Method for producing a guide vane of a turbomachine

Abstract

Method for producing a guide vane (10) of a turbomachine, wherein the guide vane (10) has a cast or turned base body (11) and guide vanes (12) applied to the base body (11) by means of a generative manufacturing process, comprising the following steps: Providing the cast or turned base body (11); Roughening the provided base body (11); Preheating the roughened base body (11); Building up the guide vanes (12) using a generative manufacturing process on the roughened and preheated base body (11).

Description

The invention relates to a method for producing a guide vane of a turbomachine.A turbomachine, such as a compressor or a turbine, has a rotor and a stator. The rotor of a turbomachine is bladed with a plurality of rotor blades. The stator of a turbomachine includes a housing and typically a guide vane with a plurality of guide vanes.In practice, guide vanes of turbomachines are either milled from solid material or are completely cast. Such guide gratings have both geometric and functional limitations.DE 10 2016 003 701 A1 discloses an impeller of a turbomachine, the rotor blades of which are formed by a generative manufacturing method. The hub supporting the blades is made by a casting method.There is a need for a novel method for producing a guide vane of a turbomachine.Proceeding from this, the object of the present invention is to provide methods for producing a guide vane of a turbomachine and the same.This object is achieved by a method for producing a guide vane of a turbomachine according to Claim 1.The guide vane to be produced has a cast or turned main body and guide vanes applied to the main body via a generative manufacturing method.The method comprises at least the following steps: providing the cast or rotated base body. roughening the provided basic body. preheating the roughened base body. building the guide vanes on the roughened and preheated base body via a generative manufacturing method. With such a method, the inventive guide grid can be produced particularly advantageously.A guide vane to be produced is designed in hybrid construction or mixed construction with a cast or turned main body and with guide vanes constructed by means of a generative or additive manufacturing method and can provide novel vane geometries of the guide vanes. Further functions, e.g. for sound absorption, heat protection or the like, can be provided.The main body can be a separate main body, especially for the guide grid. The base body can also be provided by another component of the turbocharger which is already present, for example by an insert piece or a heat shield of the turbocharger.According to an advantageous development, the guide vanes consist of a nickel-based alloy or a titanium-based alloy or a cobalt-based alloy. The guide vanes preferably consist of a nickel-chromium-iron alloy with niobium and molybdenum and with aluminum and titanium. These materials are particularly preferred from the manufacturing point of view as well as from the functional point of view.As already explained above, the base body can be a separate base body especially for the guide grid. The base body can also be provided by another component of the turbocharger which is already present, for example by an insert piece or a heat shield of the turbocharger.According to an advantageous development, the roughening of the main body is carried out over the entire surface in such a way that the main body roughened over the entire surface has a roughness Rzbetween 25 and 32. The full-surface roughening of the base body with a roughness between Rz 25 and Rz 32 is particularly preferred in order subsequently to build up the guide vanes via the generative manufacturing method.According to an advantageous development, the main body roughened over the entire surface is preheated over the entire surface to a temperature between 200° C. and 600° C. The full-surface preheating of the roughened base body to a temperature in this temperature range is also particularly preferred for the subsequent build-up of the guide vanes via the generative manufacturing method.Preferred developments of the invention are evident from the dependent claims and the following description. Exemplary embodiments of the invention are explained in more detail with reference to the drawings, without being restricted thereto. The following shows: FIG. 1 shows a detail of a guide grid.The invention relates to a method for producing a guide vane turbomachine.FIG. 1 shows a detail of a guide vane 10 of a turbomachine. The guide vane 10 can be a guide vane of a compressor or else a guide vane of a turbine.The guide vane has a main body 11 and a plurality of guide vanes 12.The main body 11 of the guide grid 10 is a cast or turned main body. The main body 11 can be a separate main body, especially for the guide grid 10. The base body 11 can also be provided by another component of the turbocharger which is already present, for example by an insert piece or a heat shield of the turbocharger.The base body 11 preferably consists of an aluminum-silicon alloy, preferably of an AlSi alloy of the 4000 series. Other materials can also be used for the base body 11.The guide vanes 12 of the guide vane 10 are guide vanes which are applied or constructed on the base body 11 by a generative manufacturing method and which consist in particular of a nickel alloy or a titanium-based alloy or a cobalt-based alloy.As nickel-based alloys, it is possible to use, for example, Hastelloy X, IN625; IN718; IN939. As titanium-based alloys, for example, TiAl6V4, TiAl6Nb7can be used. Cobalt-based alloys which can be used are, for example, CoCr, MAR-M509.The guide vanes 12 of the guide vane 10 particularly preferably consist of a nickel-chromium-iron alloy with components of niobium, molybdenum, aluminum and titanium.In order to provide such a guide grid 10, a cast or rotated base body 11 is first provided. As already explained, the base body 11 can be a separate base body, especially for the guide grid. The base body 11 can also be provided by another component of the turbocharger which is already present, for example by an insert piece or a heat shield of the turbocharger. Subsequently, the provided base body 11 is roughened. Subsequently, the roughened base body is preheated. The guide blades 12 are built up on the roughened and preheated base body via a generative manufacturing method.The roughening of the cast or rotated base body takes place over the entire surface, preferably by means of shot blasting. In this case, a roughness of Rz 25 to Rz 32 is then set on the base body 11.After roughening the base body 11, the latter is preheated, and in particular preferably over the entire surface to a temperature between 200° C. and 600° C.The guide blades 12 are built up on the base body roughened and preheated in this way, namely via the generative or additive manufacturing method.Before the actual construction of the guide vanes 12 with the aid of the generative manufacturing method, the roughened and preheated main body is further heated with the aid of an energy source, preferably with the aid of a laser, at least at those locations at which the guide vanes are constructed.The laser or the energy source is preferably operated with a power of between 400 W and 1000 W in order to further heat the corresponding regions of the base body before the actual construction of the guide vanes.Only after this further heating of the roughened and preheated base body with the aid of the energy source, in particular the laser, is the actual construction of the guide vanes 12 then carried out with the aid of the generative manufacturing method, namely preferably by applying a first layer of a metallic powder of a nickel-chromium-iron alloy to the corresponding sections of the base body 11 and subsequently melting it with the aid of a laser. This is done layer by layer so as to successively build up the guide vanes 12.It is also possible to further heat the base body 11 over the entire surface via the energy source, in particular via the laser, after roughening and preheating, and then apply a coating, preferably made of the nickel-chromium-iron alloy material, over the entire surface on the base body, in order thus also to provide a functional layer 14 in those sections 13 of the base body 11 which are formed or positioned between the guide vanes 12. Thus, for example, in the sections 13 between adjacent guide vanes 12, a porous structure can be formed which serves for sound absorption. Furthermore, holes and grooves for flow guidance can be formed in the sections 13 between adjacent guide vanes 12.List of reference characters10 Guide vane 11 Base body 12 Guide vane 13 Section 14 Functional layer

