Turbine assembly with clearance sensor having integrated internal cooling

Patent metadata

Field	Value
Publication number	US-12104492-B1
Application number	US-202318372438-A
Country	US
Kind code	B1
Filing date	Sep 25, 2023
Priority date	Sep 25, 2023
Publication date	Oct 1, 2024
Grant date	Oct 1, 2024

Abstract

A turbine assembly includes a bladed rotor mounted for rotation about an axis of the gas turbine engine, a case assembly, and an internally-cooled tip clearance system. The internally-cooled tip clearance system includes a sensor is configured to monitor a tip clearance formed between the bladed rotor and the case assembly during operation of the gas turbine engine.

First claim

What is claimed is:

1. A turbine assembly adapted for use in a gas turbine engine, the turbine assembly comprising
a bladed rotor mounted for rotation about an axis of the gas turbine engine,
an inner case that extends circumferentially around the bladed rotor to define an outer boundary of a gas path of the turbine assembly to block combustion products from moving through the gas path of the turbine assembly without interaction with blades on the bladed rotor, and
a tip clearance system including a tip clearance sensor located radially outward of the inner case to engage the inner case radially outward of the gas path of the turbine assembly and configured to monitor a tip clearance formed between the bladed rotor and the inner case during operation of the gas turbine engine,
wherein the tip clearance sensor includes sensor components and a sensor housing shaped to define an inner chamber that receives the sensor components and a cooling passageway that extends around the inner chamber so that a portion of the cooling passageway is located radially between the sensor components and the inner case to create a gap radially between the sensor components and the inner case that provides thermal insulation between the sensor components and the inner case and conducts a flow of cooling air at a temperature lower than a temperature of the combustion products through the sensor housing to transfer heat from the tip clearance sensor to the flow of cooling air so as to cool the tip clearance sensor during operation of the gas turbine engine.

2. The turbine assembly of claim 1 , wherein the internally-cooled tip clearance system further includes a cooling air source in fluid communication with the cooling passageway formed in the tip clearance sensor to supply the flow of cooling air to the cooling passageway.

3. The turbine assembly of claim 2 , wherein the sensor housing further includes a plurality of protrusions that extend into the cooling passageway and configured to induce turbulence in the flow of cooling air supplied to the cooling passageway during operation of the gas turbine engine such that heat is more effectively transferred from the tip clearance sensor to the flow of cooling air.

4. The turbine assembly of claim 3 , wherein the cooling passageway has an inlet radial section that extends radially inward toward the inner case from an inlet opening, an interconnecting section that extends axially from the inlet radial section, and an outlet radially section that extends radially outward from the interconnecting section to an outlet opening, the interconnecting section of the cooling passageway defines the portion of the cooling passageway located radially between the sensor components and the inner case to create the gap between the sensor components and the inner case, and the plurality of protrusions are located in one of the inlet radial section, the interconnecting section, and the outlet radially section of the cooling passageway.

5. The turbine assembly of claim 4 , wherein the plurality of protrusions are only located in the interconnecting section of the cooling passageway formed in the sensor housing.

6. The turbine assembly of claim 4 , wherein the plurality of protrusions are located in the inlet radial section, the interconnecting section, and the outlet radially section of the cooling passageway formed in the sensor housing.

7. The turbine assembly of claim 1 , wherein the sensor housing of the tip clearance sensor defines a radially-inwardly facing surface that directly engages a radially-outwardly facing surface of the inner case.

8. The turbine assembly of claim 7 , wherein the cooling passageway has an inlet radial section that extends radially inward toward the inner case from an inlet opening, a interconnecting section that extends axially from the inlet radial section, and an outlet radially section that extends radially outward from the interconnecting section to an outlet opening, the interconnecting section of the cooling passageway defines the portion of the cooling passageway located radially between the sensor components and the inner case to create the gap between the sensor components and the inner case.

9. The turbine assembly of claim 7 , wherein the sensor housing includes a thermal barrier coating layer that defines the radially-inwardly facing surface of the sensor housing.

10. The turbine assembly of claim 1 , further comprising an outer case that extends circumferentially around the inner case and is spaced radially outward of the inner case to define an annular plenum therebetween, and wherein the cooling passageway is not in fluid communication with the annular plenum.

11. A gas turbine engine comprising
a compressor configured to compress air drawn in to the gas turbine engine and discharge pressurized air,
a combustor configured to mix fuel with the pressurized air from the compressor and ignites the fuel to produce hot, high pressure combustion products,
a turbine assembly configured to receive the combustion products and to extract mechanical work form the combustion products as the combustion products move through the turbine assembly, the turbine assembly including
a bladed rotor mounted for rotation about an axis of the gas turbine engine,
an inner case that extends circumferentially around the bladed rotor, and
a tip clearance system including a tip clearance sensor located radially outward of the inner case to engage the inner case and configured to monitor a tip clearance formed between the bladed rotor and the inner case during operation of the gas turbine engine and a cooling air source in fluid communication with a cooling passageway formed in the tip clearance sensor to supply a flow of cooling air to the cooling passageway to transfer heat from the tip clearance sensor to the flow of cooling air,

wherein the tip clearance sensor includes a sensor housing shaped to define an inner chamber and the cooling passageway that extends around the inner chamber and sensor components located in the inner chamber so that a portion of the cooling passageway is located radially between the sensor components and the inner case to create a gap between the sensor components and the inner case.

12. The gas turbine engine of claim 11 , wherein the sensor housing further includes a plurality of protrusions that extend into the cooling passageway and configured to induce turbulence in the flow of cooling air supplied to the cooling passageway during operation of the gas turbine engine such that heat is more effectively transferred from the tip clearance sensor to the flow of cooling air.

13. The gas turbine engine of claim 12 , wherein the cooling passageway has an inlet radial section that extends radially inward toward the inner case from an inlet opening, an interconnecting section that extends axially from the inlet radial section, and an outlet radially section that extends radially outward from the interconnecting section to an outlet opening, the interconnecting section of the cooling passageway defines the portion of the cooling passageway located radially between the sensor components and the inner case to create the gap between the sensor components and the inner case, and the plurality of protrusions are located in one of the inlet radial section, the interconnecting section, and the outlet radially section of the cooling passageway.

14. The gas turbine engine of claim 13 , wherein the plurality of protrusions are only located in the interconnecting section of the cooling passageway formed in the sensor housing.

15. The gas turbine engine of claim 13 , wherein the plurality of

Assignees

• Rolls Royce Nam Tech Inc

Inventors

• Hartnagel Brett
• Snyder Brandon R

Classifications

• F01D17/02

  Arrangement of sensing elements · CPC title

• F01D11/24 Primary

  by selectively cooling-heating stator or rotor components · CPC title

• G01B21/16 Primary

  for measuring distance of clearance between spaced objects · CPC title

• F05D2220/32

  in gas turbines · CPC title

• F05D2260/20

  Heat transfer, e.g. cooling · CPC title