Rotor blade system for turbine engines
AssigneeGeneral Electric Company
InventorsKeegan Nathaniel Mehrtens, Yoon Seok Choi, Ramakrishna Mallina, Robert Bruce Dickman
Life of this patent
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Abstract
A rotor blade system for a turbine engine having a longitudinal centerline axis. The rotor blade system includes a rotor configured to rotate about the longitudinal centerline axis and a plurality of rotor blades coupled circumferentially around the rotor, each rotor blade having a leading edge, a trailing edge, a suction side, and a pressure side. At least one rotor blade of the plurality of rotor blades has an axial sweep of both the leading edge and the trailing edge as compared to a base blade of the plurality of rotor blades.
Claims20
A rotor blade system for a turbine engine having a longitudinal centerline axis, the rotor blade system comprising:
- a rotor configured to rotate about the longitudinal centerline axis;
- and
- a plurality of rotor blades coupled circumferentially around the rotor, each rotor blade having a leading edge, a trailing edge, a suction side, and a pressure side,
- wherein at least one rotor blade of the plurality of rotor blades is a base blade, and
- wherein at least one rotor blade of the plurality of rotor blades is a swept blade, the swept blade having a leading edge axial sweep of the leading edge as compared to a leading edge of the base blade of the plurality of rotor blades and a trailing edge axial sweep of the trailing edge as compared to a trailing edge of the base blade of the plurality of rotor blades.
(canceled)
A turbine engine having a longitudinal centerline axis, the turbine engine comprising:
- a rotor blade system comprising:
- a rotor configured to rotate about the longitudinal centerline axis;
- and
- a plurality of rotor blades coupled circumferentially around the rotor, each rotor blade having a leading edge, a trailing edge, a suction side, and a pressure side,
- a low-pressure turbine, a high-pressure turbine, a low-pressure compressor, and a high-pressure compressor;
- and
- a fan,
- wherein the rotor blade system is included in at least one stage of at least one of the low-pressure turbine, the high-pressure turbine, the low-pressure compressor, the high-pressure compressor, or the fan, and
- wherein at least one rotor blade of the plurality of rotor blades is a base blade, and wherein at least one rotor blade of the plurality of rotor blades is a swept blade, the swept blade having a leading edge axial sweep of the leading edge as compared to a leading edge of the base blade of the plurality of rotor blades and a trailing edge axial sweep of the trailing edge as compared to a trailing edge of the base blade of the plurality of rotor blades.
Dependencies are inferred from the claim text.