Production method for a component having integrated channels and component

Abstract

A production method for a component having integrated channels for internal fluid guidance, having a first region, which is connected to a second region, and wherein the channels extend both through the first region and through the second region. The geometry of the component is modified to the technological characteristics of both production methods. The first region is produced by a method for casting using lost models without undercuts, and proceeding from the first region, the second region is built up using an additive manufacturing method.

Claims

1. A production method for a component having integrated channels for internal guidance of fluid, the component comprising a first region which is connected to a second region and wherein the integrated channels run through both the first region and the second region, the method comprising: producing the first region without undercuts by means of a process for casting with lost models, and, starting from the first region, building up the second region using a generative manufacturing process, and forming at least one aperture which is open toward the second region in the first region, said aperture forming a deflection region of a channel, running through the second region, with a change in flow direction.

2. The production method as claimed in claim 1, wherein a greater number of channels are formed in the second region than in the first region.

3. The production method as claimed in claim 1, wherein the first region is produced by means of precision casting.

4. The production method as claimed in claim 1, wherein the first region is produced in series.

5. The production method as claimed in claim 1, wherein the second region is manufactured individually.

6. The production method as claimed in claim 1, wherein the first region is configured in the form of a blade root of a turbine blade and the second region is configured in the form of a blade airfoil of a turbine blade.

7. The production method as claimed in claim 6, wherein the second region is configured in such a way that it comprises a part of the blade root.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

(1) One exemplary embodiment of the invention is explained in more detail with reference to a drawing, in which:

(2) FIG. 1 shows a perspective view of a turbine blade comprising a blade root and a blade airfoil,

(3) FIG. 2 shows a partial longitudinal section through a turbine blade according to a first embodiment, and

(4) FIG. 3 shows a perspective view of the blade root of a turbine blade according to a second embodiment.

DETAILED DESCRIPTION OF INVENTION

(5) Identical reference designations have the same meaning in the various figures.

(6) FIG. 1 shows a turbine blade 2, here a guide blade, which is of two-part construction.

(7) A first region 4 of the turbine blade 2 is constructed as a cast part and substantially comprises a blade root 6 of the turbine blade 2. This first region 4 is produced in series by means of a process for casting with lost models, in particular by means of precision casting. In precision casting, a wax model in the form of the workpiece to be produced is made for each cast part. In this case, the production of the cast part 4 has been significantly simplified in that the blade root 6 does not have any undercuts. Thus, no ceramic cores are used in the production of the blade root 6.

(8) A second region 8 of the turbine blade 2 is produced by means of a generative manufacturing process and comprises a blade airfoil 10 and a small part 12 of the blade root 6, said small part adjoining the blade airfoil 10. A first layer of the part 12 of the blade root 6 is connected to the cast part in a materially bonded manner and the rest of the second region 8 is built up in layers on it. In this case, there is particularly great flexibility in the design of the second region 8, said flexibility being able to be utilized to individually print a blade airfoil 10 on the standard cast part 4.

(9) The boundary between the first region 4 and the second region 8 is shown in FIG. 2 by way of a dashed line A. The turbine blade 2 is cooled internally and, for cooling purposes, a plurality of channels or cooling channels 14a, 14b, 14c, 14d are formed in the turbine blade 2.

(10) As can be seen from FIG. 3, the surface of the blade root 6 has cutouts 16a, 16b, 16c, wherein 16a and 16c form the openings of channels 14a, 14c which extend through both the first region 4 and the second region 8. Between the channels 14a, 14c, an aperture 16b is formed on the surface of the blade root 6, said aperture forming the deflection region of the channel 14b, running through the second region, with a change in flow direction. A partition 18 of the channel 14b, said partition enabling the change in flow direction, runs only through the second region 8, as shown in FIG. 2.

(11) The blade root 6 according to FIG. 3 differs from that according to FIG. 2 in that the channel 14c has a relatively large cross section in the first region 4 and a plurality of channels (not shown here) are connected to the channel 14c in the second region, each channel having a small cross section. In this case, the cooling fluid flowing during operation of the turbine blade 2 is distributed, starting from the channel 14c, into the smaller channels in the blade airfoil 10. In comparison to FIG. 2, the channels 14c and 14d are combined to form a single channel 14c in the first region 4, but they run as separate channels in the second region 8.