Trailing edge cooling configuration for a gas turbine engine airfoil

Patent metadata

Field	Value
Publication number	US-10100645-B2
Application number	US-201213584172-A
Country	US
Kind code	B2
Filing date	Aug 13, 2012
Priority date	Aug 13, 2012
Publication date	Oct 16, 2018
Grant date	Oct 16, 2018

Abstract

An airfoil for a gas turbine engine includes pressure and suction surfaces provided by pressure and suction walls that extend in a radial direction and are joined at a leading edge and a trailing edge. A cooling passage is arranged between the pressure and suction walls and extends to the trailing edge. Elongated pedestals are arranged in the cooling passage and interconnect the pressure and suction walls. The elongated pedestals are spaced apart from one another in the radial direction and extend from a plane to the trailing edge. A metering pedestal includes at least a portion that is arranged between the plane and the trailing edge. The portion is provided between adjacent elongated pedestals in the radial direction.

First claim

What is claimed is:

1. An airfoil for a gas turbine engine comprising:
pressure and suction surfaces provided by pressure and suction walls extending in a radial direction and joined at a leading edge and a trailing edge;
a cooling passage arranged between the pressure and suction walls and extending to the trailing edge;
elongated pedestals arranged in the cooling passage and interconnecting the pressure and suction walls, the elongated pedestals spaced apart from one another in the radial direction and extending from a plane to the trailing edge;
a metering pedestal interconnecting the pressure and suction walls, the metering pedestal including at least a portion arranged between the plane and the trailing edge, the portion provided between adjacent elongated pedestals in the radial direction;
a thermal barrier coating in the trailing edge exit downstream from the metering pedestal without reaching the metering pedestal; and
wherein the elongated pedestals are spaced apart from one another between 0.045 inch (1.14 mm) and 0.075 inch (1.91 mm) in the radial direction.

2. An airfoil for a gas turbine engine comprising:
pressure and suction surfaces provided by pressure and suction walls extending in a radial direction and joined at a leading edge and a trailing edge;
a cooling passage arranged between the pressure and suction walls and extending to the trailing edge;
elongated pedestals arranged in the cooling passage and interconnecting the pressure and suction walls, the elongated pedestals spaced apart from one another in the radial direction and extending from a plane to the trailing edge;
a metering pedestal interconnecting the pressure and suction walls, the metering pedestal including at least a portion arranged between the plane and the trailing edge, the portion provided between adjacent elongated pedestals in the radial direction;
a thermal barrier coating in the trailing edge exit downstream from the metering pedestal without reaching the metering pedestal; and
wherein a trailing edge exit is provided between the elongated pedestals in the radial direction at the trailing edge, the trailing edge exit having an uncoated width of between 0.030 inch (0.76 mm) and 0.060 inch (1.52 mm).

3. An airfoil for a gas turbine engine comprising:
pressure and suction surfaces provided by pressure and suction walls extending in a radial direction and joined at a leading edge and a trailing edge;
a cooling passage arranged between the pressure and suction walls and extending to the trailing edge;
elongated pedestals arranged in the cooling passage and interconnecting the pressure and suction walls, the elongated pedestals spaced apart from one another in the radial direction and extending from a plane to the trailing edge;
a metering pedestal interconnecting the pressure and suction walls, the metering pedestal including at least a portion arranged between the plane and the trailing edge, the portion provided between adjacent elongated pedestals in the radial direction;
a thermal barrier coating in the trailing edge exit downstream from the metering pedestal without reaching the metering pedestal; and
wherein a trailing edge exit is provided between the elongated pedestals in the radial direction at the trailing edge, the trailing edge exit having an uncoated height of between 0.010 inch (0.25 mm) and 0.016 inch (0.41 mm).

Assignees

• Lewis Scott D
• Zess Gary A
• United Technologies Corp

Inventors

• Lewis Scott D
• Zess Gary A

Classifications

• F01D5/18 Primary

  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 title

• F01D5/288

  Protective coatings for blades · CPC title

• F05D2260/22141

  using fins or ribs · CPC title

• F05D2240/127

  Vortex generators, turbulators, or the like, for mixing · CPC title

• F01D5/187 Primary

  Convection cooling · CPC title