Pressure and temperature sensors and related methods

Patent metadata

Field	Value
Publication number	US-11655726-B2
Application number	US-202016805486-A
Country	US
Kind code	B2
Filing date	Feb 28, 2020
Priority date	Feb 28, 2020
Publication date	May 23, 2023
Grant date	May 23, 2023

Abstract

A sensor includes an airfoil body, a heater element, and a temperature probe. The airfoil body defines a sensor axis, an insulating cavity, and extends between a leading edge and a trailing edge of the airfoil body. The heater element extends axially within the airfoil body and is positioned between the leading edge and the trailing edge of the airfoil body. The temperature probe extends axially within the airfoil body, is positioned between the heater element and the trailing edge of the airfoil body, and is separated from the heater element by the insulating cavity to limit thermal communication between the temperature probe and the heater element. Gas turbine engines, methods of making sensors, and methods of thermally separating temperature probes and heater elements in sensors are also described.

First claim

What is claimed is:

1. A sensor, comprising:
an airfoil body defining a sensor axis and an insulating cavity, the airfoil body extending between a leading edge and a trailing edge of the airfoil body;
a heater element extending axially within the airfoil body, the heater element positioned between the leading edge and the trailing edge of the airfoil body;
a temperature probe extending axially within the airfoil body and positioned between the heater element and the trailing edge of the airfoil body, wherein the temperature probe is separated from the heater element by the insulating cavity to limit thermal communication between the temperature probe and the heater element;
a pressure inlet disposed at the leading edge; and
an expansion chamber fluidly connected to the pressure inlet via an inlet segment;
wherein the heater element is disposed axially between the pressure inlet and the expansion chamber.

2. The sensor of claim 1 , wherein the airfoil body has a tip surface extending to the trailing edge of the airfoil body.

3. The sensor of claim 2 , wherein the tip surface of the airfoil body defines an insulating cavity inlet that is fluidly coupled to the insulating cavity.

4. The sensor of claim 2 , wherein the airfoil body has a first face extending between the leading edge and the trailing edge of the airfoil body, the first face defining a first face first outlet vent, wherein the first face first outlet vent is fluidly coupled to the insulating cavity.

5. The sensor of claim 2 , wherein the airfoil body has a second face extending between the leading edge and the trailing edge of the airfoil body, the second face defining a second face first outlet vent, wherein the second face first outlet vent is fluidly coupled to the insulating cavity.

6. The sensor of claim 2 , wherein the airfoil body has an ice accretion feature extending between the tip surface and the leading edge of the air foil body, the ice accretion feature axially overlapping the leading edge of the airfoil body.

7. The sensor of claim 1 , wherein the airfoil body defines a temperature sense chamber between the insulating cavity and the trailing edge of the airfoil body, wherein the temperature probe extends into the temperature sense chamber.

8. The sensor of claim 7 , wherein the airfoil body has a tip surface extending to the trailing edge of the airfoil body, the tip surface defining tip surface aperture, and wherein the tip surface aperture is fluidly coupled to the temperature sense chamber.

9. The sensor of claim 7 , wherein the airfoil body has a first face extending between the leading edge and the trailing edge of the airfoil body, the first face defining a first face aperture, wherein the temperature sense chamber is fluidly coupled to the external environment through the first face aperture.

10. The sensor of claim 7 , wherein the airfoil body has a second face extending between the leading edge and the trailing edge of the airfoil body, the second face defining a second face aperture, wherein the temperature sense chamber is fluidly coupled to the external environment through the second face aperture.

11. The sensor of claim 1 , wherein the airfoil body has a tip surface defining therein a scoop feature, the scoop feature axially overlaying the temperature probe and the insulating cavity.

12. The sensor of claim 11 , wherein the airfoil body has an ice accretion feature arranged between the scoop feature and the leading edge of the airfoil body.

13. The sensor of claim 11 , wherein the scoop feature terminates at a tip surface aperture, wherein the tip surface aperture fluidly couples the scoop feature to the temperature probe.

14. The sensor of claim 11 , wherein the scoop feature spans an insulating cavity inlet defined by the tip surface of the airfoil body, and wherein the insulating cavity inlet fluidly couples the scoop feature to the insulating cavity.

15. A gas turbine engine, comprising:
a compressor section with a compressor inlet;
a combustor section in fluid communication with the compressor section;
a turbine section in fluid communication with the combustor section; and
a sensor as recited in claim 1 , wherein the sensor is a P2T2 sensor supported within the compressor inlet of the gas turbine engine.

16. The gas turbine engine of claim 15 , wherein the airfoil body has a tip surface extending to the trailing edge of the airfoil body; and wherein the airfoil body defines a temperature sense chamber between the insulating cavity and the trailing edge of the airfoil body, wherein the temperature probe extends into the temperature sense chamber.

17. The gas turbine engine of claim 15 , wherein the airfoil body defines a temperature sense chamber between the insulating cavity and the trailing edge of the airfoil body, wherein the temperature probe extends into the temperature sense chamber; and wherein the airfoil body has a tip surface defining therein a scoop feature, the scoop feature axially overlaying the temperature probe and the insulating cavity.

18. The gas turbine engine of claim 15 , wherein the airfoil body has a tip surface defining therein a scoop feature, the scoop feature axially overlaying the temperature probe and the insulating cavity; and wherein the tip surface extends to the trailing edge of the airfoil body.

19. A method of making a sensor, comprising:
forming an airfoil body defining a sensor axis and an insulating cavity, the airfoil body extending between a leading edge and a trailing edge of the airfoil body, using an additive manufacturing technique;
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 insulating cavity and the trailing edge of the airfoil body;
wherein forming the airfoil with the additive manufacturing technique includes defining the insulating cavity 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;
wherein the airfoil body includes:
a pressure inlet disposed at the leading edge; and
an expansion chamber fluidly connected to the pressure inlet via an inlet segment;

wherein the heater element is disposed axially between the pressure inlet and the expansion chamber.

20. A method thermally separating a temperature probe from a heater element, comprising:
at a sensor including an airfoil body defining a sensor axis, an insulating cavity, and extending between a leading edge and a trailing edge of the airfoil body; the heater element extending axially within the airfoil body and positioned between the leading edge and the trailing edge of the airfoil body; and the temperature probe extending axially within the airfoil body and positioned between the heater element and the trailing edge of the airfoil body, the temperature probe separated from the heater element by the insulating cavity,
heating the leading edge of the airfoil body with the heater element;
thermally separating the temperature probe from the heater element by flowing fluid from the environment external to the sensor through the insulating cavity;
flowing further fluid from the environment external to the sensor acros

Assignees

• Rosemount Aerospace Inc

Inventors

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

Classifications

• G01L19/0654

  against moisture or humidity · CPC title

• G01K13/028 Primary

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

• F05D2270/80

  Devices generating input signals, e.g. transducers, sensors, cameras or strain gauges · CPC title

• G01L19/0092

  Pressure sensor associated with other sensors, e.g. for measuring acceleration or temperature (G01L9/025, G01L9/045, G01L9/065, G01L9/085, G01L9/105, G01L9/125, G01L19/02, G01L19/04 take precedence; measuring two or more variable G01D21/02; temperature sensors with pressure compensation G01K1/26) · CPC title

• F05D2270/303

  Temperature · CPC title