Replaceable rotor blade tip clearance measurement device for a gas turbine engine
A replaceable rotor blade tip clearance measurement device for a gas turbine engine, includes a threaded section along an axis and an integral abradable tip with an internal lattice geometry that extends from the threaded section along the axis.
1. A replaceable rotor blade tip clearance measurement device for a gas turbine engine, consisting of:
a threaded section along an axis, the threaded section having a first end and a second end opposite from the first end along the axis;
an integral abradable tip with an internal lattice geometry that extends from the first end of the threaded section along the axis; and
a bolt head at the second end of the threaded section along the axis.
2. The device as recited in claim 1 , wherein the integral abradable tip is 0.1-1.0 inches in diameter.
3. The device as recited in claim 1 , wherein the integral abradable tip is of a smaller diameter than the threaded section.
4. The device as recited in claim 1 , wherein the internal lattice geometry is of a honeycomb pattern.
5. The device as recited in claim 1 , wherein the internal lattice geometry is of a spiral pattern.
6. The device as recited in claim 1 , wherein the internal lattice geometry is of a multiple circle pattern.
7. The device as recited in claim 1 , wherein the internal lattice geometry is abradeable equivalent to an abradeable surface of a blade outer air seal.
8. The device as recited in claim 1 , wherein the internal lattice geometry is additively manufactured.
9. A gas turbine engine, comprising:
an engine case; and
a replaceable rotor blade tip clearance measurement device accessible from outside the engine case, the replaceable rotor blade tip clearance measurement device consisting of:
a threaded section along an axis;
an integral abradable tip with an internal lattice geometry that extends from the threaded section along the axis; and
a bolt head at an opposite end of the threaded section from the integral abradable tip, wherein the integral abradable tip has an internal lattice geometry that defines a percent open area greater than 90%.
10. The gas turbine engine as recited in claim 9 , wherein the threaded section, the bolt head and the integral abradable tip are aligned along the axis.
11. The gas turbine engine as recited in claim 10 , wherein the integral abradable tip is of a smaller diameter than the threaded section.
12. The gas turbine engine as recited in claim 11 , wherein the internal lattice geometry is one of a honeycomb pattern, a spiral pattern, and a multiple circle pattern.
13. The gas turbine engine as recited in claim 11 , wherein the internal lattice geometry is shaped to define a predefined porosity with respect to a blade.
14. The gas turbine engine as recited in claim 11 , wherein the replaceable rotor blade tip clearance measurement device is additively manufactured.
15. The gas turbine engine as recited in claim 11 , further comprising a multiple of replaceable rotor blade tip clearance measurement devices disposed circumferentially about the engine case.
16. The gas turbine engine as recited in claim 11 , wherein the internal lattice geometry is additively manufactured.
17. The gas turbine engine as recited in claim 9 , wherein the integral abradable tip extends through a blade outer air seal.
18. The gas turbine engine as recited in claim 17 , wherein the integral abradable tip abrades equivalent to the blade outer air seal.
19. The gas turbine engine as recited in claim 9 , further comprising a blade outer air seal and rotor blades rotatably positioned within the blade outer air seal, the blade outer air seal and integral abradable tip being abradable by the rotor blades, wherein abrasion to the integral abradable tip is representative of abrasion to the blade outer air seal.
20. The gas turbine engine as recited in claim 9 , wherein the replaceable rotor blade tip clearance measurement device extends through the engine case.