Turbine blade with cooling and with improved service life

• US 7,670,112 B2
• Filed: 12/04/2006
• Issued: 03/02/2010
• Est. Priority Date: 12/05/2005
• Status: Active Grant

• Current Assignee: Safran Aircraft Engine Company
• Original Assignee: Snecma (Safran SA)
• Inventors: Moreau, Guy, Boury, Jacques Auguste Amedee, Eneau, Patrice
• Primary Examiner(s): Look; Edward
• Assistant Examiner(s): Ellis; Ryan H
• Application Number:
  US11/566,423
• Publication Number:
  US 20070128036A1
• Time in Patent Office: 1,184 Days
• Field of Search: 415/115, 416/96.R, 416/97.R
• US Class Current: 416/97.00R
• CPC Class Codes: F01D 5/18 Hollow blades, i.e. blades with cooling or heating channels or cavities structure of hollow blades in general F01D5/147; Heating, heat-insulating or cooling means on blades
• CPC Class Codes: F01D 5/186 Film cooling F01D5/187 takes precedence
• CPC Class Codes: F05D 2260/20 Heat transfer, e.g. cooling
• CPC Class Codes: F05D 2260/202 by film cooling
• CPC Class Codes: F05D 2260/22141 using fins or ribs
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A turbine blade, including an intrados wall, an extrados wall, at least one first radial trailing edge cavity, at least one second radial cavity upstream of the trailing edge cavity, an internal wall separating the radial cavities and with at least one channel connecting the cavities to one another, the channel being oriented in an axis intersecting the internal surface of the intrados wall.

Claims

1. A moving blade of a turbine comprising an intrados wall, an extrados wall, at least one first radial trailing edge cavity, at least one second radial cavity upstream of the trailing edge cavity, an internal wall separating the radial cavities and containing at least one channel connecting the cavities to one another, the channel being oriented in an axis intersecting the internal surface of the intrados wall in the first radial trailing edge cavity, wherein the upstream extremity of the channel is connected at its outlet in the radial cavity, on the one hand, to the internal surface of the extrados wall via a throat having an upstream extrados radius of curvature and, on the other hand, to the internal surface of the intrados wall via a rounded area and a throat having an upstream intrados of curvature, wherein said upstream extrados radius of curvature is larger than said upstream intrados radius of curvature, said throat being a vertex of an angle formed by the upstream extremity of the channel and the internal wall of the extrados wall and

whereas the downstream extremity of the channel is connected at its outlet in the radial trailing edge cavity, on the one hand, to the internal surface of the intrados wall via a throat having a downstream intrados radius of curvature and, on the other hand, to the internal surface of the extrados wall via a rounded area and a throat having a downstream extrados radius of curvature, wherein said downstream intrados radius of curvature is larger than said downstream extrados radius of curvature.

2. The turbine blade as claimed in claim 1, wherein the said axis is inclined at an angle (α

) in the range between 5° and

70°

in relation to a tangent to a portion of a camber surface of the blade, said portion of the camber surface being located in the interior of the channel.

3. The turbine blade as claimed in claim 2, wherein said angle (α

) lies in the range between 5° and

35°

.

4. The turbine blade as claimed in claim 3, wherein the angle (α

) is equal to 25°

.

5. The turbine blade as claimed in claim 1, wherein the channel comprises a guiding length (L) and a guiding width (l), the ratio of the guiding length (L) to the guiding width (l) being greater than 1.

6. The turbine blade as claimed in claim 5, wherein the ratio of the guiding length (L) to the guiding width (l) is greater than 1.5.

7. The turbine blade as claimed in claim 1, wherein at least one internal surface of the radial trailing edge cavity includes perturbators.

8. A turbine including at least one turbine blade as claimed in claim 1.

9. A turbo machine including a turbine as claimed in claim 8.

10. The turbine blade as claimed in claim 1, wherein the upstream extremity of the channel discharges to define an angle (β

) with the axis of the channel lying in a range between 90° and

120°

.