Method for producing a run-in coating, a run-in system, a turbomachine, as well as a guide vane

Abstract

A method for producing a run-in coating for a turbomachine for braking a rotor in the event of a shaft breakage, the run-in coating being formed as an integral, generative blade portion during a generative manufacture of a blade. A run-in system having an abradable ring that is configured circumferentially on a blade row and has a chamber-type material structure. A turbomachine having a run-in system of this kind, as well as a guide vane having such a run-in coating.

Claims

1. A method for producing a run-in coating for a turbomachine for braking a rotor in the event of a shaft breakage, comprising: forming the run-in coating as an integral blade portion during a generative manufacture of a blade, wherein the generative manufacture includes forming the blade and the run-in coating through deposition and melting of metal powder in layers.

2. The method as recited in claim 1 further comprising constructing a generative structure during manufacture of the blade and removing the structure following the manufacture of the blade.

3. The method of claim 1, wherein the run-in coating forms an abradable ring, and the abradable ring includes a plurality of run-in coatings mutually laterally spaced apart by circumferential gaps which together form an integral, closed or open abradable ring having a chamber-type material structure.

4. The method of claim 1, wherein each run-in coating includes a damping layer for shock absorption and a braking layer for optimizing braking.

5. A run-in system comprising an integral, closed or open abradable ring including a plurality of run-in coatings mutually laterally spaced apart by circumferential gaps along the circumference of the abradable ring, the run-in coatings forming the abradable ring extending over a rotor blade row and located axially between outer shrouds of the rotor blade row and outer shrouds of a guide vane row and having a chamber-type material structure.

6. The run-in system as recited in claim 5 wherein the abradable ring is formed either on a side of the outer shrouds of the rotor blade row opposite a side of the outer shrouds of the guide vane row, or on a side of the outer shroud of the guide blade row opposite a side of the outer shroud of the rotor vane row.

7. The run-in system as recited in claim 5 wherein the abradable ring is placeable on leading sides of outer shrouds of the guide vane row.

8. The run-in system as recited in claim 5 wherein the abradable ring is placeable on leading edges of guide vanes.

9. The run-in system as recited in claim 5 wherein an abrasive ring is configurable for running onto the abradable ring of trailing sides of outer shrouds of the rotor blade row in response to a shaft breakage.

10. The run-in system as recited in claim 5 wherein the run-in coatings are manufactured in accordance with the method recited in claim 1.

11. A turbomachine comprising the run-in system as recited in claim 5, and an abrasive ring for running onto the abradable ring in response to a shaft breakage, the abradable ring being disposed in the leading region of the guide vane row, and the abrasive ring being formed in the upstream trailing region of a rotor blade row opposite the abradable ring.

12. A guide vane row comprising a plurality of guide vanes, each guide vane including an outer shroud and an inner shroud; and an abradable ring in a leading region of the guide vane, wherein the abradable ring includes a plurality of run-in coatings mutually laterally spaced apart by circumferential gaps along the circumference of the abradable ring, the plurality of run-in coatings having a chamber-type material structure.

13. The guide vane as recited in claim 12 wherein the run-in coatings are formed on a leading side of the outer shrouds.

14. The guide vane as recited in claim 12 wherein the run-in coatings are formed radially outwardly on a leading edge of a blades of each guide vane.

15. The guide vane as recited in claim 12 wherein the run-in coatings are formed on an edge portion of a leading edge displaced upstream relative to a radially inner edge portion of each guide vane.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

(1) Preferred exemplary embodiments of the present invention are described in greater detail in the following with reference to greatly simplified schematic representations, in which:

(2) FIG. 1 shows a part section through a turbomachine including a first exemplary embodiment of a run-in system according to the present invention;

(3) FIG. 2 shows an axial plan view of a leading region of a guide vane row;

(4) FIG. 3 is a lateral detailed representation of the leading region;

(5) FIG. 4 shows a plan view of a rotor blade row in the region of the outer trailing edges thereof;

(6) FIGS. 5 and 6 illustrate methods of functioning of the run-in system in the event of a shaft breakage;

(7) FIG. 7 illustrates a method for producing a run-in coating according to the present invention; and

(8) FIG. 8 shows a part section through a turbomachine having a second exemplary embodiment of the run-in system according to the present invention.

