Rotor with improved balancing features
AssigneePratt & Whitney Canada Corp.
InventorsDavid DENIS, Amir Maria
Life of this patent
Estimating the term…
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.
Claims17
A rotor assembly for a gas turbine engine, the rotor assembly comprising a disk, a circumferential array of regularly spaced apart blades extending from the disk, a circumferential array of regularly spaced apart features provided on the disk and at least one balancing weight, each of the features being configured for receiving one of the at least one balancing weight, the circumferential array of features having an angular orientation relative to the circumferential array of blades such that all the features are each located at an at least substantially same offset angle from a stacking line of a respective adjacent one of the blades.
The rotor assembly for a gas turbine engine, wherein the at least one balancing weight includes a plurality of balancing weights, the balancing weights being all engaged to a respective one of the features.
A method of locating features on a rotor assembly of a gas turbine engine, the rotor including a rotor disk and a circumferential array of regularly spaced apart blades extending from the disk, the features being configured to receive at least one balancing weight, the method comprising:
- determining a quantity of the features to be provided on the rotor corresponding to a quantity of the blades extending from the disk;
- determining an offset angle for the features with respect to the circumferential array of blades based on a leading edge stress of the blades;
- and
- providing the features on the disk in a regularly circumferentially spaced manner such that each of the features is at least substantially located at the offset angle from a respective adjacent one of the blades.
A method of locating 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:
- selecting an angular position on the disk where a stress concentration caused by one of the features is minimal, the angular position being located at 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.
Dependencies are inferred from the claim text.