfoil body defining a sensor axis and having a leading edge, a trailing edge, an ice accretion feature and a tip surface extending from the ice accretion feature to the trailing edge;
wherein forming the airfoil with the additive manufacturing technique includes defining a heater element seat extending axially through the airfoil body between the leading edge and the trailing edge of the airfoil body;
wherein forming the airfoil body with the additive manufacturing technique includes defining a temperature probe seat extending axially through the airfoil body between the heater element seat and the trailing edge of the airfoil body such that the ice accretion feature axially overlaps the heater element seat;
wherein forming the airfoil body with the additive manufacturing technique includes forming the ice accretion feature such that the airfoil body includes a fin body extending from the leading edge to an ice accretion feature terminus that is located chordwise between the heater element seat and the temperature probe seat;
positioning a heater element within the heater element seat; and
positioning a temperature probe within the temperature probe seat.

15. A method of making a sensor, comprising:
forming, using an additive manufacturing technique, an airfoil body defining a sensor axis and having a leading edge, a trailing edge, an ice accretion feature and a tip surface extending from the ice accretion feature to the trailing edge;
wherein forming the airfoil with the additive manufacturing technique includes defining a heater element seat extending axially through the airfoil body between the leading edge and the trailing edge of the airfoil body;
wherein forming the airfoil body with the additive manufacturing technique includes defining a temperature probe seat extending axially through the airfoil body between the heater element seat and the trailing edge of the airfoil body such that the ice accretion feature axially overlaps the heater element seat;
positioning a heater element within the heater element seat; and
positioning a temperature probe within the temperature probe seat;
wherein the airfoil body has a first face and a second face defining therebetween an airfoil width, and wherein the ice accretion feature has an ice accretion feature width that is greater than the airfoil width.

Assignees

• Rosemount Aerospace Inc

Inventors

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

Classifications

• G01K13/028 Primary

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

• G01K13/02

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

• G01K1/20

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

• G01K1/08

  Protective devices, e.g. casings · CPC title

• F05D2220/323

  for aircraft propulsion, e.g. jet engines · CPC title