Method for joining a modular hot gas component using welding and high-temperature soldering, and joined component

Abstract

A method for joining a modular hot gas component by welding and high-temperature soldering. In order to optimally join high-temperature components, a first component is plugged into pins of a second component, a soldering material is placed between the two components, and the pins of the second component are welded to the first component.

Claims

1. A method for joining at least two components, wherein at least one component has at least one hole for corresponding pins of an other component, the method comprising: inserting the pins into or through the at least one hole, wherein the pins are accessible on or from an other side of the at least one component, applying a solder material in advance between the components in a joining region, preheating of the pins in advance so that the components are held firmly in relation to one another by a compressive stress, welding of the pins on the other side, so that the components are firmly connected to one another, and in a final process, high-temperature soldering of the components.

2. The method as claimed in claim 1, wherein the solder material takes the form of a film.

3. The method as claimed in claim 1, wherein the solder material has been applied by laser build-up welding.

4. The method as claimed in claim 1, wherein laser beam welding, is used for the welding.

5. The method as claimed in claim 1, wherein the at least one component has been or is produced by an additive manufacturing method.

6. The method as claimed in claim 1, wherein the components have been or are produced by various production methods.

7. The method as claimed in claim 1, wherein the pins are formed in one piece with the other component.

8. The method as claimed in claim 1, wherein the pins have a bore.

9. The method as claimed in claim 1, wherein the pins have a diameter of 2 cm to 3 cm.

10. The method as claimed in claim 1, wherein the bores have a depth of 30 mm-50 mm.

11. The method as claimed in claim 1, wherein the at least one component is formed flat in the joining region.

12. The method as claimed in claim 1, wherein the preheating of the pins comprises preheating to 773K-1073K.

13. The method as claimed in claim 1, wherein the preheating of the pins comprises preheating by a laser.

14. The method as claimed in claim 1, wherein the final process comprises a batch process.

15. The method as claimed in claim 4, wherein laser beam welding in single mode is used for the welding.

16. The method as claimed in claim 6, wherein the components have been or are produced by a casting technique and additive manufacturing methods.

17. The method as claimed in claim 8, wherein the pins have a bore with a diameter of 3 mm to 5 mm.

18. The method as claimed in claim 1, wherein the components comprise a first component and a second component, each having at least one hole for corresponding pins of an intermediate component joined between.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

(1) FIGS. 1 and 2 schematically show the invention.

DETAILED DESCRIPTION OF INVENTION

(2) The description and the figures only represent exemplary embodiments of the invention.

(3) Proposed is a joining method for hot gas components, such as in particular for stationary and moving turbine blades, of nickel-based superalloys, only discussed by way of example for these components.

(4) In this case, the various components of the hot gas components, for example the airfoil, outer and inner platforms, are produced from materials optimized for this and by production methods suitable for this, for example production by casting techniques, selective laser melting.

(5) This is performed in two steps: the positive joining of the outer platforms and the airfoil is performed by means of pins on the airfoil and bores in the outer platform in four steps. A solder material is introduced between the airfoil and the platform in the form of a film or by means of laser beam build-up welding. The pins with an advantageous diameter of 20 mm-30 mm are advantageously provided with bores with an advantageous diameter=3 mm-5 mm and advantageously have a depth of 30 mm-50 mm.

(6) 1. By means of defocused laser radiation and adapted laser power, the pins are individually preheated to 773K-1073K. As a result, compressive stresses between the platform 10 and the airfoil 7 are achieved and the components 7, 10 cannot be displaced in relation to one another during the later joining process.

(7) 2. The preheating is controlled to a constant value by means of a (for example optical) temperature measurement and the solder 16 advantageously does not melt.

(8) 3. Laser beam welding is performed in particular with single-mode laser radiation in the preheated state, whereby a reduction of the susceptibility to hot cracking of the nickel-based superalloy is obtained and moreover no tacking is necessary as preparation for the welding process.

(9) 4. High-temperature soldering of the component.

(10) Advantages are: Components for highest thermal-mechanical stresses High-temperature soldering possible without a complicated device.

(11) FIG. 1 shows a component 1 by way of example, which is constructed from two or more parts 4, 7, 10 that are to be joined together.

(12) In this example it is a stationary blade, but may also take the form of a moving blade or generally a component in which two components are to be joined to one another.

(13) In the case of this component 1 of a moving turbine blade, it has an airfoil 7 and lower and upper blade platforms 4, 10, which platforms 4, 10 are formed in particular flat in the joining region (here for example the stump of the airfoil on the platform 4). The two outer solid platforms 4, 10 may be produced by means of a conventional precision casting technique or an additive manufacturing method such as SLS or SLM. A comparable situation applies to the airfoil 7.

(14) In FIG. 2 it is shown more specifically how two components 7, 10 are joined to one another.

(15) The airfoil 7 or the component 7 has at least one pin, in particular three pins 13′, 13″, 13′″, which can be inserted in or through corresponding openings 14′, 14″, 14′″ in the second component 10, the outer blade platform 10.

(16) On the contact surface between the first component 7 and the second component 10 (=joining region), here the airfoil 7 and the blade platform 10, there is a solder material, in particular a film or solder material that has been applied by means of laser build-up welding. The two components 7, 10 are then fitted one in the other in such a way that the solder material 16 is then present between them.

(17) The pins 13′, 13″, 13″ are heated to correspondingly high temperatures, in particular of 773K-1073K, to achieve a stress between the pins 13′, 13″, 13′″ and the blade platform 10, so that they are prestressed.

(18) Then, the pins 13, 13″ of the first component 7 are welded to the second component, so that there is a firm connection.

(19) After that, high-temperature soldering of the component 1 takes place in a furnace, which can take a number of such components.