Turbomachine blade/vane for subsonic conditions

• US 5,228,833 A
• Filed: 06/23/1992
• Issued: 07/20/1993
• Est. Priority Date: 06/28/1991
• Status: Expired due to Fees

• Current Assignee: ASEA Brown Boveri SA de CV (ABB Limited)
• Original Assignee: ASEA Brown Boveri SA de CV (ABB Limited)
• Inventors: Steiger, Ulrich, Schonenberger, Martin, Lannefors, Nils, Havakechian, Said
• Primary Examiner(s): KWON, JOHN
• Application Number:
  US07/902,738
• Time in Patent Office: 392 Days
• Field of Search: 415/181, 415/191, 415/208.1, 415/914
• US Class Current: 415/181
• CPC Class Codes: F01D 5/141 Shape, i.e. outer, aerodynamic form F01D5/148 - F01D5/20 take precedence; blade construction F01D5/147
• CPC Class Codes: F01D 5/145 Means for influencing boundary layers or secondary circulations for compressors F04D29/68
• CPC Class Codes: Y10S 415/914 Device to control boundary layer

Abstract

In a turbomachine blade/vane for subsonic conditions with a convex curvature profile contour in the region of the leading edge and over the major part of the suction surface (S) and with a concave curvature profile contour in the region of the pressure surface (D), the profile contour in the suction-surface trailing edge region is designed to be concave (K). The momentum loss thickness mainly responsible for the profile loss is reduced in this region.

Claims

1. A turbomachine blade/vane for subsonic conditions with a convex curvature profile contour in the region of the leading edge and over the major part of the suction surface and with a concave curvature profile contour in the region of the pressure surface, the whole of the profile contour exhibiting a continuous curve, wherein the profile contour in the suction-surface trailing edge region is designed to be concave.

2. The turbomachine blade/vane as claimed in claim 1, wherein the concave section in the trailing edge region extends from the trailing edge a length between one and two times the distance of the throat between two adjacent blades/vanes arranged in a turbomachine.

3. A blade carrier for a turbomachine for subsonic conditions, comprising:

a blade carrier body;

a plurality of blades mounted on the body in a spaced, parallel relationship;

each blade mounted on the body so that adjacent blades form a flow region having a narrowest flow throat between a pressure surface trailing edge of a blade and a convex suction surface of an adjacent blade;

each blade having a continuous profile contour, a convex curvature in a region of a leading edge of the blade and over a major part of a suction surface of the blade, a concave curvature profile contour in a region of a pressure surface of the blade, and a concave profile surface in a trailing edge region of the suction surface, said trailing edge concave region extending from the trailing edge toward the leading edge a distance substantially equal to the distance between adjacent blades at the flow throat.