Intentionally mistuned integrally bladed rotor

• US 8,043,063 B2
• Filed: 03/26/2009
• Issued: 10/25/2011
• Est. Priority Date: 03/26/2009
• Status: Active Grant

• Current Assignee: Pratt & Whitney Canada Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Original Assignee: Pratt & Whitney Canada Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Wu, Yuhua, Kelly, Frank, Fazari, Edward, Heikurinen, Kari
• Primary Examiner(s): Sarkar; Asok
• Application Number:
  US12/411,644
• Publication Number:
  US 20100247310A1
• Time in Patent Office: 943 Days
• Field of Search: 415/119, 415/208.3, 416/61, 416/144, 416/175, 416/203, 416/223.A, 416/228, 416/234, 416/243, 416/500
• US Class Current: 416/203
• CPC Class Codes: F01D 5/10 Anti- vibration means specially adapted for radial flow machines or engines F01D5/04
• CPC Class Codes: F01D 5/16 for counteracting blade vibration
• CPC Class Codes: F05D 2260/96 Preventing, counteracting or reducing vibration or noise
• CPC Class Codes: F05D 2260/961 by mistuning rotor blades or stator vanes with irregular interblade spacing, airfoil shape
• CPC Class Codes: Y10S 416/50 Vibration damping features

Abstract

A frequency mistuned integrally bladed rotor (IBR) for a gas turbine engine comprises a hub and a circumferential row of blades of varying frequency projecting integrally from the hub. Each blade in the row alternate with another blade having a different pressure surface definition but similar suction surface, leading edge and trailing edge definitions.

Claims

1. An integrally bladed rotor (IBR) for a gas turbine engine, comprises a hub and a circumferential row of blades projecting integrally from said hub, the row including an even number of blades alternating between blades having first and second airfoil definitions around the hub, each blade having a pressure side and a suction side disposed on opposed sides of a median axis and extending between a trailing edge and a leading edge, the first and second airfoil definitions being different and having respective pressure side thicknesses T1 and T2 defined between respective median axes and respective pressure sides of the blades, the pressure side thickness T1 of the first airfoil definition being greater than the pressure side thickness T2 of the second airfoil definition.

2. The IBR defined in claim 1, wherein the first and second airfoil definitions have a same suction surface, leading edge and trailing edge profile but a different pressure surface profile.

3. The IBR defined in claim 1, wherein a first interblade passage defined between the pressure side of a first blade having the first airfoil definition and the suction side of an adjacent blade having the second airfoil definition has a smaller passage section than that of a second interblade passage defined between the pressure side of the adjacent blade and the suction side of a next blade having the first airfoil definition, thereby providing for alternate small and large interblade passages around the hub.

4. The IBR defined in claim 1, wherein the natural frequency of the blades having the pressure side thickness T1 differs from the natural frequency of the blades having the pressure side thickness T2 by at least 3% and up to 10%.

5. The IBR defined in claim 1, wherein the difference in thickness between T1 and T2 is provided over substantially the full span of the blades.

6. The IBR defined in claim 1, wherein the first airfoil definition is thicker than the second airfoil definition between the leading edge and the trailing edge of the blades.

7. A frequency mistuned integrally bladed rotor (IBR) for a gas turbine engine, comprising a hub and a circumferential row of blades of varying frequency projecting integrally from the hub, the row including an even number of blades, each blade in the row alternates with another blade having a different pressure surface definition but substantially identical suction surface, leading edge and trailing edge definitions.

8. The mistuned IBR defined in claim 7, wherein the circumferential row of blades includes a first group of blades and a second group of blades disposed in an alternating pattern around the hub, the blades of the first and second groups of blades having corresponding first and second blades sections over the full span of the blades, the corresponding first and second blades sections when superposed having coincident suction side, leading edge and trailing edge outlines but a different pressure side outline, the pressure side outline of the first blade section being offset outwardly from the corresponding pressure side outline of the second blade section along at least a chord-wise portion of the blades.

9. The mistuned IBR defined in claim 8, wherein the offset extends over substantially a full span of the blades.

10. The mistuned IBR defined in claim 8, wherein the offset between the pressure side outlines of the first and second corresponding blade sections is provided between the leading edge and the trailing edge of the blades.

11. The mistuned IBR defined in claim 8, wherein the blades of the first group of blades have a thicker pressure side than that of the blades of the second group of blades.

12. The mistuned IBR defined in claim 8, wherein the blades of the first group of blades have a natural frequency which differs from the natural frequency of the blades of the second group of blades by at least 3% and up to 10%.

13. A method of reducing vibration in an gas turbine engine integrally bladed rotor (IBR) having a circumferential row of blades extending integrally from a hub, the circumferential row of blades comprising an even number of blades;

the method comprising varying the natural frequency of the blades around the hub in an alternate pattern by providing first and second distinct airfoil profiles around the hub, the first and second profiles having similar suction side, leading edge and trailing edge profiles but a different pressure side profile.