Hollow turbine blade with internal cooling system

• US 5,193,980 A
• Filed: 01/30/1992
• Issued: 03/16/1993
• Est. Priority Date: 02/06/1991
• Status: Expired due to Term

• Current Assignee: Snecma (Safran SA)
• Original Assignee: Societe Nationale D'Etude Et De Construction De Moteurs D'Aviation
• Inventors: Mortgat, Didier M., Kaincz, Christian, Miraucourt, Carmen, Mazeaud, Georges
• Primary Examiner(s): Look, Edward L.
• Assistant Examiner(s): VERDIER, CHRISTOPHER M
• Application Number:
  US07/828,104
• Time in Patent Office: 411 Days
• Field of Search: 415/115, 415/116, 416/96 R, 416/96 A, 416/97 R
• US Class Current: 416/97.00R
• CPC Class Codes: F01D 5/186 Film cooling F01D5/187 takes precedence
• CPC Class Codes: F01D 5/188 with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A hollow turbine blade equipped with a cooling system comprises a pair of internal partitions connected to the intrados and extrados walls of the blade and dividing the interior of the blade into at least one internal cavity extending from the root end to the tip end of the blade, a median partition connected to the two internal partitions to divide the cavity defined between the two internal partitions into two half-cavities, the median partition leaving an aperture at or near one end of the blade to establish communication between the two half-cavities, air inlet holes opening into the half-cavity on the intrados side of the median partition at or near the other end of the blade, air flow disturbing regions disposed on at least part of the internal face of the intrados wall opposite the median partition, and air outlet holes provided in the extrados wall opposite the median partition. Preferably each half-cavity is divided into two passages by half-partitions extending between the median partition and the intrados and extrados walls from root to tip of the blade.

Claims

1. A hollow turbine blade equipped with a cooling system, said blade comprising an intrados wall, an extrados wall, first and second ends respectively defining a root and a tip of said blade, two internal partitions connected to said intrados and extrados walls and dividing the interior of said blade into at least one internal cavity extending from said root to said tip of said blade, a median partition connected to said two internal partitions to divide the internal cavity defined between said two internal partitions into two half-cavities, said median partition leaving an aperture in the proximity of one of said ends of said blade to establish communication between said two half-cavities separated by said median partition, air inlet holes opening into said half-cavity on the intrados side of said median partition in the proximity of the other of said ends of said blade, air flow disturbing means disposed on at least part of the internal face of said intrados wall opposite said median partition, and air outlet holes provided in said extrados wall opposite said median partition.

2. A turbine blade according to claim 1, further comprising two transverse half-partitions connected to said median partition and respectively to said intrados and said extrados walls to divide each of said two half-cavities into two passages, each of said half-partitions extending from said first end to said second end of said blade.

3. A turbine blade according to claim 2, wherein said disturbing means are disposed on the internal face of said intrados wall facing both passages of said half-cavity on the intrados side of said median partition, said air inlet holes open into both said passages of said intrados half-cavity, and said air outlet holes communicate with both passages of said half-cavity on the extrados side of said median partition.

4. A turbine blade according to claim 1, wherein said median partition is formed by casting at the same time as the remainder of said blade.

5. A turbine blade according to claim 1, wherein said median partition is formed as a separate part, said part having two edges which are secured in a sealed manner to said two internal partitions.

6. A turbine blade according to claim 2, wherein said median partition and said two transverse half-partitions are formed by casting at the same time as the remainder of said blade.

7. A turbine blade according to claim 2, wherein said median partition and said transverse half-partitions are formed as a single part which is secured in a sealed manner to said internal partitions and to said intrados and extrados walls.

8. A turbine blade according to claim 2, wherein said transverse half-partitions are formed by casting at the same time as the remainder of said blade, and said median partition is formed by two separate parts secured in a sealed manner to said transverse half-partitions and to said internal partitions.

9. A turbine blade according to claim 1, wherein said disturbing means are formed by a corrugated surface on the inner face of said intrados wall.

10. A turbine blade according to claim 1, wherein said disturbing means comprise roughening formed on the inner face of said intrados wall.