Ventilated high pressure blade of a helicopter turbine comprising an upstream duct and a central cooling chamber

Patent metadata

Field	Value
Publication number	US-11525360-B2
Application number	US-201816483828-A
Country	US
Kind code	B2
Filing date	Feb 5, 2018
Priority date	Feb 7, 2017
Publication date	Dec 13, 2022
Grant date	Dec 13, 2022

Abstract

A blade of a high-pressure turbine of a turboshaft engine, the blade including an airfoil extending in a spanwise direction, terminating in an apex and having a suction wall and a pressure wall joined by a leading edge and joined by a trailing edge. The blade further includes an internal cooling circuit having only an upstream duct and a central chamber for cooling the blade by circulating air. The upstream duct and the central chamber are separately supplied with air. The upstream duct being dedicated to the cooling of the leading edge and the suction wall, and the central chamber being dedicated to the cooling of the pressure wall and the trailing edge and being provided with bridge elements each connecting the pressure wall and the suction wall.

First claim

What is claimed is:

1. A blade for a high-pressure turbine of a turbine engine, comprising:
an airfoil extending in a spanwise direction, terminating in an apex and comprising a suction wall and a pressure wall joined at an upstream side by a leading edge and joined at a downstream side by a trailing edge;
an internal cooling circuit having only an upstream duct and a central chamber for cooling the blade by circulating air;
a plurality of disturbers projecting from the pressure wall and extending into the central chamber;
a plurality of pressure wall cooling holes formed in the pressure wall for cooling the trailing edge, the plurality of pressure wall cooling holes being arranged in separate first and second columns extending along the spanwise direction, the first and second columns being offset from one another in a direction perpendicular to the spanwise direction, and the second column being positioned closer to the trailing edge than the first column,
the upstream duct and the central chamber being separately supplied with air,
the upstream duct being dedicated to the cooling of the leading edge and the suction wall, and
the central chamber being dedicated to the cooling of the pressure wall and the trailing edge and being provided with bridge elements each connecting the suction wall and the pressure wall,
wherein each pressure wall cooling hole of the plurality of pressure wall cooling holes intersects an external face of the pressure wall by forming an ellipse having an orientation inclined towards the trailing edge and relative to a rotation axis, wherein each pressure wall cooling hole is inclined such that an outlet thereof is offset from an inlet thereof towards the apex and towards the trailing edge,
wherein the respective ellipses of the plurality of pressure wall cooling holes arranged in the first column have a greater angle of inclination with respect to the rotation axis than the respective ellipses of the plurality of pressure wall cooling holes arranged in the second column,
wherein the plurality of disturbers extend parallel to the rotation axis,
wherein the upstream duct and the central chamber are supplied by two inlets, respectively, located on a lower face of the root,
wherein for a section of the airfoil perpendicular to the spanwise direction at the lower face, an area of the inlet of the upstream duct is equal to an area of the inlet of the central chamber, and
wherein for any section of the airfoil perpendicular to the spanwise direction and beyond respective inlets of the upstream duct and the central chamber, a cross-sectional area of the upstream duct is less than or equal to one quarter of a corresponding cross-sectional area of the central chamber.

2. The blade according to claim 1 , wherein the root is prolonged by a platform supporting the airfoil, wherein the upstream duct narrows from its inlet to the platform, and wherein the central chamber widens from its inlet to the platform.

3. The blade according to claim 1 , each pressure wall cooling hole having a circular section and connecting the central chamber with an exterior of the blade by passing through the pressure wall, each pressure wall cooling hole extending from the respective inlet on an internal face of the pressure wall to the respective outlet on the external face of the pressure wall.

4. The blade according to claim 3 , wherein the respective angles of inclination of the pressure wall cooling holes arranged in the first column are oriented such that, the closer to the apex the pressure wall cooling hole is, the larger said angle of inclination is, and wherein the respective angles of inclination of the pressure wall cooling holes arranged in the second column are oriented such that, the closer to the apex the pressure wall cooling hole is, the larger said angle of inclination is.

5. The blade according to claim 1 , wherein the leading edge comprises a series of leading edge cooling holes each of which connects the upstream duct with an exterior of the blade, each leading edge cooling hole being inclined and comprising an outlet located on an external face of the leading edge, an inlet located on an internal face of the leading edge, each outlet of the respective leading edge cooling hole being closer to the apex than the respective inlet.

6. The blade according to claim 5 , wherein each leading edge cooling hole is inclined by an angle, the closer to the apex each leading edge cooling hole is, the larger said angle is.

7. The blade according to claim 1 , wherein the suction wall comprises a series of suction wall cooling holes for cooling the suction wall, each suction wall cooling hole having a section that increases from an inlet located on an inner face of the suction wall to an outlet located on an outer face of the suction wall.

8. The blade according to claim 7 , wherein each suction wall cooling hole has an average section, the further from the apex the suction wall cooling hole is, the larger said average section is.

9. The blade according to claim 1 , further comprising a plurality of ribs protruding from the pressure wall and extending into the upstream duct, wherein each rib of the plurality of ribs is inclined towards the leading edge and relative to the rotation axis.

10. The blade according to claim 1 , further comprising:
a first dust removal hole connecting the upstream duct to an exterior of the blade at the apex;
a second dust removal hole connecting the central chamber to the exterior of the blade at the apex; and
a third dust removal hole connecting the central chamber to the exterior of the blade at the apex,
wherein the second dust removal hole is interposed between the first and third dust removal holes, and wherein the second dust removal hole has a diameter less than respective diameters of the first and third dust removal holes.

11. A turbine comprising a blade according to claim 1 .

12. A helicopter comprising a turbine according to claim 11 .

Assignees

• Safran Helicopter Engines

Inventors

• Martineau Gontran
• Pardo Frédéric Philippe Jean-Jacques
• Pilette Kévin
• Sahores Jean-Luc Pierre
• Carbon Julien

Classifications

• Y02T50/60

  Efficient propulsion technologies, e.g. for aircraft · CPC title

• B64C27/18

  the means being jet-reaction apparatus · CPC title

• F05D2220/323

  for aircraft propulsion, e.g. jet engines · CPC title

• F01D5/186 Primary

  Film cooling (F01D5/187 takes precedence) · CPC title

• F05D2240/301

  Cross-sectional characteristics · CPC title