Rotor with improved balancing features
First Claim
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1. A method of locating a circumferential array of features configured to receive a balancing weight in a rotor of a gas turbine engine, the rotor including a disk supporting a plurality of blades, the method comprising:
- determining a quantity of the features to correspond to a quantity of the blades extending from the disk;
selecting an angular position on the disk where a stress concentration caused by one of the features is minimal, defining the angular position as an offset angle from a stacking line of an adjacent one of the blades; and
providing each of the features on the disk at the offset angle from the stacking line of a respective one of the blades.
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Abstract
A rotor assembly for a gas turbine engine including a circumferential array of regularly spaced apart features provided on the disk which are each configured for receiving a balancing weight. The circumferential array of features has an angular orientation relative to the circumferential array of blades such that the features are each located at an at least substantially same offset angle from a stacking line of a respective adjacent blade.
41 Citations
8 Claims
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1. A method of locating a circumferential array of features configured to receive a balancing weight in a rotor of a gas turbine engine, the rotor including a disk supporting a plurality of blades, the method comprising:
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determining a quantity of the features to correspond to a quantity of the blades extending from the disk; selecting an angular position on the disk where a stress concentration caused by one of the features is minimal, defining the angular position as an offset angle from a stacking line of an adjacent one of the blades; and providing each of the features on the disk at the offset angle from the stacking line of a respective one of the blades. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8)
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Specification