US 2017/0254340 A1 · AIRFOIL TIP GEOMETRY TO REDUCE BLADE WEAR IN GAS TURBINE ENGINES

Abstract

An airfoil for use in a turbomachine includes a pressure sidewall and a suction sidewall coupled to the pressure sidewall. The suction sidewall and the pressure sidewall define a leading edge and an opposite trailing edge. The leading edge and the trailing edge define a chord distance. The airfoil further includes a root portion, and a tip portion. The tip portion extends between the pressure sidewall and the suction sidewall such that the tip portion is substantially perpendicular to each sidewall. The tip portion includes at least one planar section and at least one oblique section that forms a recess within the tip portion. The at least one oblique section extends from the at least one planar section towards the root portion along the chord distance. The tip portion is configured to reduce airfoil wear during contact with a surrounding casing.

Claims20

Dependent claims

An airfoil for use in a turbomachine, said airfoil comprising:

a pressure sidewall;
a suction sidewall coupled to said pressure sidewall, wherein said suction sidewall and said pressure sidewall define a leading edge and an opposite trailing edge, wherein said leading edge and said trailing edge define a chord distance;
a root portion;
and
a tip portion extending between said pressure sidewall and said suction sidewall such that said tip portion is substantially perpendicular to each sidewall, said tip portion comprises at least one planar section and at least one oblique section that forms a recess within said tip portion, said at least one oblique section extends from said at least one planar section towards said root portion along said chord distance, said tip portion is configured to reduce airfoil wear during contact with a surrounding casing.

2 more elements

A turbomachine comprising:

a casing;
a rotor assembly, said casing at least partially extending about said rotor assembly, said rotor assembly comprising:
a rotor shaft;
a plurality of rotor blades coupled to said rotor shaft, each rotor blade of said plurality of rotor blades comprises an airfoil comprising a pressure sidewall and a suction sidewall coupled to said pressure sidewall, wherein said suction sidewall and said pressure sidewall define a leading edge and an opposite trailing edge, wherein said leading edge and said trailing edge define a chord distance, said airfoil further comprising a root portion and a tip portion extending between said pressure sidewall and said suction sidewall such that said tip portion is substantially perpendicular to each sidewall, said tip portion comprising at least one planar section and at least one oblique section that forms a recess within said tip portion, said at least one oblique section extends from said at least one planar section towards said root portion along said chord distance, said tip portion is configured to reduce rotor blade wear during contact with said casing.

1 more element

A method for reducing blade wear during turbomachine operation, the turbomachine including a casing, a rotor shaft, and a plurality of rotor blades, each rotor blade of the plurality of rotor blades including an airfoil including a pressure sidewall and a suction sidewall coupled to the pressure sidewall, wherein the suction sidewall and the pressure sidewall define a leading edge and an opposite trailing edge, wherein the leading edge and the trailing edge define a chord distance, the airfoil further includes a root portion and a tip portion extending between the pressure sidewall and the suction sidewall such that the tip portion is substantially perpendicular to each sidewall, said method comprising:

removing blade material from the tip portion comprising forming a recess from at least one oblique section adjacent at least one planar section on the tip portion, the at least one oblique section extends from the at least one planar section towards the root portion along the chord distance;
and
coupling the rotor blade to the rotor shaft such that during turbomachine operation when the tip portion contacts the casing, wear of the rotor blade is reduced.

Dependencies are inferred from the claim text.

Airfoil tip geometry to reduce blade wear in gas turbine engines

Life of this patent

Airfoil tip geometry to reduce blade wear in gas turbine engines

Life of this patent

Abstract

Claims20