Pressure sensor assembly for a turbine engine

1. A gas turbine engine defining a radial direction and a circumferential direction, the gas turbine engine comprising:

a liner positioned within a combustion section or a turbine section of the gas turbine engine and at least partially defining a core air flowpath through the gas turbine engine, the liner defining a liner opening;

a casing at least partially enclosing the liner, the casing defining a first, inner side along the radial direction, a second, outer side opposite the first side, and a casing opening; and

a pressure sensor assembly comprising a body, an extension member, and a pressure sensor that comprises a diaphragm,

wherein the pressure sensor is positioned at least partially within the body and the body positioned at least partially on the second side of the casing,

wherein the extension member extends from the body through the casing opening in the casing and towards the liner opening in the liner,

wherein the extension member defines a continuous sense cavity extending between the sensor and the core air flowpath, exposing the pressure sensor to the core air flowpath,

wherein a radial thickness of a first portion of the casing immediately around the pressure sensor assembly is greater than a thickness of a second portion of the casing at least partially surrounding the first portion in the circumferential direction, and

wherein the diaphragm is positioned closer to an outer surface of the first portion of the casing in the radial direction than an inner surface of the casing to the outer surface of the first portion of the casing.

2. The gas turbine engine of claim 1 ,

wherein the liner is an outer liner of a combustor assembly of the gas turbine engine, and

wherein the casing is a combustor casing.

3. The gas turbine engine of claim 1 ,

wherein the diaphragm is exposed to the sense cavity of the extension member, and

wherein the pressure sensor further comprises piezo-electric material positioned against the diaphragm opposite the sense cavity.

4. The gas turbine engine of claim 1 ,

wherein the diaphragm is exposed to the sense cavity of the extension member, and

wherein the pressure sensor is an optical-based sensor for measuring a deflection of the diaphragm.

5. The gas turbine engine of claim 4 , wherein the optical-based sensor includes an optical laser directed to the diaphragm.

6. The gas turbine engine of claim 1 , wherein the extension member defines one or more cooling holes located inward of the casing along the radial direction and outward of the liner along the radial direction.

7. The gas turbine engine of claim 1 ,

wherein the liner comprises a ferrule, and

wherein the extension member extends into the ferrule.

8. The gas turbine engine of claim 1 , wherein the pressure sensor assembly is removably coupled to the casing.

9. The gas turbine engine of claim 1 ,

wherein the pressure sensor assembly further comprises a clamp nut, and

wherein the clamp nut is removably coupled to the body to hold the sensor in position.

10. The gas turbine engine of claim 1 , further comprising:

a plurality of pressure sensor assemblies arranged along the circumferential direction of the gas turbine engine.

11. The gas turbine engine of claim 1 , wherein the casing opening of the casing and the liner opening of the liner are each configured as part of a borescope inspection port.

12. The gas turbine engine of claim 1 , wherein the extension member is moveably engaged with the liner.

13. The gas turbine engine of claim 1 ,

wherein the liner includes ferrule,

wherein the extension member extends at least partially into the ferrule and is slidably connected to the ferrule.

14. A pressure sensor assembly for a gas turbine engine defining a radial direction and comprising a liner at least partially defining a core air flowpath through a combustion section or a turbine section and a casing at least partially enclosing the liner, the pressure sensor assembly comprising:

a body configured for positioning adjacent to the casing of the gas turbine engine;

a pressure sensor positioned at least partially within the body and comprising a diaphragm; and

an extension member extending from the body and configured to extend at least partially through a casing opening in the casing and towards a liner opening in the liner,

wherein the extension member defines a continuous sense cavity extending between the sensor and the core air flowpath, to expose the pressure sensor to the core air flowpath of the gas turbine engine,

wherein a radial thickness of a first portion of the casing immediately around the pressure sensor assembly is greater than a thickness of a second portion of the casing at least partially surrounding the first portion in the circumferential direction, and

wherein the diaphragm is positioned closer to an outer surface of the first portion of the casing in the radial direction than an inner surface of the casing to the outer surface of the first portion of the casing.

15. The pressure sensor assembly of claim 14 ,

wherein the diaphragm is exposed to the sense cavity of the extension member, and

wherein the pressure sensor further comprises piezo-electric material positioned against the diaphragm opposite the sense cavity.

16. The pressure sensor assembly of claim 14 , wherein the extension member defines one or more cooling holes located inward of the casing along the radial direction and outward of the liner along the radial direction when the pressure sensor assembly is installed in the gas turbine engine.

17. The pressure sensor assembly of claim 14 , wherein the pressure sensor assembly is configured to be removably coupled to the casing.

18. The pressure sensor assembly of claim 14 ,

wherein the pressure sensor assembly further comprises a clamp nut, and

wherein the clamp nut is removably coupled to the body to hold the sensor in position.

19. The pressure sensor assembly of claim 14 ,

wherein the liner is an outer liner of a combustor assembly of the gas turbine engine, and

wherein the casing is a combustor casing.

20. A gas turbine engine defining a radial direction and a circumferential direction, the gas turbine engine comprising:

a liner positioned within a combustion section or a turbine section of the gas turbine engine and at least partially defining a core air flowpath through the gas turbine engine, the liner defining a liner opening;

a casing at least partially enclosing the liner, the casing defining a first, inner side along the radial direction, a second, outer side opposite the first side, and a casing opening; and

a pressure sensor assembly comprising an extension member and a pressure sensor comprising a diaphragm,

wherein the pressure sensor is positioned at least partially on the second side of the casing,

wherein the extension member extends through the casing opening in the casing and towards the liner opening in the liner,

wherein the extension member defines a continuous sense cavity extending between the sensor and the core air flowpath, exposing the pressure sensor to the core air flowpath,

wherein a radial thickness of a first portion of the casing immediately around the pressure sensor assembly is greater than a thickness of a second portion of the casing at least partially surrounding the first portion in the circumferential direction, and

wherein the diaphragm is positioned closer to an outer surface of the first portion of the casing in the radial direction than an inner surface of the casing to the outer surface of the first portion of the casing.