Turbine abradable layer with inclined angle surface ridge or groove pattern

1. A turbine engine ring segment abradable component, adapted for coupling to an interior circumference of a turbine casing in opposed orientation with a rotating turbine blade tip circumferential swept path, the component comprising:

a support surface adapted for coupling to a turbine casing inner circumference that circumscribes a turbine blade rotational axis;

an abradable substrate coupled to the support surface, having a substrate surface; and

a plurality of ridges projecting from the substrate surface in a radial direction and defining grooves therebetween, each ridge of the plurality of ridges respectively having an opposed pair of first and second lateral walls, the plurality of ridges comprising a stepped rib profile comprising a first step defined between the first and second lateral walls and terminating in a first ridge tip surface, the first step defining a lower wear zone between the first ridge tip surface and the substrate surface, the plurality of ridges further comprising a second step terminating in a second ridge tip surface defining an upper wear zone between the second ridge tip surface and the first step, the plurality of ridges configured for orientation in opposed spaced relationship with a rotating turbine blade tip, so as to form a blade tip gap therebetween;

wherein the first lateral wall faces upstream of and is inclined opposite an opposed turbine blade rotational direction, for resisting blade tip airflow leakage from a turbine blade higher pressure side to a lower pressure side through a blade tip gap by redirecting at least some of the leakage opposite the blade rotational direction;

wherein the first lateral sidewall comprises an inflected compound angle profile extending in the radial direction having a lowermost portion in the radial direction which is inclined in the blade rotational direction and extends inward into a body of the ridge and an uppermost portion in the radial direction which is inclined opposite the blade rotational direction and extends away from the lowermost portion and the body of the ridge; and

wherein either or both of the first ridge tip surface and the second ridge tip surface is inclined for varying blade tip gap between the first and second lateral walls dissipating leakage flow energy.

2. The component of claim 1 , the second lateral wall intersecting a base of an adjoining groove of the grooves for redirecting airflow leakage in the groove toward the first lateral wall of a next downstream ridge of the plurality of ridges defining the adjoining groove.

3. The component of claim 1 , further comprising an inclined groove base between successive pairs of ridges of the plurality of ridges that define one of the grooves for redirecting airflow leakage into the one of the grooves and away from the blade tip gap.

4. A turbine engine, comprising:

a turbine casing having an inner circumference;

a rotor having blades rotatively mounted in the turbine casing inner circumference, distal tips of which forming a blade tip circumferential swept path in the blade rotation direction, the blade tips having a rotational direction, a lower pressure side downstream of the blade rotational direction and a higher pressure side upstream of the blade rotational direction; and

an abradable component having:

a support surface adapted for coupling to the turbine casing inner circumference that circumscribes the turbine blade rotational axis;

an abradable substrate coupled to the support surface, having a substrate surface; and

a plurality of ridges projecting from the substrate surface in a radial direction and defining grooves therebetween, each ridge of the plurality of ridges respectively having an opposed pair of first and second lateral walls, the plurality of ridges comprising a stepped rib profile comprising a first step defined between the first and second lateral walls and terminating in a first ridge tip surface, the first step defining a lower wear zone between the first ridge tip surface and the substrate surface, the plurality of ridges further comprising a second step terminating in a second ridge tip surface defining an upper wear zone between the second ridge tip surface and the first step, the plurality of ridges configured for orientation in opposed spaced relationship with the rotating turbine blade tips, so as to form a blade tip gap therebetween;

wherein the first lateral wall faces upstream of and is inclined opposite the turbine blade rotational direction, for resisting blade tip airflow leakage from the turbine blade higher pressure side to the lower pressure side through the blade tip gap by redirecting at least some of the leakage opposite the blade rotational direction;

wherein the first lateral sidewall comprises an inflected compound angle profile extending in the radial direction having a lowermost portion in the radial direction which is inclined in the blade rotational direction and extends inward into a body of the ridge and an uppermost portion in the radial direction which is inclined opposite the blade rotational direction and extends away from the lowermost portion and the body of the ridge; and

wherein either or both of the first ridge tip surface and the second ridge tip surface is inclined for varying blade tip gap between the first and second lateral walls dissipating leakage flow energy.

5. A method for reducing turbine engine blade tip wear, comprising:

providing a turbine engine that includes a turbine casing having an inner circumference, a rotor having blades rotatively mounted in the turbine casing, distal tips of which forming a blade tip circumferential swept path in the blade rotation direction;

inserting a generally arcuate shaped abradable component in the turbine casing inner circumference in opposed, spaced relationship with a plurality of blade tips, defining a blade gap there between, the abradable component having:

a support surface adapted for coupling to the turbine casing inner circumference that circumscribes the turbine blade rotational axis;

an abradable substrate coupled to the support surface, having a substrate surface; and

a plurality of ridges projecting from the substrate surface in a radial direction and defining grooves therebetween, each ridge of the plurality of ridges respectively having an opposed pair of first and second lateral walls, the plurality of ridges comprising a stepped rib profile comprising a first step defined between the first and second lateral walls and terminating in a first ridge tip surface, the first step defining a lower wear zone between the first ridge tip surface and the substrate surface, the plurality of ridges further comprising a second step terminating in a second ridge tip surface defining an upper wear zone between the second ridge tip surface and the first step, the plurality of ridges configured for orientation in opposed spaced relationship with a rotating turbine blade tip of the blade tips so as to form a blade tip gap therebetween, wherein the either or both of the first ridge tip surface and the second ridge tip surface is inclined for varying blade tip gap between the first and second lateral walls dissipating leakage flow energy;

the first lateral wall facing upstream of and inclined opposite the turbine blade rotational direction;

operating the turbine engine, so that any contact between the blade tips and the abradable surface initially abrades the second lateral ridge tip surface prior to the first lateral ridge tip surface; and

redirecting at least some blade tip airflow leakage opposite the blade rotational direction with the first lateral wall, wherein the first lateral sidewall comprises an inflected compound angle profile extending in the radial direction having a lowermost portion in the radial direction which is inclined in the blade rotational direction and extends inward into a body of the ridge and an uppermost portion in the radial direction which is inclined opposite the blade rotational direction and extends away from the lowermost portion and the body of the ridge.