DETAILED DESCRIPTION

(9) The part-sectional view in FIG. 1 shows a lateral view of a rotor blade 2 and of an adjacent downstream guide vane, respectively of a guide vane segment 4 of a rotor in the compressor of an aircraft engine.

(10) Together with a multitude of other rotor blades, rotor blade 2 forms a rotor blade rim, respectively a rotor blade row that is configured via a hub 6 on the blade root side and a disk accommodating the same on a shaft 10 rotating about an axis of rotation 8. Rotor blades 2 each have a blade root 12 that is configured in an annular space between an inner shroud 14 and an outer shroud 16 of rotor blades 2. Shrouds 14, 16 each define the annular space traversed by a main flow and each have a leading side 18 oriented oppositely to the flow direction, as well as a trailing side 20 oriented in the flow direction.

(11) In this exemplary embodiment, guide vanes 4 are each fixed in position by root portions 24a, 24b thereof in a housing-side recess. In alternative exemplary embodiments, guide vanes 4 are integrally included on or bolted to the housing. In correspondence with rotor blades 2, they each have a blade leaf 22 that is configured in an annular space between an inner shroud 26 and an outer shroud 28 of rotor blades 4 and that each feature an upstream oriented leading side 30 and a downstream oriented trailing side 32. However, when guide vanes 4 are combined into guide vane segments, a plurality of blades 22 are configured in each case between an inner shroud 26 and an outer shroud 28.

(12) In accordance with the representation in FIG. 1, a run-in system 34 (marked by a dashed-line circle) for guiding and braking the rotor in response to a shaft breakage is configured between outer shrouds 16 of the rotor blade row and outer shrouds 28 of guide vane row. Run-in system 34 has an abradable ring 36 configured in the leading region of the guide vane row and an opposite abrasive ring 38 configured in the trailing region of the upstream rotor blade row that are mutually axially spaced apart in the case of an undamaged rotor. In this first exemplary embodiment, abradable ring 36 and abrasive ring 38 are circumferentially closed.

(13) As shown in FIG. 2, abradable ring 36 is formed by a multitude of preferably generatively produced run-in coatings 40 that are configured on the leading sides 30 of outer shrouds 28 as integral blade portions and are mutually laterally spaced apart across a narrow circumferential gap 42a, 42b. For the sake of clarity, merely two circumferential gaps 42a, 42b are shown that may be closed using adapters suited for that purpose. Thus, each run-in coating 40 forms a ring segment of abradable ring 36 and covers only a radially inner region of leading sides 30.

(14) As shown by the detail view in FIG. 3, run-in coatings 40 have a chamber-type material structure. In this context, “chamber-type” signifies a porous, cellular, honeycomb-shaped, skeleton-type, latticework-type and similar material structure. In particular, “chamber-type” signifies a structurally weaker internal structure than a bearing structure accommodating run-in coating 40 and an abrasive element, such as abrasive ring 38, that runs into run-in coatings 40, abrading the same. They merge transitionally by a peripheral surface 44 facing the annular space into a cylindrical or conical shroud surface 46 facing the annular space. They have a maximum radial extent that corresponds to a radial extent, respectively thickness of outer shrouds 16 of rotor blades 2 in the region of trailing edges 20 thereof (see FIGS. 5 and 6).

(15) Abrasive ring 38 indicated in FIG. 4 is formed by outer trailing sides 20 of rotor blades 2. Rotor blades 2 are likewise mutually spaced apart, in each case across a small circumferential gap 42a, 42b that may be closed using adapters suited for that purpose. Abrasive ring 38 is made of a harder material than abradable ring 36 and thus leads to an ablation of abradable ring 36 in response to a shaft breakage.

(16) As shown in FIG. 5, in response to a shaft breakage, rotor blades 2 run onto abradable ring 36 of guide vanes 4 via abrasive ring 38 thereof and thus directly via trailing sides 20 thereof forming abrasive ring 38, in the direction of flow in accordance with the arrow. Abrasive ring 38 rubs into run-in coating 36, whereby the rotor is braked, and abradable ring 36 is abraded, respectively worn down, at least in portions thereof, as shown in FIG. 6. In this context, abradable ring 36 has such a chamber-type material structure and such an axial extent that outer shrouds 16 of rotor blades 2 are prevented from running directly by trailing sides 20 thereof onto leading sides 30 of outer shrouds 28 of guide vanes 4. Any fragmentation of rotor blades 2 and/or of guide vanes 4 is thereby effectively prevented.

