Fan rotor with flow induced resonance control

Patent metadata

Field	Value
Publication number	US-11035385-B2
Application number	US-201916591876-A
Country	US
Kind code	B2
Filing date	Oct 3, 2019
Priority date	Mar 22, 2017
Publication date	Jun 15, 2021
Grant date	Jun 15, 2021

Abstract

A rotor for a gas turbine is disclosed which includes alternating first and second set of rotor blades, the first set of rotor blades having a baseline profile and the second set of rotor blades having a profile with a cutback relative to the baseline profile, the cutback defining a removed portion of the baseline profile surrounding a maximum deflection point of a selected natural vibration mode. The cutback may be a leading edge cutback at a span position located a distance away from the hub between 20% and 50% of the total span length. The selected natural vibration mode may be a natural vibration mode higher than the 1st natural vibration mode, more specifically may be the 5t″ natural vibration mode.

First claim

The invention claimed is:

1. A fan for a gas turbine, the fan comprising fan blades circumferentially distributed around and extending a full span length from a central hub, the fan blades including alternating first fan blades and second fan blades, the first fan blades having a baseline profile and the second fan blades having a modified profile being the same as the baseline profile but for a leading edge cutback, the leading edge cutback on the second fan blades located between 20% and 50% of the full span length away from the hub, a maximum deflection point for a selected natural vibration mode of the first fan blade having the baseline profile is located at a given span, and wherein a span location on the second fan blades corresponding to the given span is located within the leading edge cutback.

2. The fan as defined in claim 1 , wherein the leading edge cutback removes a portion of the baseline profile surrounding the maximum deflection point on the second fan blades and all points of at least 95% of maximum deflection of the selected natural vibration mode.

3. The fan as defined in claim 1 , wherein the leading edge cutback removes a portion of the baseline profile surrounding the maximum deflection point on the second fan blades and all points of no less than 65% of maximum deflection of the selected natural vibration mode.

4. The fan as defined in claim 1 , wherein the selected natural vibration mode is a natural vibration mode higher than a 1 st natural vibration mode.

5. The fan as defined in claim 4 , wherein the selected natural vibration mode is a 5 th natural vibration mode.

6. The fan as defined in claim 1 , wherein the fan blades are swept fan blades.

7. The fan as defined in claim 1 , the fan blades including successively alternating first fan blades, second fan blades and third fan blades, the third fan blades having a second modified profile, the second modified profile being the same as the baseline profile but for cutback different from the cutback of the modified profile of the second fan blades.

8. A rotor for a gas turbine, the rotor comprising rotor blades circumferentially distributed around and extending a total span length from a central hub, the rotor blades including alternating first rotor blades and second rotor blades, the first rotor blades having a leading edge baseline profile and the second rotor blades having a leading edge profile with a leading edge cutback relative to the baseline profile, the leading edge cutback extending from a first span position to a second span position, wherein the first and second span positions are located at a distance away from the hub of between 20% and 50% of the total span length.

9. The rotor as defined in claim 8 , wherein the first position is located radially outwardly of a span location corresponding to a maximum deflection point for a selected natural vibration mode of a fan blade having a leading edge baseline profile and the second span position is located radially inwardly of the maximum deflection point, the selected natural vibration mode being a natural vibration mode higher than a 1 st natural vibration mode.

10. The rotor as defined in claim 9 , wherein the selected natural vibration mode is a 5 th natural vibration mode.

11. The fan as defined in claim 8 , wherein the fan blades are swept fan blades.

12. A rotor for a gas turbine, the rotor comprising rotor blades circumferentially distributed around and extending a total span length from a central hub, the rotor blades including alternating first rotor blades and second rotor blades, the first rotor blades having a baseline profile and the second rotor blades having a profile with a leading edge cutback relative to the baseline profile, the leading edge cutback of the second rotor blades defining a removed portion of the baseline profile surrounding a maximum deflection point of a selected natural vibration mode higher than a 1 st natural vibration mode.

13. The rotor of claim 12 , wherein the portion of the baseline profile removed by the cutback surrounds the maximum deflection point and all points of at least 95% of maximum deflection of the selected natural vibration mode.

14. The rotor of claim 12 , wherein the portion of the baseline profile removed by the cutback surrounds the maximum deflection point and all points of no less than 65% of maximum deflection of the selected natural vibration mode.

15. The rotor as defined in claim 12 , wherein the selected natural vibration mode is a 5 th natural vibration mode.

Assignees

• Pratt & Whitney Canada

Inventors

• Theratil Ignatius
• Balike Krishna

Classifications

• F05D2230/10

  by removing material · CPC title

• F04D29/666 Primary

  by means of rotor construction or layout, e.g. unequal distribution of blades or vanes · CPC title

• F05D2260/961

  by mistuning rotor blades or stator vanes with irregular interblade spacing, airfoil shape · CPC title

• F04D29/327

  with non identical blades · CPC title

• B64D27/20

  within, or attached to, fuselages · CPC title