Patent Application
20140356644
The present application claims priority under 35 U.S.C. §119 of German Patent Application No. 102013209994.0, filed May 29, 2013, the entire disclosure of which is expressly incorporated by reference herein.
1. Field of the Invention
The present invention relates to a component for a turbomachine having at least one region made of an intermetallic material, in particular a TiAl blade for a stationary gas turbine or an aircraft engine, and also to a process for producing such a component.
2. Discussion of Background Information
Intermetallic materials, such as titanium aluminides, which consist to a large extent of intermetallic phases are of interest for specific applications, for example in the construction of aircraft turbines, since, on account of their structure and their chemical bonds, they can have high strengths and at the same time, on account of a low specific weight, can form components having a low weight, as is the case in particular with materials based on titanium aluminides (TiAl materials).
However, for use in stationary gas turbines or aircraft engines, the TiAl materials in certain applications require additional surface modification in order to fulfill all the requirements.
Thus, it is known, for example, to solder on small plates made of a wear-resistant alloy, for example the alloy Tribaloy T800 (trade name of Deloro Stellite Holdings Corporation), in the region of the contact surfaces of shrouds of adjacent blades, what is termed the z notch, in the case of TiAl blades of gas turbines, in order to reduce the wear.
However, intermetallic materials and correspondingly also TiAl blades are difficult to solder, and therefore the soldered joint with the T800 small plates which have been soldered on often does not satisfy the requirements.
Moreover, it may also be necessary to modify the surface in other regions of TiAl blades, in order for example to avoid the formation of cracks, as can form for example in the region of the blade roots at the contact points with the disk groove of a rotor disk or during the impingement of particles on the main blade part.
In view of the foregoing, it would be advantageous to provide surface modification for components based on intermetallic materials, such that firstly the connection to other components, for example wear-resistant plates, is improved and secondly the surface generally becomes less sensitive to the formation of cracks. It would also be advantageous if a a corresponding surface modification could be made easily and reliably.
The present invention provides a component for a turbomachine. The component comprises at least one region made of an intermetallic material which is formed from an intermetallic compound or comprises an intermetallic phase as the largest constituent, in particular to an extent of more than 50% by volume. The intermetallic material is compacted and/or modified in microstructure, in particular deformed, by microplasticization at least partially at a surface or interface in a region close to the surface or interface.
In one aspect of the component, the interface may be an interface to a coating of the component or the interface of an integral bond.
In another aspect of the component, the intermetallic material may be selected from silicides, nickel aluminides, titanium aluminides.
In yet another aspect of the component of the present invention, the component may be micro-alloyed and/or diffusion welded in the region of the microplasticization.
In a still further aspect, the component may be a blade of a turbomachine that comprises a titanium aluminide material.
In another aspect, the component may be a blade of a turbomachine, which blade comprises a microplasticized region with a plating, in particular a plating comprising a cobalt-base alloy, or a microplasticized, micro-alloyed region in the region of the shroud stop surface and/or of the blade root flank, the micro-alloyed region being alloyed with at least one element selected from niobium, tantalum, molybdenum, tungsten, platinum, rhenium.
The present invention also provides a process for producing a component for a turbomachine, in particular a component as set forth above, including the various aspects thereof. In this process there is provided a component having at least one region made of an intermetallic material which is formed from an intermetallic compound or comprises an intermetallic phase as the largest constituent, in particular to an extent of more than 50% by volume, and microplasticization is carried out in the intermetallic material at least partially at a surface or interface in a region close to the surface or interface.
In one aspect of the process, the microplasticization may be effected thermally and/or mechanically.
In another aspect, the microplasticization may be carried out as high-speed microplasticization.
In yet another aspect, the microplasticization may be effected by micropeening, in particular ultrasonic peening.
In a still further aspect of the process of the present invention, a plate or a coating in the form of a powder, a film, a lacquer or a vapor-deposited layer may be applied to the region subjected to the microplasticization before the microplasticization. For example, the plate may be applied by ultrasonic welding.
The present invention is based on the idea that, in intermetallic materials, it is possible to achieve an improvement in the connection properties to adjacent components or in general terms a resistance of the surface to the formation of cracks by virtue of the fact that microplasticization is carried out in a region close to the surface or interface, since microplasticization of the intermetallic materials can be carried out surprisingly effectively in spite of the high strengths and the partly brittle behavior of the intermetallic phases with respect to macroscopic deformation. The microplasticization leads to compaction in the region close to the surface or interface or in general terms to a modification of the microstructure and in particular to the formation of residual compressive stresses, which lead to an increase in the surface strength and thus to a reduction in the formation of cracks.
