Modulated turbine vane cooling

Patent metadata

Field	Value
Publication number	US-9670797-B2
Application number	US-201213630681-A
Country	US
Kind code	B2
Filing date	Sep 28, 2012
Priority date	Sep 28, 2012
Publication date	Jun 6, 2017
Grant date	Jun 6, 2017

Abstract

A vane structure includes a baffle movably mounted within an aperture, the baffle movable to control a cooling flow between a first cooling cavity and a second cooling cavity.

First claim

What is claimed is:

1. A vane structure for a gas turbine engine comprising:
an airfoil section which defines an aperture, said aperture circular in cross-section;
a baffle movably mounted within said aperture, said baffle circular in cross-section and configured to rotate about an axis;
a first cooling cavity in communication with said aperture;
a second cooling cavity in communication with said aperture; and
a third cooling cavity in communication with said aperture,
wherein said first cooling cavity defines film cooling cavities,
wherein said second cooling cavity defines convective cooling and rotor purge feed cavities, and
wherein said third cooling cavity defines convective cooling cavities.

2. The vane structure as recited in claim 1 , wherein said baffle includes a plurality of baffle holes along a length of the baffle and terminates in a vane platform segment to block a distal end of the baffle such that a cooling airflow is configured to be communicated through the plurality of baffle holes.

3. The vane structure as recited in claim 1 , further comprising:
a vane platform segment,
wherein said baffle terminates in the vane platform segment and includes a plurality of baffle holes along a length of the baffle.

4. A method of communicating a cooling airflow comprising:
rotating a baffle within an aperture of an airfoil section of a turbine vane about an axis, wherein the turbine vane includes:
a first cooling cavity in communication with said aperture;
a second cooling cavity in communication with said aperture; and
a third cooling cavity in communication with said aperture,

wherein said first cooling cavity defines film cooling cavities,
wherein said second cooling cavity defines convective cooling and rotor purge feed cavities, and
wherein said third cooling cavity defines convective cooling cavities.

5. The method as recited in claim 4 , further comprising:
rotating the airfoil section of the turbine vane.

6. The method as recited in claim 4 , further comprising:
distributing a cooling airflow between the film cooling cavities and the convective cooling cavities.

7. The method as recited in claim 4 , further comprising:
distributing a cooling airflow 80%-20% between the film cooling cavities and the convective cooling cavities with the baffle.

8. The method as recited in claim 4 , further comprising:
distributing a cooling airflow 20%-80% between the film cooling cavities and the convection cooling cavities with the baffle.

9. The method as recited in claim 4 , further comprising:
blocking a cooling airflow 20%-80% between the film cooling cavities and the convection cooling cavities with the baffle.

10. The method as recited in claim 4 , wherein said baffle terminates in a vane platform segment and includes a plurality of baffle holes along a length of the baffle.

Assignees

• Slavens Thomas N
• Pietraszkiewicz Edward F
• Martin Thomas J
• Zelesky Mark F
• Gautschi Steven B
• Devore Matthew A
• Staroselsky Alexander
• United Technologies Corp

Inventors

• Slavens Thomas N
• Pietraszkiewicz Edward F
• Martin Thomas J
• Zelesky Mark F
• Gautschi Steven B
• Devore Matthew A
• Staroselsky Alexander

Classifications

• F01D9/065

  Fluid supply or removal conduits traversing the working fluid flow, e.g. for lubrication-, cooling-, or sealing fluids (see also F01D25/16, F01D25/24 and F01D25/26) · CPC title

• F01D25/12 Primary

  Cooling · CPC title

• F05D2220/32

  in gas turbines · CPC title

• F01D5/187

  Convection cooling · CPC title

• F01D9/04

  forming ring or sector · CPC title