Compressor abradable material seal with tailored wear ratio and desirable erosion resistance

1. A wear resistant seal system, adapted for resisting wear of a rotating part in a gas turbine engine as it rotates against a stationary part in the engine, the system comprising:

an axially rotable member including an abrasive tip having a first tensile strength; and

a stationary structure radially exterior and adjacent to the rotable member, the stationary structure including an abradable material that includes:

a matrix material having a second tensile strength that, at least in a first temperature range, is lower than the first tensile strength, wherein the matrix material includes at least one of Cu5Al, Cu 8 Al 1 Fe or Cu 38 Ni; and

a filler material interspersed with the matrix material.

2. The wear resistant seal of claim 1 , wherein the rotating member is a blade and the stationary member is a blade housing.

3. The wear resistant seal of claim 1 , wherein the matrix material has a single phase up to an onset of melting.

4. The wear resistant seal of claim 1 , wherein a first melting point of the matrix material is lower than a second melting point of the abrasive tip.

5. The wear resistant seal of claim 1 , wherein a first yield strength of the matrix material is at least 25 percent lower than a second yield strength of the abrasive tip.

6. The wear resistant seal of claim 1 , wherein, in response to an interaction between the abradable material and the abrasive tip, at least 90 percent of volumetric loss is attributed to the abradable material.

7. The wear resistant seal of claim 1 , wherein the matrix material has a third tensile strength that, in a second temperature range, is lower than the first tensile strength.

8. The wear resistant seal of claim 1 , wherein the filler material is structurally weaker than the matrix material.

9. The wear resistant seal system of claim 1 , wherein a first yield strength of the matrix material is at least 25 percent lower than a second yield strength of the abrasive tip.

10. A wear resistant seal system, adapted for resisting wear of a rotating part in a gas turbine engine as it rotates against a stationary part in the engine, the system comprising:

an airfoil configured to rotate about an axis in a compressor or a turbine of the gas turbine engine;

an abrasive tip positioned on the airfoil and having a first tensile strength; and

a stationary structure radially exterior and adjacent to the airfoil, the stationary structure including an abradable material that includes:

a matrix material having a second tensile strength that, at least in a first temperature range, is lower than the first tensile strength, wherein the matrix material includes at least one of Cu 5 Al, Cu 8 Al 1 Fe, or Cu 38 Ni, and

a filler material interspersed with the matrix material.

11. The wear resistant seal system of claim 10 , wherein the second tensile strength is lower than the first tensile strength between −40 degrees Fahrenheit and 1,922 degrees Fahrenheit.

12. The wear resistant seal system of claim 10 , wherein the matrix material has a single phase up to an onset of melting.

13. A wear resistant seal system, adapted for resisting wear of a rotating part in a gas turbine engine as it rotates against a stationary part in the engine, the system comprising:

an axially rotable member having an abrasive tip comprising a composition that by weight contains between 17% and 21% chromium, between 2.8% and 3.3% molybdenum, between 50% to 55% nickel, and between 4.75% and 5.5% niobium; and

a stationary structure radially exterior and adjacent to the rotable member, the stationary structure including an abradable material that includes a matrix material comprising Cu 5 Al, Cu 8 Al 1 Fe, or Cu 38 Ni.