Blade with wearable tip-rub-portions above squealer pocket

1. A blade for a gas turbine engine, comprising:

a blade root;

a blade body that extends radially from the blade root to a blade tip, the blade body having a pressure side and a suction side each extending from a leading edge of the blade body to a trailing edge of the blade body;

a squealer pocket located in the blade tip;

a first wearable tip-rub-portion located radially at the blade tip, radially above the squealer pocket, and extending between the pressure side and the suction side, the first wearable tip-rub-portion terminating at a first wearable tip-rub-portion distal end that is located radially at the blade tip;

a second wearable tip-rub-portion located radially at the blade tip, radially above the squealer pocket, and extending between the suction side and the pressure side, the second wearable tip-rub-portion terminating at a second wearable tip-rub-portion distal end that is located radially at the blade tip,

wherein:

the first and second wearable tip-rub-portion distal ends are spaced from each other to define a wearable tip-rub-portion opening that is located radially at the blade tip and in fluid communication with the squealer pocket; and

the first and second wearable tip-rub-portions are continuous with each other about the leading and trailing edges of the blade body;

a core passage defined within the blade body;

a first metering tip-portion located radially between the squealer pocket and the core passage, and extending between the pressure side and the suction side, the first metering tip-portion terminating at a first metering tip-portion distal end; and

a second metering tip-portion located radially between the squealer pocket and the core passage, and extending between the suction side and the pressure side, the second metering tip-portion terminating at a second metering tip-portion distal end,

wherein the first and second metering tip-portion distal ends are spaced from each other to define a metering tip-portion opening that is in fluid communication with the squealer pocket, so that the core passage is in fluid communication with the wearable tip-rub-portion opening; and

wherein:

the first and second metering tip-portions are continuous with each other about the leading and trailing edges of the blade body, and

the first and second wearable tip-rub-portions and the first and second metering tip-portions have a same shape, so that the tip-rub-portion opening and the metering tip-portion opening have a same shape.

2. The blade of claim 1 , wherein

the first and second wearable tip-rub-portions have a first radial thickness and the first and second metering tip-portions have a second radial thickness that is greater than the first radial thickness.

3. The blade of claim 2 , wherein

the squealer pocket has a first radial height that is greater than the second radial thickness.

4. The blade of claim 3 , wherein

the wearable tip-rub-portion opening has a first axial span and the metering tip-portion opening has a second axial span that is the same as the first axial span.

5. The blade of claim 4 , wherein

the squealer pocket has a third axial span that is greater than the first axial span.

6. The blade of claim 1 , wherein

the blade is a turbine blade.

7. A gas turbine engine, comprising:

a blade that includes:

a blade root;

a blade body that extends radially from the blade root to a blade tip, the blade body having a pressure side and a suction side each extending from a leading edge of the blade body to a trailing edge of the blade body;

a squealer pocket located in the blade tip; and

a first wearable tip-rub-portion located radially at the blade tip, radially above the squealer pocket, and extending between the pressure side and the suction side, the first wearable tip-rub-portion terminating at a first wearable tip-rub-portion distal end that is located radially at the blade tip;

a second wearable tip-rub-portion located radially at the blade tip, radially above the squealer pocket, and extending between the suction side and the pressure side, the second wearable tip-rub-portion terminating at a second wearable tip-rub-portion distal end that is located radially at the blade tip,

wherein:

the first and second wearable tip-rub-portion distal ends are spaced from each other to define a wearable tip-rub-portion opening that is located radially at the blade tip and in fluid communication with the squealer pocket; and

the first and second wearable tip-rub-portions are continuous with each other about the leading and trailing edges of the blade body;

a core passage defined within the blade body;

a first metering tip-portion located radially between the squealer pocket and the core passage, and extending between the pressure side and the suction side, the first metering tip-portion terminating at a first metering tip-portion distal end; and

a second metering tip-portion located radially between the squealer pocket and the core passage, and extending between the suction side and the pressure side, the second metering tip-portion terminating at a second metering tip-portion distal end,

wherein the first and second metering tip-portion distal ends are spaced from each other to define a metering tip-portion opening that is in fluid communication with the squealer pocket, so that the core passage is in fluid communications with the wearable tip-rub-portion opening; and

wherein:

the first and second metering tip-portions are continuous with each other about the leading and trailing edges of the blade body, and

the first and second wearable tip-rub-portions and the first and second metering tip-portions have a same shape, so that the tip-rub-portion opening and the metering tip-portion opening have a same shape.

8. The gas turbine engine of claim 7 , wherein

the first and second wearable tip-rub-portions have a first radial thickness and the first and second metering tip-portions have a second radial thickness that is greater than the first radial thickness.

9. The gas turbine engine of claim 8 , wherein

the squealer pocket has a first radial height that is greater than the second radial thickness.

10. The gas turbine engine of claim 9 , wherein

the wearable tip-rub-portion opening has a first axial span and the metering tip-portion opening has a second axial span that is the same as the first axial span.

11. The gas turbine engine of claim 10 , wherein

the squealer pocket has a third axial span that is greater than the first axial span.

12. The gas turbine engine of claim 7 , further comprising

a turbine section, wherein the blade is turbine blade operationally connected to the turbine section.

13. A method of shaping a blade outer air seal of a gas turbine engine which includes a blade,

wherein the blade includes:

a blade root;

a blade body that extends radially from the blade root to a blade tip, the blade body having a pressure side and a suction side each extending from a leading edge of the blade body to a trailing edge of the blade body;

a squealer pocket located in the blade tip;

a first wearable tip-rub-portion located radially at the blade tip, radially above the squealer pocket, and extending between the pressure side and the suction side, the first wearable tip-rub-portion terminating at a first wearable tip-rub-portion distal end that is located radially at the blade tip;

a second wearable tip-rub-portion located radially at the blade tip, radially above the squealer pocket, and extending between the suction side and the pressure side, the second wearable tip-rub-portion terminating at a second wearable tip-rub-portion distal end that is located radially at the blade tip,

wherein:

the first and second wearable tip-rub-portion distal ends are spaced from each other to define a wearable tip-rub-portion opening that is located radially at the blade tip and in fluid communication with the squealer pocket; and

the first and second wearable tip-rub-portions are continuous with each other about the leading and trailing edges of the blade body;

a core passage defined within the blade body;

a first metering tip-portion located radially between the squealer pocket and the core passage, and extending between the pressure side and the suction side, the first metering tip-portion terminating at a first metering tip-portion distal end; and

a second metering tip-portion located radially between the squealer pocket and the core passage, and extending between the suction side and the pressure side, the second metering tip-portion terminating at a second metering tip-portion distal end,

wherein the first and second metering tip-portion distal ends are spaced from each other to define a metering tip-portion opening that is in fluid communication with the squealer pocket, so that the core passage is in fluid communication with the wearable tip-rub-portion opening; and

wherein:

the first and second metering tip-portions are continuous with each other about the leading and trailing edges of the blade body, and

the first and second wearable tip-rub-portions and the first and second metering tip-portions have a same shape, so that the tip-rub-portion opening and the metering tip-portion opening have a same shape,

the method comprising:

driving the blade about an engine center axis; and

rubbing, from the driving, the first wearable tip-rub-portion of the blade that is located radially above the squealer pocket against the blade outer air seal to shape the blade outer air seal.

14. The method of claim 13 , further comprising

rubbing away, from the driving, the first wearable tip-rub-portion to expose the squealer pocket.