Blade cascade and turbomachine

Patent metadata

Field	Value
Publication number	US-10041353-B2
Application number	US-201414452594-A
Country	US
Kind code	B2
Filing date	Aug 6, 2014
Priority date	Aug 6, 2013
Publication date	Aug 7, 2018
Grant date	Aug 7, 2018

Abstract

A blade cascade of a turbomachine whose at least one side wall is configured to be circumferentially undulated and which has at least two elevations and at least one depression or at least two depressions having at least one elevation, as well as a turbomachine having a blade cascade of this kind.

First claim

What is claimed is:

1. A blade cascade of a turbomachine comprising:
a plurality of blade channels each circumferentially bounded by a pressure side of a blade and by an opposite suction side of an adjacent blade, each blade channel radially bounded by two opposing side walls, at least one of the two side walls of the blade channels being provided with a side-wall contour, the side-wall contour being circumferentially undulated and comprising at least two elevations relative to a non-contoured surface of the at least one of the two side walls and at least one depression relative to the non-contoured surface of the at least one of the two side walls;
wherein the amplitudes of the elevations differ from one another; and
wherein a plurality of depressions merge into the at least one depression.

2. The blade cascade as recited in claim 1 wherein the side-wall contour extends to a downstream side-wall edge.

3. The blade cascade as recited in claim 1 wherein the elevations and the at least one depression having widths that vary circumferentially or lengths that differ in the direction of flow.

4. The blade cascade as recited in claim 1 wherein the elevations and the at least one depression have amplitudes that vary in the direction of flow.

5. The blade cascade as recited in claim 1 wherein a pressure side-proximal elevation has a greater amplitude than a pressure side-distal elevation.

6. The blade cascade as recited in claim 1 wherein radii of curvature of the side-wall contour vary.

7. A turbomachine comprising at least one blade cascade as recited in claim 1 .

8. A blade cascade of a turbomachine comprising:
a plurality of blade channels each circumferentially bounded by a pressure side of a blade and by an opposite suction side of an adjacent blade, each blade channel radially bounded by two opposing side walls, at least one of the two side walls of the blade channels being provided with a side-wall contour, the side-wall contour being circumferentially undulated and comprising at least two depressions relative to a non-contoured surface of the at least one of the two side walls and at least one elevation relative to the non-contoured surface of the at least one of the two side walls; wherein the amplitudes of the depressions differ from one another; and wherein a suction side-proximal depression has a greater amplitude than a suction side-distal depression.

9. The blade cascade as recited in claim 8 wherein the side-wall contour extends to a downstream side-wall edge.

10. The blade cascade as recited in claim 8 wherein the depressions and the at least one elevation have widths that vary circumferentially or lengths that differ in the direction of flow.

11. The blade cascade as recited in claim 8 wherein the depressions and the at least one elevation are configured downstream from a constriction region of the blade channel and normally to the constriction region.

12. The blade cascade as recited in claim 8 wherein a plurality of depressions merge into one of the depressions.

13. The blade cascade as recited in claim 8 wherein the depressions and the at least one elevation have amplitudes that vary in the direction of flow.

14. The blade cascade as recited in claim 8 wherein radii of curvature of the side-wall contour vary.

15. The blade cascade as recited in claim 8 , wherein each of the depressions includes a trough.

16. A turbomachine comprising at least one blade cascade as recited in claim 8 .

Assignees

• MTU Aero Engines AG

Inventors

• Gier Jochen
• Guendogdu Yavuz
• Engel Karl

Classifications

• F05D2250/712

  concave · CPC title

• F01D9/02

  Nozzles; Nozzle boxes; Stator blades; Guide conduits {, e.g. individual nozzles (nozzle boxes F01D9/047)} · CPC title

• F05D2250/611

  undulated · CPC title

• F05D2250/711

  convex · CPC title

• F01D5/145

  Means for influencing boundary layers or secondary circulations (for compressors F04D29/68) · CPC title