Method for machining an integrally bladed rotor

Patent metadata

Field	Value
Publication number	US-9382916-B2
Application number	US-81607906-A
Country	US
Kind code	B2
Filing date	Feb 4, 2006
Priority date	Feb 12, 2005
Publication date	Jul 5, 2016
Grant date	Jul 5, 2016

Abstract

A method for machining an integrally bladed rotor of a fluid-flow machine is disclosed. In accordance with an embodiment of the invention, the method includes the steps of: a) providing an integrally bladed rotor having a main rotor body and several rotor blades integrally attached to the main rotor body; b) determining the natural frequency of each rotor blade of the integrally bladed rotor; and c) machining at least one rotor blade of the integrally bladed rotor by removing material to adjust the natural frequency of the particular rotor blade to a specified value.

First claim

What is claimed is:

1. A method for machining an integrally bladed rotor of a fluid-flow machine, comprising the steps of:
a) providing an integrally bladed rotor having a main rotor body and several rotor blades integrally attached to the main rotor body;
b) determining a natural frequency of each rotor blade of the integrally bladed rotor; and
c) machining at least one rotor blade of the integrally bladed rotor by removing material to adjust the natural frequency of the at least one rotor blade to a specified value;
wherein the at least one rotor blade of the integrally bladed rotor is machined through material removal in an area of a radially inward lying transition section between the main rotor body and the rotor blade such that a radius of a fillet formed between the main rotor body and the rotor blade of the integrally bladed rotor varies as a result of the material removal.

2. The method according to claim 1 , wherein the natural frequency of each rotor blade of the integrally bladed rotor is determined by measurement.

3. The method according to claim 1 , wherein the natural frequency of each rotor blade of the integrally bladed rotor is determined analytically.

4. The method according to claim 1 , wherein a squealer tip is introduced in an area of a pressure side and/or a suction side of the at least one rotor blade through material removal in an area of a radially outward lying blade tip section.

5. The method according to claim 1 , wherein the natural frequency of the at least one machined rotor blade is adjusted such that all other rotor blades of the integrally bladed rotor have a same natural frequency.

6. The method according to claim 1 , wherein the natural frequency of the at least one machined rotor blade is adjusted such that the natural frequencies of the rotor blades of the integrally bladed rotor periodically change over a circumference of the integrally bladed rotor.

7. The method according to claim 1 , wherein the at least one rotor blade of the integrally bladed rotor is machined through material removal in an area of a radially outward lying transition section between an outer shroud and the rotor blade such that a radius of a fillet formed between the outer shroud and the rotor blade varies as a result of the material removal.

8. The method according to claim 1 , wherein the integrally bladed rotor is a compressor rotor of a gas turbine.

9. A method for modifying a vibration characteristic of a rotor blade of an integrally bladed rotor of a gas turbine, comprising the steps of:
determining a natural frequency of the rotor blade of the integrally bladed rotor; and
machining the rotor blade to modify the natural frequency of the rotor blade;
wherein the rotor blade of the integrally bladed rotor is machined through material removal in an area of a radially inward lying transition section between a main rotor body and the rotor blade such that a radius of a fillet formed between the main rotor body and the rotor blade of the integrally bladed rotor varies as a result of the material removal.

10. The method according to claim 9 , wherein the integrally bladed rotor includes a second rotor blade and further comprising the steps of:
determining a natural frequency of the second rotor blade of the integrally bladed rotor; and
machining the second rotor blade to modify the natural frequency of the second rotor blade.

11. The method according to claim 10 , wherein the modified natural frequency of the rotor blade is a same frequency as the modified natural frequency of the second rotor blade.

12. The method according to claim 10 , wherein the modified natural frequency of the rotor blade is a different frequency than the modified natural frequency of the second rotor blade.

13. The method according to claim 9 , wherein the step of machining includes removal of a material that forms the rotor blade.

14. The method according to claim 13 , wherein the material is removed from a section of the rotor blade.

15. The method according to claim 9 , wherein the rotor blade of the integrally bladed rotor is machined through material removal in an area of a radially outward lying transition section between an outer shroud and the rotor blade such that a radius of a fillet formed between the outer shroud and the rotor blade varies as a result of the material removal.

16. A method for modifying a vibration characteristic of a rotor blade of an integrally bladed rotor of a gas turbine, comprising the steps of:
determining a natural frequency of the rotor blade of the integrally bladed rotor; and
modifying the natural frequency of the rotor blade by removing material in an area of a radially inward lying transition section between a main rotor body and the rotor blade such that a radius of a fillet between the main rotor body and the rotor blade of the integrally bladed rotor varies as a result of the removing material.

Assignees

• Schoenenborn Harald
• Mtu Aero Engines Gmbh

Inventors

• Schoenenborn Harald

Classifications

• F02C7/045

  having provisions for noise suppression · CPC title

• F04D29/668

  damping or preventing mechanical vibrations · CPC title

• F05D2260/961

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

• F01D5/16

  for counteracting blade vibration · CPC title

• F01D5/34

  Rotor-blade aggregates of unitary construction {, e.g. formed of sheet laminae; (discs formed of sheet laminae F01D5/028; ceramic materials F01D5/284, composite materials F01D5/282)} · CPC title