Turbine abradable layer with zig zag groove pattern
AssigneeSiemens Aktiengesellschaft
InventorsChing-Pang Lee, Kok-Mun Tham, Gm Salam Azad
Life of this patent
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Abstract
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.
Claims21
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.
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.
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.
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.
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.
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.
Dependencies are inferred from the claim text.