Blade channel, blade cascade and turbomachine

Patent metadata

Field	Value
Publication number	US-10458248-B2
Application number	US-201615365339-A
Country	US
Kind code	B2
Filing date	Nov 30, 2016
Priority date	Dec 4, 2015
Publication date	Oct 29, 2019
Grant date	Oct 29, 2019

Abstract

A blade channel of a turbomachine that is delimited in the circumferential direction of the turbomachine by a pressure side of an airfoil and by an opposite suction side of an adjacent airfoil that, in the radial direction of the turbomachine, is delimited by two opposing side walls, and whose extent in the axial direction of the turbomachine is delimited by leading edges and by trailing edges of airfoils; at least one of the side walls being provided with localized contours, of which at least two are formed as elevations and at least two as depressions; a saddle surface being formed between the contours that, in one rotation, alternately merges into an elevation and a depression; a blade cascade having such blade channels, as well as a turbomachine having such a blade cascade.

First claim

What is claimed is:

1. A blade channel of a turbomachine comprising:
in a circumferential direction of the turbomachine, a pressure side of an airfoil and an opposite suction side of an adjacent airfoil,
two opposing side walls,
the blade channel having an extent in the axial direction of the turbomachine delimited by leading edges and by trailing edges of the airfoil and the adjacent airfoil,
at least one of the side walls being provided with localized contours, at least two of the localized contours being formed as elevations and at least two further of the localized contours as depressions;
a saddle surface being formed between the localized contours so that, in one revolution, the saddle surface alternately merges into one of the elevations and one of the depressions; wherein the elevations are configured relative to each other in the circumferential direction, and the depressions are configured relative to each other in the axial direction and wherein a leading depression of the depressions is configured close to the suction side, and a trailing depression of the depressions is configured on the pressure side, the saddle surface being in an intersecting region of the localized contours.

2. The blade channel as recited in claim 1 wherein the saddle surface being located within a range of 30% to 70% of an axial channel extent.

3. The blade channel as recited in claim 1 wherein the saddle surface is located within a range of 40% to 60% of an axial channel extent.

4. The blade channel as recited in claim 1 wherein the saddle surface is situated circumferentially in the middle between the airfoil and the adjacent airfoil.

5. The blade channel as recited in claim 1 wherein the elevations have different heights or the depressions have different depths.

6. The blade channel as recited in claim 1 wherein by a maximum thereof, a pressure-side elevation of the elevations is contiguous to the pressure side, and, by another maximum thereof, a suction-side elevation of the elevations is contiguous to the suction side.

7. The blade channel as recited in claim 6 wherein the pressure-side elevation begins upstream of the suction-side elevation, and the suction-side elevation ends downstream of the pressure-side elevation.

8. The blade channel as recited in claim 1 wherein the depressions are positioned relative to each other in axial direction, and extend by respective longitudinal axes parallel to a mean camber line of the adjacent airfoil.

9. The blade channel as recited in claim 1 wherein the leading depression begins upstream of a pressure-side elevation of the elevations, and the trailing depression ends downstream of a suction-side elevation of the elevations.

10. A blade cascade of a turbomachine comprising a plurality of blade channels as recited in claim 1 .

11. A turbomachine comprising at least one blade cascade as recited in claim 10 .

Assignees

• MTU Aero Engines AG

Inventors

• Wolfrum Nina
• Brettschneider Markus
• Mahle Inga
• Schlemmer Markus
• Pernleitner Martin

Classifications

• B63H1/26

  Blades · CPC title

• F01D5/02

  Blade-carrying members, e.g. rotors (rotors of non-bladed type F01D1/34; stators F01D9/00 {; selecting particular materials F01D5/28}) · CPC title

• F05D2220/30

  in turbines · CPC title

• B63H21/00

  Use of propulsion power plant or units on vessels · CPC title

• F01D5/145 Primary

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