Blade cascade with side wall contours and continuous-flow machine

Patent metadata

Field	Value
Publication number	US-9453415-B2
Application number	US-201313955192-A
Country	US
Kind code	B2
Filing date	Jul 31, 2013
Priority date	Aug 2, 2012
Publication date	Sep 27, 2016
Grant date	Sep 27, 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 suction-side depression that, in the circumferential direction, is at a distance from a suction-side wall, and having a section located upstream from the leading edges and a section located downstream from the leading edges, it has a pressure-side elevation that makes a transition to a pressure-side wall and that is located in a front blade area, and it has a pressure-side depression that is located upstream from the pressure-side elevation, and also discloses a continuous-flow machine having such a blade cascade.

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 blade and by an opposite suction-side wall of an adjacent blade, and delimited in the radial direction by two opposite delimiting walls, and delimited in the direction of a main flow by leading edges and by trailing edges of the blades,
at least one of the delimiting walls being provided with at least one suction-side depression, at least one pressure-side elevation and a pressure-side depression,
the at least one suction-side depression being at a distance from the suction-side wall in the circumferential direction, a section of the at least one suction-side depression being arranged upstream from the leading edges and an other section of the at least one suction-side depression being arranged downstream from the leading edges,
the at least one pressure-side elevation transitioning into the pressure-side wall and being located in a front blade area, and
the pressure-side depression being located upstream from the at least one pressure-side elevation.

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

3. The blade cascade as recited in claim 1 wherein the at least one suction-side depression extends all the way to a largest curvature of the suction-side wall.

4. The blade cascade as recited in claim 1 wherein the at least one suction-side depression has a lowest section extending upstream and downstream from the leading edges.

5. The blade cascade as recited in claim 4 wherein a highest section of the at least one pressure-side elevation and the lowest section of the at least one suction-side depression are configured as plateaus, the highest section having a larger plateau surface than the lowest section.

6. The blade cascade as recited in claim 4 wherein the lowest section and a highest section of the at least one pressure-side elevation are each located at a radial position whose values are the same.

7. The blade cascade as recited in claim 1 wherein the at least one pressure-side elevation runs downstream along the pressure-side wall beyond the at least one suction-side depression, and a highest section of the at least one pressure-side elevation runs upstream all the way to the leading edge.

8. The blade cascade as recited in claim 7 wherein the highest section of the at least one pressure-side elevation and a lowest section of the at least one suction-side depression are configured as plateaus, the highest section having a larger plateau surface than the lowest section.

9. The blade cascade as recited in claim 7 wherein a lowest section of the at least one suction-side depression and the highest section are each located at a radial position whose values are the same.

10. The blade cascade as recited in claim 1 wherein the pressure-side and the at least one suction-side depressions start at a similar axial position in the flow direction.

11. The blade cascade as recited in claim 1 wherein the pressure-side depression is funnel-shaped and a lowest section is located radially outwards with respect to a lowest section of the at least one suction-side depression.

12. The blade cascade as recited in claim 1 wherein a suction-side elevation is provided on the suction-side wall downstream from the at least one suction-side depression.

13. The blade cascade as recited in claim 12 wherein, as seen in the circumferential direction, the at least one pressure-side elevation and suction side elevation transition into each other and end downstream at similar positions.

14. The blade cascade as recited in claim 12 wherein a highest section of the at least one pressure-side elevation is located radially outwards with respect to a highest section of the suction-side elevation, and has a larger surface area than the highest section of the suction-side elevation.

15. The blade cascade as recited in claim 1 wherein the inner delimiting wall has the at least one suction-side depression, pressure-side depression and the at least one pressure-side elevation and is configured to be non-contoured upstream from the at least one suction-side depression and pressure depression, and downstream from the trailing edges.

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

Assignees

• MTU Aero Engines AG
• Mtu Aero Engines Gmbh

Inventors

• Engel Karl

Classifications

• Y02T50/673

  Cross-Sectional Technologies · mapped topic

• F01D5/143 Primary

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

• F01D5/145

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

• F01D5/12 Primary

  Blades ({specially adapted for radial flow machines or engines F01D5/04}; blade roots F01D5/30; rotors with blades adjustable in operation F01D7/00; stator blades F01D9/02) · CPC title

• Y02T50/60

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