Turbine abradable layer with zig zag groove pattern
Turbine and compressor casing abradable component embodiments for turbine engines, with zig-zag pattern abradable surface ridges and grooves. Some embodiments include distinct forward upstream and aft downstream composite multi orientation groove and vertically projecting ridges planform patterns, to reduce, redirect and/or block blade tip airflow leakage downstream into the grooves rather than from turbine blade airfoil high to low pressure sides. Ridge or rib embodiments have first lower and second upper wear zones. The lower zone optimizes engine airflow characteristics while the upper zone is optimized to minimize blade tip gap and wear by being more easily abradable than the lower zone.
1. A turbine abradable component, comprising:
a support surface for coupling to a turbine casing; and
an abradable substrate coupled to the support surface, having a blade-facing abradable surface with a single and continuous zig zag groove formed thereon in a two-dimensional planform pattern that is oriented on the entire surface axially in gas flow and longitudinally in blade rotational directions.
2. A turbine abradable component, comprising:
a support surface for coupling to a turbine casing; and
an abradable substrate coupled to the support surface, having a blade-facing abradable surface with a two-dimensional and continuous pattern corresponding to a single zig-zag groove formed thereon that is oriented on the entire surface axially in gas flow and longitudinally in blade rotational directions.
3. The component of claim 2 , the pattern cut in the abradable surface.
4. The component of claim 2 , the pattern defined by a pair of spaced ridges formed on the abradable surface.
5. The component of claim 2 , the pattern comprising a series of parallel first portions extending diagonally across the abradable substrate surface, joined sequentially at alternate opposing ends by shorter longitudinally oriented groove segments.
6. The component of claim 2 , the pattern comprising a series of parallel first portions extending diagonally across the abradable substrate surface at an angle of 15 degrees plus or minus a corresponding turbine blade trailing edge angle, joined sequentially at alternate opposing ends by shorter longitudinally oriented groove segments.
7. The component of claim 2 , the pattern comprising a series of vee-shaped first portions, with apexes aligned vertically in the blade rotational direction and between one-third and one-half of axial width of the substrate surface.
8. The component of claim 7 , the apexes aligned axially between a leading edge and a mid-chord of a corresponding turbine blade airfoil at a cutoff point where an axially aligned line on the abradable surface is tangent to a pressure surface of the airfoil.
9. The component of claim 8 , a forward portion of the vee forward of the apex aligned at an angle approximating a leading edge angle of the airfoil and an aft portion of the vee aft of the apex is aligned at an angle of 15 degrees plus or minus a trailing edge angle of the airfoil.
10. The component of claim 2 , comprising the pattern corresponding to a dual depth groove defining upper and lower groove heights, with the upper groove establishing an upper wear zone and the lower groove establishing a lower wear zone having greater turbine blade abrasion properties.
11. A turbine abradable component, comprising:
a support surface for coupling to a turbine casing; and
an abradable substrate coupled to the support surface, having a blade-facing abradable surface with a two-dimensional and continuous pattern corresponding to a zig-zag groove formed thereon that is oriented on the entire surface axially in gas flow and longitudinally in blade rotational directions, the pattern having a series of parallel first portions extending axially across the abradable substrate surface, joined sequentially at alternate opposing ends by shorter longitudinally oriented groove segments.
12. A turbine engine, comprising:
a turbine casing;
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 and axially with respect to the turbine casing; and
an abradable component having:
a support surface for coupling to the turbine casing; and
an abradable substrate coupled to the support surface, having a blade-facing abradable surface with a two-dimensional and continuous pattern corresponding to a single zig-zag groove formed thereon that is oriented on the entire surface axially in gas flow and longitudinally in blade rotational directions.
13. The engine of claim 12 , the pattern cut in the abradable surface.
14. The engine of claim 12 , the pattern comprising a series of parallel first portions extending diagonally across the abradable surface, joined sequentially at alternate opposing ends by shorter longitudinally oriented groove segments.
15. The engine of claim 12 , the pattern comprising a series of parallel first portions extending diagonally across the abradable substrate surface at an angle of 15 degrees plus or minus a corresponding turbine blade trailing edge angle, joined sequentially at alternate opposing ends by shorter longitudinally oriented groove segments.
16. The engine of claim 12 , the pattern comprising a series of vee-shaped first portions, with apexes aligned vertically in the blade rotational direction and between one-third and one-half of axial width of the substrate surface.
17. The engine of claim 16 , the apexes aligned axially between a leading edge and a mid-chord of a corresponding turbine blade airfoil at a cutoff point where an axially aligned line on the abradable surface is approximately tangent to a pressure surface of the airfoil; a forward portion of the vee forward of the apex aligned at an angle of 15 degrees plus or minus a leading edge angle of the airfoil; and an aft portion of the vee aft of the apex is aligned at an angle between approximately 15 degrees plus or minus a trailing edge angle of the airfoil.
18. The engine of claim 12 , comprising the pattern corresponding to a dual depth groove defining upper and lower groove heights, with the upper groove establishing an upper wear zone and the lower groove establishing a lower wear zone having greater turbine blade abrasion properties.
19. A turbine engine, comprising:
a turbine casing;
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 and axially with respect to the turbine casing; and
an abradable component having:
a support surface for coupling to the turbine casing; and
an abradable substrate coupled to the support surface, having a blade-facing abradable surface with a two-dimensional and continuous pattern corresponding to a zig-zag groove formed thereon that is oriented on the entire surface axially in gas flow and longitudinally in blade rotational directions, the pattern comprising a series of parallel first portions extending axially across the abradable substrate surface, joined sequentially at alternate opposing ends by shorter longitudinally oriented groove segments.
20. A method for making a turbine abradable component comprising:
providing a support surface for coupling to a turbine casing and an abradable substrate coupled to the support surface, having a blade-facing abradable surface and
forming a two-dimensional and continuous pattern corresponding to a single zig-zag groove formed thereon that is oriented on the entire surface axially in gas flow and longitudinally in blade rotational directions.
21. The method of claim 20 comprising forming the zig-zag pattern by cutting a groove in the abradable surface.