STATOR VANE FOR A GAS TURBINE ENGINE

• US 20100150710A1
• Filed: 12/23/2009
• Published: 06/17/2010
• Est. Priority Date: 06/28/2007
• Status: Active Grant

• Current Assignee: General Electric Technology GmbH (GE Vernova, Inc.)
• Original Assignee: Alstom Technology Ltd. (Alstom SA)
• Inventors: Kurganov, Igor, Odinokov, Victor, Khanin, Alexander, Vorontsov, Sergey
• Granted Patent: US 8,152,454 B2
• Time in Patent Office: Days
• US Class Current: 415/208.100
• CPC Class Codes: F01D 11/005 Sealing means between non relatively rotating elements
• CPC Class Codes: F01D 9/041 using blades F01D5/148 takes precedence
• CPC Class Codes: F05D 2230/10 by removing material
• CPC Class Codes: F05D 2240/11 Shroud seal segments
• CPC Class Codes: F05D 2240/57 Leaf seals
• CPC Class Codes: F05D 2240/80 Platforms for stationary or moving blades
• CPC Class Codes: F05D 2250/29 machined; miscellaneous

Abstract

A guide vane for a gas turbine includes a vane body having a leading edge and a trailing edge and a shroud extending at least between the leading edge and the trailing edge. The shroud has a first side wall and a second side wall extending essentially radially and in a longitudinal direction of the gas turbine. The first side wall has a groove disposed in a region of the trailing edge extending in a longitudinal direction of the shroud and is configured to receive a sealing plate. The first side wall also has a clearance extending from the groove in a region of the trailing edge, wherein a depth of the clearance in a circumferential direction of the gas turbine is equal to a depth of the groove, and wherein a width of the clearance in the longitudinal direction of the shroud is between one to three times the depth of the clearance.

Claims

1. A guide vane for a gas turbine comprising:

a vane body having a leading edge and a trailing edge; and

a shroud extending at least between the leading edge and the trailing edge, the shroud having a first side wall and a second side wall extending essentially radially and in a longitudinal direction of the gas turbine, the first side wall having a groove disposed in a region of the trailing edge extending in a longitudinal direction of the shroud and configured to receive a sealing plate, the first side wall further having a clearance extending from the groove in a region of the trailing edge, wherein a depth of the clearance in a circumferential direction of the gas turbine is equal to a depth of the groove, and wherein a width of the clearance in the longitudinal direction of the shroud is between one to three times the depth of the clearance.

2. The guide vane as recited in claim 1, wherein the shroud is disposed radially outwardly with respect to the vane body.

3. The guide vane as recited in claim 1, wherein the clearance extends radially outward at right angles with respect to the groove.

4. The guide vane as recited in claim 1, wherein the clearance is disposed essentially aligned with the trailing edge in the longitudinal direction of the shroud.

5. The guide vane as recited in claim 1, wherein a distance between the trailing edge and the clearance in the circumferential direction of the gas turbine is less than or equal to the depth of the groove.

6. The guide vane as recited in claim 1, wherein a profile of the clearance has a rectangular shape.

7. The guide vane as recited in claim 1, wherein the side of the shroud opposite the clearance includes an elevation in a region of the clearance.

8. The guide vane as recited in claim 1, wherein the clearance is disposed in a radial inner portion of the shroud and extends radially inward essentially at a right angle with respect to the groove.