Film-cooled gas turbine component

Patent metadata

Field	Value
Publication number	US-10352174-B2
Application number	US-201515539259-A
Country	US
Kind code	B2
Filing date	Dec 16, 2015
Priority date	Jan 9, 2015
Publication date	Jul 16, 2019
Grant date	Jul 16, 2019

Abstract

A film-cooled gas turbine component for a gas turbine has a surface exposed to a hot gas and a number of film-cooling openings open out, which film-cooling openings combined to form at least one row transverse to a flow direction of the hot gas. Each of the film-cooling openings has a duct section and a diffuser section having an upstream diffuser edge, two diffuser longitudinal edges and a downstream diffuser edge. At least two immediately adjacent film-cooling openings, of the respective row have their duct axes of the respective duct sections laterally inclined relative to the local flow direction of the hot gas and their diffuser sections are formed asymmetrically with respect to a projection of the duct axis, such that immediately adjacent corner regions of the respective film-cooling openings are in alignment without the respective diffuser sections making contact with one another.

First claim

The invention claimed is:

1. A gas turbine component for a gas turbine, comprising:
a surface to be exposed to a hot gas and in which a number of film-cooling openings open out, wherein the number of film-cooling openings combine to form at least one row in a direction transverse to a flow direction of the hot gas,
wherein each of the respective film-cooling openings comprises, along its throughflow direction, a duct section and a diffuser section directly adjoining the duct section, wherein each diffuser section comprises an upstream diffuser edge, two diffuser longitudinal edges and a downstream diffuser edge, and wherein in each diffuser section each diffuser longitudinal edge intersects the downstream diffuser edge at a respective corner region, and
wherein at least two immediately adjacent film-cooling openings of the at least one row are designed such that duct axes of the respective duct sections are laterally inclined relative to a local flow direction of the hot gas and the diffuser sections are formed in each case asymmetrically with respect to a projection of a duct axis and in such a way that when viewing the at least two immediately adjacent film-cooling openings from above the surface, immediately adjacent corner regions of the at least two immediately adjacent film-cooling openings are laterally aligned with the local flow direction, or laterally overlap each other perpendicular to the local flow direction, without the respective diffuser sections making contact with one another.

2. The gas turbine component as claimed in claim 1 ,
in which the respective diffuser sections equate to impressions of a diffuser volume in a shape of a halved truncated pyramid, a volume of which is rotated through an angle of rotation (γ) about the duct axis from a position of symmetry of the diffuser volume in order to form the asymmetry.

3. The gas turbine component as claimed in claim 2 ,
in which the angle of rotation (γ) amounts to 15°.

4. The gas turbine component as claimed in claim 3 ,
in which the downstream diffuser edge of the respective diffuser section forms an angle (α) with the local flow direction which differs from 90°.

5. The gas turbine component as claimed in claim 1 ,
in which the upstream diffuser edge, one diffuser longitudinal edge of the two diffuser longitudinal edges, the two diffuser longitudinal edges, or the downstream diffuser edge of the respective diffuser section are substantially rectilinear.

6. The gas turbine component as claimed in claim 1 ,
in which the respective duct axes are inclined by an angle of inclination (β) of 50° with respect to the local flow direction of the hot gas.

7. The gas turbine component as claimed in claim 1 ,
which is designed as a cooled turbine rotor blade comprising an aerodynamically profiled blade airfoil, which blade airfoil comprises a suction-side wall and a pressure-side wall which both—in relation to profile chords of the blade airfoil—extend from a leading edge of the blade airfoil to a trailing edge of the blade airfoil and—in relation to a radial direction—extend from a hub-side end to a freely ending blade airfoil tip,
wherein, on the blade airfoil tip, at least on a pressure side, there is provided a rubbing edge,
wherein the at least one row of the number of film-cooling openings is distributed at the pressure side along a respective profile chord at an approximately constant distance from the rubbing edge for the cooling thereof.

8. The gas turbine component as claimed in claim 7 ,
in which, with decreasing distance from the trailing edge, respective spacings between two immediately adjacent film-cooling openings increase.

9. The gas turbine component as claimed in claim 7 ,
in which, with decreasing distance from the trailing edge, the duct axes are slanted to an increasing degree with respect to the trailing edge.

10. The gas turbine component as claimed in claim 1 ,
wherein all film-cooling openings of the at least one row are designed such that the duct axes of the respective duct sections are laterally inclined relative to a respective local flow direction of the hot gas, and the diffuser sections are formed in each case asymmetrically with respect to the projection of the duct axis and in such a way that when viewing from above the surface, immediately adjacent corner regions of adjacent diffuser sections of the number of film-cooling openings are laterally aligned with each other along the respective local flow direction, or laterally overlap each other along the respective local flow direction, and are located at different positions along the respective local flow direction, without the adjacent diffuser sections making contact with one another.

11. A gas turbine component for a gas turbine, comprising:
a surface to be exposed to a hot gas and comprising a number of film-cooling openings that combine to form at least one row in a direction transverse to a flow direction of the hot gas,
wherein each film-cooling opening comprises a duct section and a diffuser section directly adjoining the duct section,
wherein for each pair of immediately-adjacent diffuser sections there is a respective local flow direction of the hot gas over the pair,
wherein each diffuser section comprises an upstream diffuser edge and a downstream diffuser edge relative to the respective local flow direction,
wherein immediately-adjacent diffuser sections do not contact one another, and
wherein when viewing each pair of immediately-adjacent diffuser sections from above the surface, immediately-adjacent ends of the immediately-adjacent downstream diffuser edges are laterally aligned with the respective local flow direction or laterally overlap each other perpendicular to the local flow direction, and the immediately-adjacent ends are located at different positions along the local flow direction.

12. The gas turbine component for a gas turbine as claimed in claim 11 , wherein each of the immediately-adjacent downstream diffuser edges is positioned obliquely relative to the respective local flow direction.

13. The gas turbine component for a gas turbine as claimed in claim 11 , comprising an airfoil comprising the surface to be exposed to the hot gas.

14. The gas turbine component for a gas turbine as claimed in claim 13 , wherein the at least one row is disposed along and configured to film cool a rubbing edge at a tip of the airfoil.

15. A gas turbine component for a gas turbine, comprising:
a surface to be exposed to a hot gas and in which a number of film-cooling openings open out, wherein the number of film-cooling openings combine to form at least one row in a direction transverse to a local flow direction of the hot gas,
wherein each of the respective film-cooling openings comprises, along its throughflow direction, a duct section and a diffuser section directly adjoining the duct section, wherein each diffuser section comprises an upstream diffuser edge, two diffuser longitudinal edges and a downstream diffuser edge, and wherein in each diffuser section each diffuser longitudinal edge intersects the downstream diffuser edge at a respective corner region,
wherein at least two immediately adjacent film-cooling openings of the at least one row are designed such that duct axes of the respective duct sections are laterally inclined relative to the local flow direction of the hot gas and the diffuser sections are formed in each case asymmetrically with respect to a projection of a duct axis and in such a way that immediately adjacent corner regions of the at least two immediately adjacent film-cooling openings are in alignment, or overlap, as vi

Assignees

• Siemens Ag

Inventors

• Heselhaus Andreas

Classifications

• F05D2260/202

  by film cooling · CPC title

• F05D2250/38

  angled, e.g. sweep angle · CPC title

• F05D2250/21

  pyramidal · CPC title

• F05D2250/13

  trapezoidal · CPC title

• F01D5/20

  Specially-shaped blade tips to seal space between tips and stator {(F01D5/225 takes precedence)} · CPC title