TURBINE IMPELLER COMPRISING BLADE WITH SQUEALER TIP

• US 20130142651A1
• Filed: 12/06/2012
• Published: 06/06/2013
• Est. Priority Date: 12/06/2011
• Status: Active Grant

• Current Assignee: Hanwha Aerospace Co., Ltd. (Hanwha Corporation)
• Original Assignee: Samsung Techwin Corporation (Hanwha Corporation)
• Inventors: LIM, Chan-sun
• Granted Patent: US 9,255,481 B2
• Time in Patent Office: Days
• US Class Current: 416/91
• CPC Class Codes: F01D 5/145 Means for influencing boundary layers or secondary circulations for compressors F04D29/68
• CPC Class Codes: F01D 5/20 Specially-shaped blade tips to seal space between tips and stator F01D5/225 takes precedence

Abstract

A turbine impeller including a rotor; a blade extending from the rotor from a first end of the blade; and a squealer tip provided at a second end opposite to the first end of the blade, wherein at least one perforated portion penetrates through the squealer tip.

Claims

1. A turbine impeller comprising:

a rotor;

a blade extending from the rotor from a first end of the blade; and

a squealer tip provided at a second end of the blade opposite to the first end,

wherein at least one perforated portion penetrates through the squealer tip.

2. The turbine impeller of claim 1, wherein a first perforated portion of the at least one perforated portion penetrates through a portion of a pressure surface of the blade closer to a leading edge of the blade than to a trailing edge of the blade.

3. The turbine impeller of claim 2, wherein a fluid flows from the outside of the blade into the squealer tip via the first perforated portion of the pressure surface of the blade, and

a cross-sectional area of the first perforated portion of the pressure surface of the blade decreases in a direction from the outside of the blade to an interior of the squealer tip.

4. The turbine impeller of claim 2, wherein a second perforated portion of the at least one perforated portion penetrates through a portion of an absorbing surface of the blade closer to the trailing edge of the blade than to the leading edge of the blade.

5. The turbine impeller of claim 4, wherein a fluid flows from the outside of the blade into the squealer tip via the first perforated portion of the pressure surface of the blade and flows from the interior of the squealer tip to outside of the blade via the second perforated portion of the absorbing surface of the blade, and

a cross-sectional area of the first perforated portion of the pressure surface of the blade decreases in a direction from the outside of the blade to an interior of the squealer tip.

6. The turbine impeller of claim 5, wherein

a cross-sectional area of the second perforated portion of the absorbing surface of the blade decreases in a direction from the interior of the squealer tip to outside of the blade.

7. The turbine impeller of claim 6, wherein surfaces of the squealer tip contacting the first and second perforated portions comprise streamline shapes.

8. The turbine impeller of claim 1, wherein a second of the at least one perforated portion perforated portion penetrates through a portion of the absorbing surface of the blade closer to the trailing edge of the blade than to the leading edge of the blade.

9. The turbine impeller of claim 8, wherein a fluid flows from an interior of the blade to outside of the blade via the second perforated portion of the absorbing surface of the blade, and

a cross-sectional area of the second perforated portion of the blade decreases in a direction from the interior of the squealer tip to the outside of the blade.

10. The turbine impeller of claim 9, wherein surfaces of the squealer tip contacting the second perforated portion comprise streamline shapes.

11. The turbine impeller of claim 1, wherein surfaces of the squealer tip contacting the at least one perforated portion comprise streamline shapes.

12. A blade extending from a rotor of a turbine impeller comprising:

a base portion provided at a first end attached to the rotor;

a pressure side airfoil;

a absorption side airfoil;

a tip provided at a second end opposite of the first end of the blade comprising;

a pressure side squealer tip;

a suction side squealer tip; and

a groove disposed between the pressure side and absorption side squealer tips,

wherein a plurality of perforated portions penetrates through each of the pressure side and the absorption side squealer tips.

13. The blade of claim 12, wherein a cross-sectional area of each of the plurality of perforated portions of the blade decreases in a direction from the pressure side airfoil to the absorption side of the airfoil.

14. The blade of claim 12, wherein surfaces of the pressure and absorption side squealer tips contacting the plurality of perforated portions comprise streamline shapes.