The microplasticization can be performed directly in the region of the surface of a corresponding component or else at corresponding interfaces, for example an interface between a coating of the component and the base material of the component or an interface formed at an integral bond between the component and another component.
The intermetallic material can be formed on the basis of titanium aluminides, nickel aluminides or silicides, the material containing one or more different intermetallic phases based on said constituents as the largest constituent.
The microplasticization can be effected thermally and/or mechanically, the microplasticization involving locally narrowly delimited mechanical deformation and/or heating. By way of example, use can be made of high-speed microplasticization, it being possible for this to be carried out by micropeening, in particular ultrasonic peening, as described, for example, in US 2007/0068605 A1, the entire disclosure of which is incorporated by reference herein, for use in metals and in particular in aluminum alloys.
The thermal microplasticization can be generated by local heating, for example by means of inductive heating, or by beam heating, for example laser beams. It goes without saying that a combination of mechanical microplasticization by micropeening and thermal microplasticization by local heating is also possible.
In addition, micro-alloying and/or diffusion welding can be effected in the region of the microplasticization.
The micro-alloying can be effected by mechanical alloying, in which case corresponding alloying constituents can be provided, before the surface is treated, by powder application, lacquering, vapor deposition or the application of a film and can then be incorporated in the surface of the component by micropeening. A thermal treatment can assist the alloying operation.
In particular, TiAl blades for stationary gas turbines or aircraft engines can be modified in various regions with or without a coating or plating in their surface or interface in order to adapt them to the requirement profile for use in corresponding gas turbomachines.
The accompanying drawings show, purely schematically, in
The particulars shown herein are by way of example and for purposes of illustrative discussion of the embodiments of the present invention only and are presented in the cause of providing what is believed to be the most useful and readily understood description of the principles and conceptual aspects of the present invention. In this regard, no attempt is made to show details of the present invention in more detail than is necessary for the fundamental understanding of the present invention, the description in combination with the drawings making apparent to those of skill in the art how the several forms of the present invention may be embodied in practice.
This is illustrated in a plan view, in
Owing to the relative movement of the adjacent shrouds 3, 3′ in relation to one another, the stop surfaces 7 are subjected to a particular amount of wear.
In order to reduce the wear at the stop surfaces 7 or to keep it as small as possible in the case of blades 1 formed from TiAl materials, i.e. TiAl alloys with a large proportion of intermetallic phases based on TiAl, the stop surfaces 7 are provided with small plates made of a wear-resistant alloy, for example a CoCrMo alloy (e.g. T800 (trade name of Deloro Stellite Holdings Corporation)), as is shown in a schematic illustration in
In order to eliminate the pores 13 and to compact the welding zone 12, the corresponding component 10 is subjected, together with the small plate 11 which has been welded on, to high-speed microplasticization by ultrasonic peening, in order to compact the welding zone 12.
As an alternative to welding the Tribaloy T800 small plate 11 to the component 10 by means of ultrasonic welding, a soldered joint between the small plate 11 and the component 10 is also possible, in which case the soldered layer can be compacted in a similar manner by microplasticization, for example in the form of ultrasonic peening. In both cases, the compaction achieves an improvement in the connection between the small plate and the component 10.
The microplasticization by the ultrasonic peening and the thermally induced diffusion lead to the formation of a mechanically alloyed and microplasticized zone 17 at the surface of the component 10, which is now indicated by the dashed line 16′, the zone 17 being compacted and strengthened such that the formation of cracks is avoided when using a corresponding component, for example in the form of a blade root in a disk groove.
Moreover, there are further possible applications for microplasticization in TiAl blades, for example in the region of the main blade part 2. The surface of the main blade part 2 can be compacted and strengthened alone by microplasticization, i.e. for example ultrasonic peening, in order to be stabilized with respect to the formation of cracks by particle impact. In addition, the surface can be further modified and improved by mechanical alloying.
The ultrasonic peening can be carried out with an operating frequency of, for example, 1 to 100 kHz and an operating power of, for example, 10 to 10,000 watts, with an effective power of, for example, 5 Newton to 5000 Newton. The machining can be effected in pulses, in particular in short pulses with a duration of, for example, 0.1 to 5 seconds.
While the present invention has been described with reference to exemplary embodiments, it is understood that the words which have been used herein are words of description and illustration, rather than words of limitation. Changes may be made, within the purview of the appended claims, as presently stated and as amended, without departing from the scope and spirit of the present invention in its aspects. Although the present invention has been described herein with reference to particular means, materials and embodiments, the present invention is not intended to be limited to the particulars disclosed herein; rather, the present invention extends to all functionally equivalent structures, methods and uses, such as are within the scope of the appended claims.
| Number | Date | Country | Kind |
|---|---|---|---|
| 102013209994.0 | May 2013 | DE | national |
