IP Library › Granted Patent US 12669060
Granted Patent B2
US 12669060 · App. 18/596,318 · Granted Jun 30, 2026

Airfoil rotor hub system having intentional frequency mistuning

Inventors: Kevin E. Turner (Liberty Township, OH); Yoon Seok Choi (Kenwood, OH); Cem Tutcu (Istanbul, TR); Keegan Nathaniel Mehrtens (Peabody, MA); Ramakrishna Mallina (Mason, OH); Robert Bruce Dickman (Cincinnati, OH)
Assignee: General Electric Company
F01D5/10F01D5/16F05D2250/11F05D2250/183F05D2260/961
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Quick Facts
Patent No.
US 12669060
App. No.
18/596,318
Granted
Jun 30, 2026
Kind
B2
Abstract

An airfoil rotor hub system including a rotor hub, the rotor hub having a variable radius around a circumference of the rotor hub, and a plurality of airfoils connected to the rotor hub, a first airfoil in the plurality of airfoils having a first span connected to a surface of the rotor hub at a first radius, and a second airfoil in the plurality of airfoils having a second span connected to the surface of the rotor hub at a second radius. The first radius is different from the second radius, and the first span of the first airfoil is different from the second span of the second airfoil so as to mistune a frequency of the first airfoil and the second airfoil to reduce or substantially to eliminate flutter in the plurality of airfoils.

Claims (18)

1 . An airfoil rotor hub system comprising:

a rotor hub having a variable radius around a circumference of the rotor hub such that a surface of the rotor hub has a variable shape around the circumference of the rotor hub, the rotor hub being a single structure; and

a plurality of airfoils connected to the rotor hub, a first airfoil in the plurality of airfoils having a first base connected to the surface of the rotor hub and a first tip extending therefrom by a first span, the first base of the first airfoil is connected to the surface of the rotor hub at a first radius, and a second airfoil in the plurality of airfoils having a second base connected to the surface of the rotor hub and a second tip extending therefrom by a second span, the second base of the second airfoil is connected to the surface of the rotor hub at a second radius, wherein the first radius is different from the second radius, and the first span of the first airfoil is different from the second span of the second airfoil so as to mistune a frequency of the first airfoil and the second airfoil to reduce or substantially to eliminate flutter in the plurality of airfoils.

2 . The airfoil rotor hub system according to claim 1 , wherein the first airfoil is adjacent to the second airfoil.

3 . The airfoil rotor hub system according to claim 1 , wherein the surface of the rotor hub has a rounded scalloped shape, or a sinewave shape, the first airfoil is connected to a peak of the rounded scalloped shape, or the sinewave shape of the surface of the rotor hub, and the second airfoil is connected to a trough of the rounded scalloped shape, or the sinewave shape of the surface of the rotor hub.

4 . The airfoil rotor hub system according to claim 1 , wherein the first span of the first airfoil is less than the second span of the second airfoil.

5 . The airfoil rotor hub system according to claim 1 , wherein the plurality of airfoils are equally spaced circumferentially around the circumference of the rotor hub.

6 . The airfoil rotor hub system according to claim 1 , wherein the airfoil rotor hub system has a radius defined as a distance between a rotation axis of the rotor hub and a tip of an airfoil in the plurality of airfoils, and the radius of the airfoil rotor hub system is equal to a sum of the radius of the rotor hub and a span of the plurality of the airfoils.

7 . A turbine engine comprising:

an airfoil rotor hub system comprising:

a rotor hub having a variable radius around a circumference of the rotor hub such that a surface of the rotor hub has a variable shape around the circumference of the rotor hub, the rotor hub being a single structure; and

a plurality of airfoils connected to the rotor hub, a first airfoil in the plurality of airfoils having a first base connected to the surface of the rotor hub and a first tip extending therefrom by a first span, the first base of the first airfoil is connected to the surface of the rotor hub at a first radius, and a second airfoil in the plurality of airfoils having a second base connected to the surface of the rotor hub and a second tip extending therefrom by a second span, the second base of the second air foil is connected to the surface of the rotor hub at a second radius,

wherein the first radius is different from the second radius, and the first span of the first airfoil is different from the second span of the second airfoil so as to mistune a frequency of the first airfoil and the second airfoil to reduce or substantially eliminate flutter in the plurality of airfoils.

8 . The turbine engine according to claim 7 , wherein the first airfoil is adjacent to the second airfoil.

9 . The turbine engine according to claim 7 , wherein the surface of the rotor hub has a rounded scalloped shape, or a sinewave shape, the first airfoil is connected to a peak of the rounded scalloped shape, or the sinewave shape of the surface of the rotor hub, and the second airfoil is connected to a trough of the rounded scalloped shape, or the sinewave shape of the surface of the rotor hub.

10 . The turbine engine according to claim 7 , wherein the first span of the first airfoil is less than the second span of the second airfoil.

11 . The turbine engine according to claim 7 , wherein the plurality of airfoils are equally spaced circumferentially around the circumference of rotor hub.

12 . The turbine engine according to claim 7 , wherein the airfoil rotor hub system has a radius defined as a distance between a rotation axis of the rotor hub and a tip of an airfoil in the plurality of airfoils, and the radius of the airfoil rotor hub system is equal to a sum of the radius of the rotor hub and a span of the plurality of the airfoils.