TURBINE NOZZLE SEGMENT AND CORRESPONDING GAS TURBINE ENGINE

• US 20130239541A1
• Filed: 10/27/2011
• Published: 09/19/2013
• Est. Priority Date: 11/25/2010
• Status: Abandoned Application

• Current Assignee: Siemens AG
• Original Assignee: Siemens AG
• Inventors: Shepherd, Andrew
• Application Number:
  US13/884,984
• Publication Number:
  US 20130239541A1
• Time in Patent Office: Days
• US Class Current: 60/39.83
• CPC Class Codes: F01D 5/143 Contour of the outer or inner working fluid flow path wall, i.e. shroud or hub contour
• CPC Class Codes: F01D 5/145 Means for influencing boundary layers or secondary circulations for compressors F04D29/68
• CPC Class Codes: F01D 9/041 using blades F01D5/148 takes precedence
• CPC Class Codes: F02C 7/12 Cooling of plants of component parts, see the relevant subclasses, e.g. F01D; cooling of engines in general F01P
• CPC Class Codes: F05D 2250/184 sinusoidal
• CPC Class Codes: F05D 2260/22141 using fins or ribs

Abstract

A turbine nozzle segment of a turbo-machine includes a platform defining a segment of a boundary for a main fluid path, the platform having a section, particularly a trailing section of the platform. The section has a surface along which a main fluid flows during operation of the turbo-machine. The surface further includes a plurality of alternating elevations and depressions, wherein the elevations and the depressions both are arranged substantially perpendicular to a direction of a main fluid flow of the main fluid.

Claims

1-11. -11. (canceled)

12. Turbine nozzle segment of a turbo-machine, comprising:

a platform defining a segment of a boundary for a main fluid path,

the platform comprising a trailing section,

the section comprising a surface, along which a main fluid flows during operation of the turbo-machine,

wherein the surface comprises alternating elevations and depressions, the alternating elevations and the depressions being arranged perpendicular to a direction of a main fluid flow of the main fluid.

13. The turbine nozzle segment according to claim 12, wherein the alternating elevations and the depressions are arranged such that a fraction of the fluid re-circulates along depression surfaces by having a motion backwards in respect of the direction of the main fluid flow and by sweeping along the surface in a region of the depressions.

14. The turbine nozzle segment according to claim 13,

wherein, in direction of the main fluid flow, a first elevation of the elevations is followed by a first depression of the depressions, and the first depression is followed by a second elevation,

wherein the first elevation, the first depression and the second elevation have a geometry such that the fraction of the fluid that has a backward motion blends again into the main fluid flow in a transition region between the first elevation and the first depression.

15. The turbine nozzle segment according to claim 12, wherein the alternating elevations and depressions are arranged such that the surface forms a wavelike profile.

16. The turbine nozzle segment according to claim 15, wherein the alternating elevations and depressions are arranged such that the surface forms a substantially sinusoidal profile in a cross-sectional plane, the cross-sectional plane being defined via the direction of main fluid flow and a direction substantially perpendicular to the surface.

17. The turbine nozzle segment according to claim 16, wherein the substantially sinusoidal profile has a sinusoid period length that is a plurality of a value of a sinusoid amplitude of the sinusoidal profile.

18. The turbine nozzle segment according to claim 12, wherein the surface comprises film cooling holes for injecting a film cooling fluid.

19. The turbine nozzle segment according to claim 12, wherein the surface is free of film cooling holes.

20. The turbine nozzle segment according to claim 12, further comprising:

a body, wherein the surface is formed onto the body by a layer of thermal barrier coating.

21. The turbine nozzle segment according to claim 20, further comprising:

a further surface being substantially opposite to the surface facing away from the surface, which is arranged to impingement cool the body of the turbo-machine component.

22. The turbine nozzle segment according to claim 12, wherein the turbine nozzle segment is a stator vane segment, the stator vane segment comprising at least one aerofoil.

23. Gas turbine engine, comprising:

a plurality of turbine nozzle segments arranged in a ring forming an annulus for guiding the main fluid, wherein each turbine nozzle segment is embodied according to claim 12.