Blade group arrangement as well as turbomachine

• US 9,470,091 B2
• Filed: 02/06/2013
• Issued: 10/18/2016
• Est. Priority Date: 02/10/2012
• Status: Active Grant

• Current Assignee: MTU Aero Engines GmbH (MTU)
• Original Assignee: MTU Aero Engines GmbH (MTU)
• Inventors: Gomez, Sergio Elorza, Hergt, Alexander, Siller, Ulrich, Schneider, Tim
• Primary Examiner(s): White, Dwayne J
• Assistant Examiner(s): Mikus, Jason
• Application Number:
  US13/760,580
• Publication Number:
  US 20130209259A1
• Time in Patent Office: 1,350 Days
• Field of Search: 416/200.A, 416/198.A, 415/193
• US Class Current: 1/1
• CPC Class Codes: F01D 5/022 with concentric rows of axial blades
• CPC Class Codes: F01D 5/146 of blades with tandem configuration, split blades or slotted blades
• CPC Class Codes: F01D 9/041 using blades F01D5/148 takes precedence
• CPC Class Codes: F04D 29/324 Blades
• CPC Class Codes: F04D 29/542 Bladed diffusers fixing blades to stators F01D9/042
• CPC Class Codes: F04D 29/544 Blade shapes
• CPC Class Codes: F04D 29/563 specially adapted for elastic fluid pumps
• CPC Class Codes: F05D 2240/301 Cross-sectional characteristics
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A blade group arrangement for a turbomachine in order to form a blade-row group, whereby a front blade and a rear blade each form an overlapping area that has a contraction ratio of at least 1.2, and it also relates to a turbomachine having such a contraction ratio between a front blade and a rear blade.

Claims

1. A blade group arrangement for a turbomachine in order to form a blade-row group, comprising:

a front blade and a rear blade arranged offset from each other in the axial and circumferential directions and forming an overlapping area running between a pressure side of the front blade and a suction side of the rear blade, the front and rear blades in the overlapping area converging with a contraction ratio KV of KV≧

1.2 between an inlet surface D_min,1 defined as a smallest distance between a leading edge of the rear blade and the pressure side of the front blade, and an outlet surface D_min,2 defined as a further smallest distance between the suction side of the rear blade and the pressure side of the front blade.

2. The blade group arrangement as recited in claim 1 wherein the contraction ratio KV is ≦

2.8.

3. The blade group arrangement as recited in claim 1 wherein the contraction ratio KV=1.7.

4. The blade group arrangement as recited in claim 1 wherein the suction side of the rear blade has a greater curvature downstream from the outlet surface D_min,2 than upstream from the outlet surface D_min,2.

5. The blade group arrangement as recited in claim 4 wherein the curvature has a maximum ranging from 1.6 to 1.7 times a mean curvature of the suction side of the rear blade.

6. The blade group arrangement as recited in claim 5 wherein the curvature maximum amounts to approximately 5% to 25% of a relative skeleton line length behind the outlet surface D_min,2.

7. A turbomachine comprising at least one blade-row group having a plurality of blade group arrangements as recited in claim 1.