Compressor blade and production and use of a compressor blade

Patent metadata

Field	Value
Publication number	US-8951008-B2
Application number	US-65955105-A
Country	US
Kind code	B2
Filing date	Jun 20, 2005
Priority date	Aug 6, 2004
Publication date	Feb 10, 2015
Grant date	Feb 10, 2015

Abstract

The invention relates to a compressor blade of a compressor which, along a main axis, comprises a blade base, a platform area and an adjacent blade profile having a profile tip. The blade profile is configured by a convex wall at the suction end and a concave wall at the pressure end opposite the wall at the suction end. These surfaces extend, with respect to a flow medium, from a leading edge to a trailing edge, a profile center line extending in the center between the two. A front face is arranged on the profile tip at an angle to the main axis, a sealing lip at least partially extending from the leading edge to the trailing edge and the blade profile including the sealing lip having a blade profile height extending in the direction of the main axis. In order to allow for an inexpensive compressor blade having improved aerodynamic properties and a modified sealing lip while having the same sealing properties, the height of the sealing lip is less than 2 percent of the height of the blade profile.

First claim

The invention claimed is:

1. A compressor blade for a compressor, comprising:
a blade root arranged along a main axis of the blade;
a platform section arranged adjacent to the blade root and along the main axis;
a blade profile adjoining the platform section having a profile tip and a profile height extending in the direction of the main axis, the blade profile extending from a leading edge with respect to a flow medium to a trailing edge between which a profile center line extends in the middle, and a convex suction side wall and a concave pressure side wall opposite the suction side wall, wherein an end face, which is disposed transversely to the main axis, is located on the profile tip; and
a sealing lip arranged on the end face, the sealing lip being formed in one piece with the blade profile, extends along the profile center line at least partially from the leading edge to the trailing edge, at a distance from suction side wall and from pressure side wall, wherein the sealing lip has a sealing lip height that is less than two percent of the height of the blade profile.

2. The compressor blade as claimed in claim 1 , wherein the sealing lip has a suction side face on the suction side and a pressure side face on the pressure side, which both side faces extend parallel to the main axis.

3. The compressor blade as claimed in claim 2 , wherein the two side faces extend parallel to the profile center line.

4. The compressor blade as claimed in claim 2 , wherein the side faces of the sealing lip are interconnected by a feathered surface disposed perpendicularly to the radius of the rotor of the compressor.

5. The compressor blade as claimed in claim 1 , wherein one of the side faces of the sealing lip is interconnected to the end face by a radius that is at most 25 percent of the height of the sealing lip.

6. The compressor blade as claimed in claim 1 , wherein the sealing lip is machined into the profile tip.

7. A method for producing a sealing lip of a compressor blade, comprising:
arranging a blade root along a main axis of the blade;
arranging a platform section adjacent to the blade root and along the main axis;
adjoining a blade profile to the platform section, the blade profile having a profile tip and a profile height extending in the direction of the main axis, the blade profile extending from a leading edge with respect to a flow medium to a trailing edge between which a profile center line extends in the middle, and a convex suction side wall and a concave pressure side wall opposite the suction side wall, wherein an end face, which is disposed transversely to the main axis, is located on the profile tip; and
arranging a sealing lip on the end face, the sealing lip being formed in one piece with the blade profile, extends along the profile center line at least partially from the leading edge to the trailing edge, at a distance from suction side wall and from pressure side wall, wherein the sealing lip has a sealing lip height that is less than two percent of the height of the blade profile and the sealing lip is machined on a profile tip of a blade profile by a milling unit.

8. The method as claimed in claim 7 , wherein the sealing lip is machined by a 3 axis milling unit.

9. The method as claimed in claim 7 , wherein the compressor blade is milled or close-tolerance forged.

10. A gas turbine engine arranged along a rotational center axis, comprising:
a rotor arranged coaxial with the center axis;
an axial flow compressor section that compresses a flow medium, the compressor section having:
a plurality of rotor disk sections that collectively form a compressor rotor section,
a plurality of compressor rotor blades arranged on the rotor disks, each rotor blades comprising:
a blade root arranged along a blade main axis,
a platform section arranged adjacent to the blade root and along the main axis,
a blade profile adjoining the platform section having a profile tip and a profile height extending in the direction of the main axis, the blade profile extending from a leading edge with respect to a flow direction of the flow medium to a trailing edge between which a profile center line extends in the middle, and a convex suction side wall and a concave pressure side wall opposite the suction side wall, wherein an end face, which is disposed transversely to the main axis, is located on the profile tip, and
a sealing lip arranged on the end face, the sealing lip being formed in one piece with the blade profile, extending along the profile center line at least partially from the leading edge to the trailing edge, at a distance from the suction side and the pressure side walls, wherein the sealing lip has a sealing lip height that is less than two percent of the height of the blade profile,

a combustor section that receives the compressed flow medium and produces a hot flow medium; and
a turbine section that expands the hot flow medium to extract mechanical energy.

11. The gas turbine engine as claimed in claim 10 , wherein the sealing lip has a suction side face on the suction side and a pressure side face on the pressure side, which both side faces extend parallel to the main axis.

12. The gas turbine engine as claimed in claim 11 , wherein the two side faces extend parallel to the profile center line.

13. The gas turbine engine as claimed in claim 11 , wherein the side faces of the sealing lip are interconnected by a feathered surface disposed perpendicularly to the radius of the rotor of the compressor.

14. The gas turbine engine as claimed in claim 10 , wherein one of the side faces of the sealing lip is interconnected to the end face by a radius that is at most 25 percent of the height of the sealing lip.

15. The gas turbine engine as claimed in claim 14 , wherein the engine is a stationary, industrial gas turbine engine.

Assignees

• Cornelius Christian
• Küsters Bernhard
• Mais Stephan
• Peters Andreas
• Schirrmacher Achim
• Stephan Lutz
• Van Den Toorn Bernd
• Siemens Ag

Inventors

• Cornelius Christian
• Küsters Bernhard
• Mais Stephan
• Peters Andreas
• Schirrmacher Achim
• Stephan Lutz
• Van Den Toorn Bernd

Classifications

• F04D29/164 Primary

  of an axial flow wheel · CPC title

• F01D5/20

  Specially-shaped blade tips to seal space between tips and stator {(F01D5/225 takes precedence)} · CPC title

• Y10T29/49336

  Blade making · CPC title

• F04D29/324

  Blades · CPC title

• Y10T29/49321

  Assembling individual fluid flow interacting members, e.g., blades, vanes, buckets, on rotary support member · CPC title