Blade cascade with side wall contours and continuous-flow machine

Patent metadata

Field	Value
Publication number	US-9470094-B2
Application number	US-201313957007-A
Country	US
Kind code	B2
Filing date	Aug 1, 2013
Priority date	Aug 9, 2012
Publication date	Oct 18, 2016
Grant date	Oct 18, 2016

Abstract

A blade cascade for a continuous-flow machine having a non-axisymmetrical side wall contour, whereby the side wall contour has at least one pressure-side elevation and one suction-side depression, whose highest section and lowest section are located over an area 30% to 60% of an extension of the blades in the axial direction, and the axial positions of the outermost sections differ from each other at the maximum by 10% in the axial direction.

First claim

What is claimed is:

1. A blade cascade for a continuous-flow machine, comprising:
at least one blade channel delimited in a circumferential direction by a pressure-side wall of a first blade and by an opposite suction-side wall of an adjacent second blade and delimited in a radial direction by two opposite delimiting walls,
in the area of the pressure-side wall, at least one of the delimiting walls being provided with at least one pressure-side elevation and, in the area of the suction-side wall, the at least one delimiting wall having at least one suction-side depression, a highest section of the at least one elevation and a lowest section of the at least one depression being located over an area of 30% to 60% of an extension of the blades in an axial direction, and wherein an axial position of the highest section and an axial position of the lowest section differ from each other at a maximum by 10% in the axial direction; and
wherein, in the area of the suction-side wall, a second suction-side depression is arranged downstream from the first depression, the second depression being at a distance from the first depression, separated by a non-contoured section of the delimiting wall.

2. The blade cascade as recited in claim 1 wherein, as seen in the circumferential direction, the at least one pressure-side elevation and the at least one suction-side depression are at a distance from each other, separated by a non-contoured delimiting wall section.

3. The blade cascade as recited in claim 2 wherein the at least one pressure-side elevation and the at least one suction-side depression are arranged downstream from a leading edge of the first and second blades and upstream from a trailing edge of the first and second blades.

4. The blade cascade as recited in claim 1 wherein the highest section of the elevation is downstream from the lowest section of the depression.

5. The blade cascade as recited in claim 1 wherein a lowest section of the second depression is arranged downstream from a highest section of a second elevation.

6. The blade cascade as recited in claim 1 wherein a second elevation is arranged on the pressure-side wall and the second depression is arranged on the suction-side wall, upstream from the leading edges.

7. The blade cascade of claim 1 , wherein, in the area of the pressure-side wall, a second pressure-side elevation is arranged downstream from the first elevation, the second elevation being at a distance from the first elevation, separated by a non-contoured delimiting wall section.

8. A continuous-flow machine comprising at least one blade cascade as recited in claim 1 .

9. A blade cascade for a continuous-flow machine, comprising:
at least one blade channel delimited in a circumferential direction by a pressure-side wall of a first blade and by an opposite suction-side wall of an adjacent second blade and delimited in a radial direction by two opposite delimiting walls,
in the area of the pressure-side wall, at least one of the delimiting walls being provided with at least one pressure-side elevation and in the area of the suction-side wall, the at least one delimiting wall having at least one suction-side depression, a highest section of the at least one elevation and a lowest section of the at least one depression being located over an area of 30% to 60% of an extension of the blades in an axial direction, and wherein an axial position of the highest section and an axial position of the lowest section differ from each other at a maximum by 10% in the axial direction;
wherein, in the area of the pressure-side wall, a second pressure-side elevation is arranged downstream from the first elevation, the second elevation being at a distance from the first elevation, separated by a non-contoured delimiting wall section.

10. The blade cascade as recited in claim 9 wherein, as seen in the circumferential direction, the second elevation and a second suction-side depression, downstream from the first depression at a distance from the first depression separated by a non-contoured section of the delimiting wall, are at a distance from each other, separated by a non-contoured delimiting wall section.

11. The blade cascade as recited in claim 10 wherein a lowest section of the second depression is arranged downstream from the highest section of the second elevation.

12. The blade cascade as recited in claim 10 wherein the second elevation is arranged on the pressure-side wall and the second depression is arranged on the suction-side wall, upstream from the leading edges.

13. The blade cascade as recited in claim 9 wherein a lowest section of a second depression is arranged downstream from a highest section of the second elevation.

14. The blade cascade as recited in claim 9 wherein the second elevation is arranged on the pressure-side wall and a second depression is arranged on the suction-side wall, upstream from the leading edges.

Assignees

• MTU Aero Engines AG

Inventors

• Mahle Inga
• Brettschneider Markus

Classifications

• F01D5/143

  Contour of the outer or inner working fluid flow path wall, i.e. shroud or hub contour · CPC title

• Y02T50/673

  Cross-Sectional Technologies · mapped topic

• F01D5/145 Primary

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

• Y02T50/60

  Efficient propulsion technologies, e.g. for aircraft · CPC title