Claims

Method for producing a guide vane (10) of a turbomachine, wherein the guide vane (10) has a cast or turned main body (11) and guide vanes (12) applied to the main body (11) via a generative manufacturing method, having the following steps: providing the cast or turned main body (11); roughening the provided main body (11); preheating the roughened main body (11); constructing the guide vanes (12) via a generative manufacturing method on the roughened and preheated main body (11).Method according to Claim 1, characterized in that the guide vanes (12) are constructed from a nickel-based alloy or a titanium-based alloy or a cobalt-based alloy.Method according to Claim 2, characterized in that a base body (11) made of an aluminium-silicon alloy is provided as base body (11).Method according to one of Claims 1 to 3, characterized in that the guide vanes (12) are constructed from a nickel-chromium-iron alloy with niobium and molybdenum and also with aluminium and titanium.Method according to Claim 4, characterized in that a base body (11) made of an AlSi alloy of the 4000 series is provided as the base body (11).Method according to one of Claims 1 to 5, characterized in that the roughening of the base body (11) is carried out by means of shot blasting.Method according to one of Claims 1 to 6, characterized in that the roughening of the base body (11) is carried out in such a way that the roughened base body (11) has a roughness Rz of between 25 and 32.Method according to one of Claims 1 to 7, characterized in that the main body (11) is roughened over its entire surface.Method according to one of Claims 1 to 8, characterized in that the roughened main body (11) is preheated over its entire surface.Method according to one of Claims 1 to 9, characterized in that the roughened main body (11) is preheated to a temperature between 200°C and 600°C.Method according to one of Claims 1 to 10, characterized in that, before the guide blades (12) are built up, the preheated main body (11) is heated further, at least at those locations of the main body (11) at which the guide blades (12) are built up, with the aid of an energy source, in particular a laser.Method according to claim 11, characterised in that the energy source, in particular the laser, is operated with a power of between 400 W and 1000 W.Method according to Claim 11 or 12, characterized in that, after roughening and preheating, the main body (11) is heated further over the full area by means of the energy source, and in that a coating is then applied over the full area to the main body (11), in order thus to provide a functional layer (14) in those sections (13) of the main body (11) which are positioned between the guide vanes (12).

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