(17) As shown in FIG. 7, run-in coatings 40 are integrally produced with particular guide vane 4 in a generative process. To this end, a suitable metal powder is deposited in layers onto a base plate 48, and an auxiliary structure 50 marked by hatched shading is produced by a high-energy beam, such as an electron beam or a laser beam. The high-energy beam is guided in tracks over the top powder layer, whereby it is melted thereon and bonded to the preceding powder layer. Auxiliary structure 50 makes it possible to compensate for unevenness of base plate 48, for example, and permits a step-by-step construction of overlying structures and, thus, the creation of a defined reference plane for particular guide vane 4. In addition, auxiliary structure 50 acts as a support for stabilizing guide vanes 4 during the generative production.

(18) By modifying the process parameters, guide vanes 4 in question are constructed generatively in layers, horizontally from leading side 30 to trailing side 32, together with integrated run-in coating 40, during production of auxiliary structure 50. Once particular guide vane 4 is completely constructed, it is separated from auxiliary structure 50.

(19) The chamber-type material structure of run-in coatings 38 is produced by varying the manufacturing parameters and thus by employing process parameters that are individualized relative to the other blade portions, such as root portions 24a, 24b, shrouds 26, 28, as well blade 22, respectively blades 22 in the case of rotor blade segments.

(20) A second exemplary embodiment of run-in system 34 according to the present invention is shown in FIG. 8. In contrast to the first exemplary embodiment, an abradable ring 36 is configured at leading edges 52 of blades 22 or guide vanes 4 and thus has an open form over the circumference of the guide vane row. Run-in coatings 40 forming abradable ring 36 are provided with the greatest axial extent thereof radially outwardly and thus in the region of an opposing abrasive ring 38. They have a chamber-type, respectively cellular, porous, honeycomb-shaped and similar material structure, as described above, and are generatively formed together with guide vanes 4. The material structure of the other blade region 54 is of the conventional type and is thus provided with a structurally harder internal structure than run-in coating 40. Run-in coatings 40 are disposed quasi in front of the particular blade 22, whereby leading edges 52 each have a radially outer, respectively outer shroud-proximate edge portion 56 that is displaced upstream in relation to a radially inner edge portion 58. Thus, leading edge 52 has a stepped form.

(21) Abrasive ring 38 of the upstream rotor blade row is identical to abrasive ring 38 in accordance with the first exemplary embodiment. Thus, abrasive ring 38 is likewise formed of outer shroud-side trailing sides 20 of the upstream rotor blade row and is made of a harder material than abradable ring 36.

(22) The method of functioning is identical to that of the first exemplary embodiment. In response to a shaft breakage, rotor blades 2 run onto open abradable ring 36 of guide vanes 4 via abrasive ring 38 thereof and thus directly via trailing sides 20 thereof forming abrasive ring 38. Abrasive ring 38 rubs into run-in coating 36, respectively partially abrades the same, whereby the rotor is braked. The chamber-type material structure and the axial extent of abradable ring 36 prevent outer shrouds 16 from running directly onto blade region 54. Thus, any fragmentation of the rotor blades and/or of the guide vanes is effectively prevented.

(23) Blade-side run-in coatings 50 are generatively, integrally produced during manufacture of guide vanes 4, so that reference is made to the above explanations pertaining to FIG. 7.

(24) A method is described for producing a run-in coating for a turbomachine for braking a rotor in the event of a shaft breakage; the run-in coating being formed as an integral blade portion in the context of a blade manufacture; a run-in system having an abradable ring having a chamber-type material structure configured circumferentially on a blade row, a turbomachine having such a run-in system, as well as a guide vane having a run-in coating of this type.

LIST OF REFERENCE NUMERALS

(25) 2 rotor blade 4 guide vane 6 hub 8 axis of rotation 10 shaft 12 blade root 14 inner shroud 16 outer shroud 18 leading side 20 trailing side 22 blade leaf 24a, b root portion 26 inner shroud 28 outer shroud 30 leading side 32 trailing side 34 run-in system 36 abradable ring 38 abrasive ring 40 run-in coating 42a, b circumferential gap 44 peripheral surface 46 shroud surface 48 base plate 50 auxiliary structure 52 leading edge 54 blade region 56 outer edge portion 58 inner edge portion