Mistuning alternate blades in a gas turbine engine
AssigneePratt & Whitney Canada Corp.
InventorsIgnatius Theratil, Krishna Prasad Balike, Ernest Adique, Anthony Bruni, Nicola Houle, Karan Anand
Life of this patent
Estimating the term…
Abstract
A gas turbine engine includes a propulsor, a compressor section and a turbine section, at least one of the propulsor, compressor section and turbine section having at least one row of blades mounted in a rotor. There is a plurality of circumferentially spaced blades in the at least one row. The plurality of blades in the at least one row each having a platform with an airfoil extending radially outwardly of the platform. The airfoils in a first group of said plurality of rotating blades has a different shape than the airfoils in a second group of the plurality of blades.
Claims3
A gas turbine engine comprising:
- a propulsor, a compressor section and a turbine section, at least one of the propulsor, compressor section, and turbine section having at least one row of blades mounted in a rotor, there being a plurality of circumferentially spaced blades in the at least one row;
- and
- the plurality of blades in the at least one row each having a platform with an airfoil extending radially outwardly of the platform, the airfoils in a first group of said plurality of blades having a different shape than the airfoils in a second group of the plurality of blades;
- wherein a tangentially shifted portion of the airfoils in the first group of the plurality of blades is shifted in a first direction and has a most shifted portion;
- wherein a tangentially shifted portion of the airfoils in the second group of the plurality of blades is shifted in a second direction opposite the first direction and occurs within 25% of a span defined along the airfoils in the second group between a root at the platform and a radially outer tip;
- and
- wherein the blades in the first group and the second group of the plurality of airfoils are identical radially outwardly of the 25% span;
- wherein the tangentially shifted portion of the airfoils in the second group has a most shifted portion which is shifted more than 1 degree and less than 2 degrees from the most shifted portion in the airfoils in the first group;
- and
- wherein an angle to define the most shifted portions of the first group and the second group is measured relative to a rotational axis of the gas turbine engine.
Dependencies are inferred from the claim text.