Local pressure side blade tip lean
AssigneeRaytheon Technologies Corporation
InventorSimon W. Evans
Life of this patent
Estimating the term…
Abstract
A rotor blade of a gas turbine engine includes a pressure side, and a suction side opposite the pressure side and defining a rotor blade profile therebetween, the pressure side and the suction side each extending from a blade root to a blade tip. The rotor blade defines a cross-sectional median line midway between the pressure side and the suction side. The cross-sectional median line extends in a generally radial direction from the blade root to a lean point between the blade root and the blade tip. The cross-sectional median line extends off of radial from the lean point to the blade tip, defining a lean of the rotor blade between the lean point and the blade tip.
Claims16
A rotor blade of a gas turbine engine, comprising:
- a pressure side;
- and
- a suction side opposite the pressure side and defining a rotor blade profile therebetween, the pressure side and the suction side each extending from a blade root to a blade tip;
- wherein the rotor blade defines a cross-sectional median line midway between the pressure side and the suction side, the cross-sectional median line extending in a generally radial direction from the blade root to a lean point between the blade root and the blade tip, the cross-sectional median line extending off of radial from the lean point to the blade tip, defining a lean of the rotor blade between the lean point and the blade tip;
- and
- wherein the lean point is disposed at a radial position defined relative to the blade tip by a distance equal to between 100% and 300% of a tip clearance, defined as the distance between the blade tip and an outer air seal.
A rotor of a gas turbine engine, comprising:
- a rotor hub;
- and
- a plurality of rotor blades extending from the hub at a blade root outwardly to a blade tip, each rotor blade including:
- a pressure side;
- and
- a suction side opposite the pressure side and defining a rotor blade profile therebetween, the pressure side and the suction side each extending from the blade root to the blade tip;
- wherein the rotor blade defines a cross-sectional median line midway between the pressure side and the suction side, the cross-sectional median line extending in a general radial direction from the blade root to a lean point between the blade root and the blade tip, the cross-sectional median line extending off of radial from the lean point to the blade tip, defining a lean of the rotor blade between the lean point and the blade tip;
- and
- wherein the lean point is disposed at a radial position defined relative to the blade tip by a distance equal to between 100% and 300% of a tip clearance, defined as the distance between the blade tip and an outer air seal.
A gas turbine engine, comprising:
- a combustor;
- and
- a compressor disposed upstream of the combustor to direct airflow to the combustor, the compressor including at least one rotor, the rotor including:
- a rotor hub;
- and
- a plurality of rotor blades extending from the hub at a blade root outwardly to a blade tip, each rotor blade including:
- a pressure side;
- and
- a suction side opposite the pressure side and defining a rotor blade profile therebetween, the pressure side and the suction side each extending from the blade root to the blade tip;
- wherein the rotor blade defines a cross-sectional median line midway between the pressure side and the suction side, the cross-sectional median line extending radially from the blade root to a lean point between the blade root and the blade tip, the cross-sectional median line extending off of radial from the lean point to the blade tip, defining a lean of the rotor blade between the lean point and the blade tip;
- and
- wherein the lean point is disposed at a radial position defined relative to the blade tip by a distance equal to between 100% and 300% of a tip clearance, defined as the distance between the blade tip and an outer air seal.
Dependencies are inferred from the claim text.