Tandem blade design

• US 8,573,941 B2
• Filed: 03/15/2010
• Issued: 11/05/2013
• Est. Priority Date: 03/16/2009
• Status: Active Grant

• Current Assignee: MTU Aero Engines GmbH (MTU)
• Original Assignee: MTU Aero Engines GmbH (MTU)
• Inventors: Hoeger, Martin
• Primary Examiner(s): VERDIER, CHRISTOPHER M
• Application Number:
  US13/145,753
• Publication Number:
  US 20110318172A1
• Time in Patent Office: 1,331 Days
• Field of Search: 415/119, 415/181, 415193-195, 415/199.4, 415/199.5, 415/209.1, 415/914, 416/198.A, 416/200.A, 416/201.R, 416/231.B, 416/223.A, 416/243, 416/DIG.2, 416/DIG.53
• US Class Current: 416/200.A
• CPC Class Codes: F01D 5/142 of the blades of successive rotor or stator blade-rows
• 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 21/00 Pump involving supersonic speed of pumped fluids
• CPC Class Codes: F04D 29/544 Blade shapes
• CPC Class Codes: F05D 2240/12 Fluid guiding means, e.g. vanes
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A tandem blade design for an axial turbomachine, comprising a front blade and a rear blade disposed with an offset thereto in the circumferential direction and in the axial direction. The rear blade is profiled and positioned with respect to the front blade such that it raises the speed level at the trailing edge of the front blade in a predetermined working range in interaction with the front blade.

Claims

1. A tandem blade design of an axial turbomachine comprising a front blade and a rear blade offset from the front blade in the circumferential and axial directions, wherein the rear blade is profiled and positioned relative to the front blade so that in the predetermined operating range the rear blade interacts with the front blade and raises the air speed level at the trailing edge of the front blade wherein the front and rear blades partially overlap viewed both in a flow direction and in the circumferential direction;

wherein the front blade has a convex curvature in its rear section such that in the predetermined operating range a flow detachment occurs at its suction face without interaction with the rear blade with a turbulent boundary layer;

wherein the suction face of the rear blade is in facing relation with the pressure face of the front blade and detachment of the flow at the suction face of the front blade can be prevented by the increase of the speed level brought about by the rear blade; and

wherein the rear blade has a small to negative curvature in its forward region, followed by a middle region with high curvature that together with the trailing edge of the front blade lies in a plane perpendicular to the flow wherein the front blade has a change of algebraic sign of the curvature on the pressure face upstream from the region of convex curvature.

2. The tandem blade design according to claim 1, wherein the curvature of the rear blade has a minimum curvature being smaller than 0.7 times the mean suction face curvature of the rear blade.

3. The tandem blade design according to claim 2, wherein the curvature of the middle region is about 1.3 times that of the mean curvature of the suction face of the rear blade.

4. The tandem blade design according to claim 3, wherein the forward region on the suction face of the rear blade extends upstream of the curvature maximum over about 2% to 30% of the chord length of the rear blade.

5. The tandem blade design according to claim 4, wherein the forward region on the suction face of the rear blade extends upstream of the point of maximum curvature in the middle region on the rear blade over about 25% of the chord length of the rear blade.

6. The tandem blade design according to claim 1, wherein the region of the convex curvature of the front blade extends over 50% to 100% of its chord length.

7. The tandem blade design according to claim 1, wherein the mean angle on the suction face of the front blade between 75% and 95% of the axial chord length is larger/the same as the mean angle on the suction face of the rear blade between the point of maximum curvature in the middle region and a point on the rear blade suction face 20% of the axial chord downstream from the point of maximum curvature, so that the outflow angle α

from the front blade is greater than the mean suction face angle of the rear blade downstream from a gap between the front blade and the rear blade.

8. The tandem blade design of claim 1, wherein the front blade and the rear blade form a tandem blade construction configured for use in a supersonic stator.