Compressor impeller blade with variable elliptic connection

• US 8,721,287 B2
• Filed: 05/14/2009
• Issued: 05/13/2014
• Est. Priority Date: 05/15/2008
• Status: Active Grant

• Current Assignee: Safran Helicopter Engines
• Original Assignee: Turbomeca
• Inventors: Billotey, Geoffroy Louis-Henri Marie, Biscay, Pierre, Cazenave-Larroche, Gilles, Ousty, Jean-Philippe
• Primary Examiner(s): VERDIER, CHRISTOPHER M
• Application Number:
  US12/990,953
• Publication Number:
  US 20110064583A1
• Time in Patent Office: 1,825 Days
• Field of Search: 415/204, 415/206, 416/183, 416/185, 416/186.R, 416/188, 416/223.B, 416/234, 416/DIG.2
• US Class Current: 416/185
• 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: F02C 3/08 the compressor comprising at least one radial stage F02C3/10 takes precedence
• CPC Class Codes: F04D 29/284 for compressors
• CPC Class Codes: F04D 29/30 Vanes
• CPC Class Codes: F05D 2250/14 elliptical
• CPC Class Codes: F05D 2250/71 curved
• CPC Class Codes: F05D 2260/94 Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF]
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A compressor impeller including at least one blade connected to an impeller hub via a junction of curved shape, the blade extending along a defined chord between a leading edge and a trailing edge of the blade. The junction presents the shape of an ellipse that varies along the chord.

Claims

1. A compressor impeller comprising:

at least one blade connected to an impeller hub by a junction of curved shape, the blade extending along a chord defined between a leading edge and a trailing edge of the blade, the junction presenting a shape that varies continuously along the chord,

wherein the junction is a portion of an ellipse, and

wherein, at the leading edge and at the trailing edge, the junction is tangential to the impeller hub and to a flank of the blade.

2. The compressor impeller according to claim 1, wherein the ellipse has a major axis and a minor axis, the junction being shaped such that at the leading edge, the major axis of the ellipse is substantially parallel to the flank of the blade, and at the trailing edge, the major axis of the ellipse is substantially perpendicular to the flank of the blade.

3. The compressor impeller according to claim 2, wherein the ratio of the major axis to the minor axis lies in a range of 1.1 to 4.

4. The compressor impeller according to claim 1, wherein the shape of the junction is caused to vary by causing lengths of axes of the ellipse to vary continuously.

5. A centrifugal compressor comprising an impeller according to claim 1.

6. A turbomachine comprising a compressor according to claim 5.