Airfoil cooling with internal cavity displacement features

Patent metadata

Field	Value
Publication number	US-10428686-B2
Application number	US-201415128492-A
Country	US
Kind code	B2
Filing date	May 8, 2014
Priority date	May 8, 2014
Publication date	Oct 1, 2019
Grant date	Oct 1, 2019

Abstract

A turbine airfoil including a central cavity defined by an outer wall including pressure and suction sides extending between and joined at leading and trailing edges, and a chordal axis extends generally centrally between the pressure and suction sides. Rib structures located in the central cavity define radial central channels extending across the chordal axis. Radial near wall passages are defined between the rib structures and each of the pressure and suction sides of the outer wall. The radial near wall passages are each open to an adjacent central channel along a radial extent of both the near wall passages and the adjacent central channel to define a radial flow pass associated with each central channel. The flow passes are connected in series to form a serpentine cooling path extending in the direction of the chordal axis.

First claim

What is claimed is:

1. A turbine airfoil including a central cavity defined by an outer wall including pressure and suction sides extending between and joined at leading and trailing edges, and a chordal axis extending generally centrally between the pressure and suction sides, the airfoil including: rib structures located in the central cavity and defining radial central channels, wherein each radial central channel extends across the chordal axis, wherein the rib structures include an enlarged main body extending across the chordal axis, wherein an axial dimension of the main body, parallel to the chordal axis, is greater than a circumferential dimension of the main body, perpendicular to the chordal axis; radial near wall passages defined between the rib structures and each of the pressure and suction sides of the outer wall, the near wall passages having an elongated dimension in a direction parallel to the chordal axis, the radial near wall passages are each open to an adjacent central channel along a radial extent of both the near wall passages and the adjacent central channel to define a radial flow pass associated with each central channel; the flow passes are connected in series to form a serpentine cooling path extending in the direction of the chordal axis, wherein at least one of the flow passes has a U-shaped flow cross-section defined by the respective near wall passages and the respective central channel.

2. The airfoil of claim 1 , wherein each of the central channels includes a length dimension, perpendicular to the chordal axis that is greater than a width dimension of the central channel, parallel to the chordal axis.

3. The airfoil of claim 2 , wherein the elongated dimension of the near wall passages is transverse to the length dimension of the central channels.

4. The airfoil of claim 1 , wherein a pair of near wall passages are open to a common central channel on opposing sides of the chordal axis.

5. The airfoil of claim 1 , wherein the rib structures include a pair of connector ribs associated with each main body, the pair of connecting ribs extending from the pressure and suction sides to opposing sides of the main body.

6. The airfoil of claim 5 , wherein the main bodies each include opposing end surfaces that extend between the opposing sides and that are spaced in the chordal direction, and the flow in the serpentine cooling path passes sequentially along each of the end surfaces of each main body.

7. The airfoil of claim 5 , wherein:
each connecting rib has a length dimension, in a direction perpendicular to the chordal axis, that is equal to a width dimension of an adjacent near wall passage, extending in a direction perpendicular to the chordal axis.

8. The airfoil of claim 5 , wherein one or more of the main bodies are formed with a hollow interior providing a supplemental cooling path for cooling fluid to pass radially through the rib structure between flow passes of the serpentine cooling path, the supplemental cooling path being separated from contact with the flow of cooling fluid in the serpentine cooling path.

9. The airfoil of claim 8 , wherein the airfoil is a stationary vane, wherein the supplemental cooling path defined by the hollow interior extends from an outer diameter to an inner diameter of the vane.

Assignees

• Siemens Energy Inc

Inventors

• Marsh Jan H
• Messmann Stephen John

Classifications

• F01D5/18

  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 title

• F05D2260/221

  Improvement of heat transfer · CPC title

• F01D5/188

  with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall · CPC title

• F01D5/187

  Convection cooling · CPC title

• F01D9/041

  using blades (F01D5/148 takes precedence) · CPC title