Device for cooling a component of a gas turbine/turbo machine by means of impingement cooling

Abstract

A device for cooling a component to be cooled of a gas turbine/turbo machine having a hot-gas-impinged outer surface, a target surface of the component, and an integrated cooling passage, includes: an impingement cooling element arranged within the cooling passage, the impingement cooling element having plural impingement cooling bores; and a surface structure arranged on the target surface. The impingement cooling element is spaced apart from the target surface of the component and configured so as to conduct a cooling fluid as an impingement cooling jet is onto the target surface, such that the impingement cooling jet impinges on the surface structure.

Claims

1. A device for cooling a component (1) to be cooled of a gas turbine/turbo machine having a hot-gas-impinged outer surface (2), a target surface (6) of the component (1), and an integrated cooling passage (3), comprising: an impingement cooling element (4) arranged within the cooling passage (3), the impingement cooling element (4) having plural impingement cooling bores (5); and a surface structure (8) arranged on the target surface (6), the surface structure (8) comprising stellate ribs (9), which ribs protrude from the target surface (6), the stellate ribs (9) run, spaced apart from a central point (Z) located opposite a respective impingement cooling bore (5), radially to the outside, the stellate ribs (9) together forming first and second radial arrangements, the first radial arrangement consisting of drop-shaped ribs, whose shape tapers radially towards the outside, and the second radial arrangement consisting of linear, rod-shaped ribs, the drop-shaped ribs and the linear, rod-shaped ribs being arranged in alternating fashion, wherein the distance from the radially innermost tip of each drop-shaped rib to the central point (Z) corresponds to approximately 75% of the length of the drop-shaped rib, and wherein the distance from the radially innermost tip of each linear, rod-shaped rib to the central point (Z) corresponds to approximately 150% of the length of the linear, rod-shaped rib, and wherein the impingement cooling element (4) is spaced apart from the target surface (6) of the component (1) and configured so as to conduct a cooling fluid as an impingement cooling jet onto the target surface (6), such that the impingement cooling jet impinges on the surface structure (8).

2. The device according to claim 1, wherein star-like arrangements out of the ribs (9) are arranged on the target surface (6) in a row opposite a corresponding row of the impingement cooling bores (5).

3. The device according to claim 1, wherein side flanks of the ribs (9) run orthogonally at least at a connection to the target surface (6) and are arranged obliquely or rounded only at a transition to a shroud side (10).

4. The device for cooling a component (1) of a gas turbine/turbo machine according to claim 3, wherein the shroud side (10) is flat and parallel to the target surface (6).

5. A gas turbine/turbo machine having the device according to claim 1.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

(1) Other advantageous further developments of the invention are shown in more detail in the following by way of the figures or together with the description of the preferred embodiment of the invention. In the drawings:

(2) FIG. 1 is a sectional view of a gas turbine component with a surface structure on the target surface of the impingement cooling;

(3) FIG. 2 is a perspective view of a target surface with ribs arranged in one row, and

(4) FIG. 3 a perspective view of a target surface with ribs arranged in multiple rows.

DETAILED DESCRIPTION OF THE PRESENTLY PREFERRED EMBODIMENTS

(5) FIG. 1 is a sectional view of a gas turbine component 1 having a device for impingement cooling, which comprises a surface structure 8 on the target surface 6 of the impingement cooling arrangement.

(6) The gas turbine component 1 comprises an outer surface 2 that is impinged by hot gas during operation and an integrated cooling passage 3 for cooling. An impingement cooling element 4, which divides the cooling passage 3 into a supply part 11 for coolant supply and a cooling part 12, in which the target surface 6 to be cooled is arranged, runs within the cooling passage 3. The impingement cooling element 4 is spaced apart from the target surface 6 to be cooled in the cooling part 12 of the component 1. Furthermore, the impingement cooling element 4 comprises four impingement cooling bores 5 in the shown region, via which a cooling fluid is conductible as an impingement cooling jet for cooling the component 1 onto a central point Z of the target surface 6 located opposite the impingement cooling bore 5.

(7) A perspective view of a target surface 6 with ribs 9 arranged in multiple rows is shown in FIG. 2. The surface structure 8 corresponds to the representation shown in FIG. 1 and described in the following.

(8) The surface structure 8, which the impingement cooling jet impinges on, is formed on the target surface 6. This surface structure 8 is formed by stellate ribs 9 each alternating in a different form, which protrude from the target surface 6. Spaced apart from the central point Z located opposite the impingement cooling bore 5, the ribs 9 run radially to the outside. The radial arrangement out of the ribs 9 on the target surface 6 are formed and arranged in a row opposite a corresponding row of impingement cooling bores 5. The side flanks of the ribs 9 run orthogonally at the juncture to the target surface 6 and are formed obliquely and rounded only at the transition towards a shroud side 10. Apart from this, the respective alternating ribs 9 have a different length and height with which the ribs extend on the target surface 6. One of the two radial arrangements comprises drop-shaped ribs 9 which taper towards the outside, and the distance of the start of each rib 9 located radially inside to the central point Z approximately corresponds to 75% of the length of this rib 9. By contrast, the ribs 9 of the other radial arrangement have a linear, rod-shaped form and the distance of the start of each rib 9 located radially inside to the central point Z corresponds approximately to 150% of the length of this rib 9. The shroud side 10 of the ribs 9 is formed flat and parallel to the target surface 6.

(9) FIG. 3 shows a perspective view of a target surface 6 with ribs 9 arranged in one row. The surface structure 8 is formed by the drop-shaped stellate ribs 9 as described before, which protrude from the target surface 6.

LIST OF REFERENCE NUMBERS

(10) 1 Gas turbine component 2 Outer surface 3 Cooling passage 4 Impingement cooling element 5 Impingement cooling bore 6 Target surface 8 Surface structure 9 Ribs 10 Shroud side 11 Supply part 12 Cooling part Z Central point

(11) Thus, while there have been shown and described and pointed out fundamental novel features of the invention as applied to a preferred embodiment thereof, it will be understood that various omissions and substitutions and changes in the form and details of the devices illustrated, and in their operation, may be made by those skilled in the art without departing from the spirit of the invention. For example, it is expressly intended that all combinations of those elements and/or method steps which perform substantially the same function in substantially the same way to achieve the same results are within the scope of the invention. Moreover, it should be recognized that structures and/or elements and/or method steps shown and/or described in connection with any disclosed form or embodiment of the invention may be incorporated in any other disclosed or described or suggested form or embodiment as a general matter of design choice. It is the intention, therefore, to be limited only as indicated by the scope of the claims appended hereto.