METHOD FOR PRODUCING ENGINE COMPONENTS WITH A GEOMETRICALLY COMPLEX STRUCTURE

Abstract

The present invention relates to a method for manufacturing thermally stressed engine components having a geometrically complex structure by metal injection moulding of metal powder mixed with a binder, by which method individual parts of the engine component are produced as separately moulded green compact sections and then as debindered brown compact sections which are joined together to form a two-part or multi-part brown compact and sintered in the assembled state, with the brown compact sections having differing shrinkage properties in the sintering process, depending on the type and size of the metal powder used, with at least one more heavily shrinking first brown compact section being automatically pressed against at least one second brown compact section during sintering of the assembled brown compact. It is provided that connecting elements in the form of positively engaging projections and recesses are provided at the joining surfaces of the brown compact sections to be joined and having differing shrinkage in such a way that during sintering of the assembled brown compact, the brown compact section with projections undergoes a greater shrinkage than the brown compact section with recesses.

Description

This invention relates to a method for manufacturing thermally stressed engine components having a geometrically complex structure by metal injection moulding of metal powder mixed with a binder, by which method individual parts of the engine component are produced as separately moulded green compact sections and then as debindered brown compact sections which are joined together to form a two-part or multi-part brown compact and sintered in the assembled state.

It is known to manufacture components of high geometrical complexity from different metals, for example special steels, case-hardened and tempered steels, intermetailic phases, light metals on titanium basis and the like, by metal injection moulding (MIM), with complete use of the material and with little or no reworking. In metal injection moulding, a metal powder is initially mixed with a binder made of thermoplastics and waxes to form a feedstock which is free-flowing and processable in an injection moulding process. The binder is then removed from the moulded part, or green compact, created by injection moulding by the use of solvents or heat, so that a porous moulded part—called the brown compact—is available and has the same dimensions as the green compact. In a subsequent heating process, the brown compact is sintered at slightly below the melting temperature of the respective metal in a sintering furnace, usually in an inert gas atmosphere or sometimes also in a vacuum. After sintering, in which the brown compact shrinks to the required final dimensions, the final moulded part is obtained, Reworking is generally not necessary.

It is known from DE 1 103 31 397 A1 to manufacture components of geometrically complicated shape for an aircraft gas turbine, in this case individual stator vane ring segments each consisting of two or more stator vanes plus an inner shroud section and an outer shroud section, by metal injection moulding. With this method, the inner and outer shroud sections are each prefabricated separately as a brown compact and then pre-sintered without shrinkage. The pre-sintered vane and shroud brown compacts are then joined together to form a stator vane segment and fixed relative to one another in the assembled position by clamps, and then sintered. A close contact at the mating surfaces, which is required for making a firm connection between the individual components, is not assured by the arrangement of clamps. Also, the restricted freedom of movement due to fixing by means of clamps can result in unwelcome deformations and cracks in the assembled stator vane segment during sintering.

US 2007/0202000 A1 describes a method for connecting two components manufactured by metal injection moulding, where the two components to be connected have differing shrinkage during sintering. The two components have projections or recesses, respectively, which positively engage in one another. During sintering, the component enclosing the projections of the other component exerts a pressure on these projections. The following connection of the two components is assured primarily by the projections and is therefore limited to a relatively small cross-sectional area (the base area of the projections) and hence to a relatively low joint strength.

The object underlying the invention is to provide a method for metal injection moulding of geometrically complex engine components joined together from separately prefabricated brown compacts, where a zero gap dimension is assured and a close and firm connection is achieved between the assembled brown compacts during the sintering process.

It is a particular object of the present invention to provide solution to the problematics by a method in accordance with the features of patent Claim 1.

Advantageous developments of the present invention become apparent from the sub-claims.

When manufacturing thermally stressed engine components of geometrically complicated structure by metal injection moulding of metal powder mixed with a binder, by which method individual parts of the component are produced as separately moulded green compact sections and then as debindered brown compact sections which are joined together to form a multi-part brown compact and sintered in the assembled state, the brown compact sections have differing shrinkage properties depending on the type and size of the metal powder used. When sintering the brown compact joined together as mentioned above, more heavily shrinking brown compact sections are automatically pressed against less heavily shrinking brown compact sections, so that a zero gap dimension and a close connection are always assured between the brown compact sections, and even complicately shaped engine components can be produced in high quality in the metal injection moulding process. It is provided here that connecting elements in the form of positively engaging projections and recesses are provided at the joining surfaces of the brown compact sections to be joined and having differing shrinkage in such a way that during sintering of the assembled brown compact, the brown compact section with projections undergoes a greater shrinkage than the brown compact section with recesses.

The inventive solution provides that during sintering of the assembled brown compact, the brown compact section having recesses is drawn to the brown compact section having projections by its shrinking projections, whereby the respective contact surfaces are pressed against one another. This has the effect that a high pressure and hence an intensive surface contact of the two brown compact sections is achieved not only in the area of the projections and recesses, but particularly along all the contact surfaces along which the two brown compact sections are in contact with one another. The brown compact sections are pressed, during sintering of the assembled brown compact, in other words over a large area at surfaces provided adjacent to the projections and recesses on the brown compact sections. With the method in accordance with the invention therefore, a zero gap dimension between the contact surfaces is assured during the sintering process of the joined-together brown compacts, and a close and firm connection is achieved.

The differing shrinkage during sintering due to the metal powder used is furthermore advantageous to the extent that when the respective metal powder is selected, the differing thermal stresses on certain component areas can also be taken into account.

The cross-sectional area of the projections and recesses is designed such that the brown compact sections are drawn against one another during sintering of the assembled brown compact. The cross-sectional area can for example be designed in an approximately dovetail-shaped and tapering form. In another design variant, the projections have a convex curvature and the recesses a concave curvature, for example in the form of spherical projections and recesses. In this way, brown compact sections of non-rotationally symmetrical shape can also be firmly joined to one another without disruptive aids during the sintering process, and non-rotationally symmetrical engine components of complicated shape, for example turbine blades designed with shrouds, can be produced by metal injection moulding.

The projections and recesses are brought into positive engagement prior to sintering, for example by longitudinal displacement or rotation of the brown compact sections to be joined.

In accordance with a design variant of the invention, the surfaces at which the brown compact sections are drawn against one another during sintering of the assembled brown compact are arranged substantially parallel to one another, which entails their having a common curvature.

In the case of rotationally symmetrical engine components the assembled brown compact includes an inner brown compact section and an outer brown compact section enclosing the former with greater shrinkage which is shrunk onto the inner brown compact section during sintering of the assembled brown compact.

In accordance with a further embodiment of the invention, the assembled brown compact can be enclosed by an additional brown compact with greater shrinkage separately produced by metal injection moulding and acting as a tool. Thanks to the assembled brown compact thus supplemented, the brown compact sections required for the engine component are closely joined to one another during sintering. The additional brown compact acting as a tool is removed from the finished component after sintering.

In an embodiment of the invention, it is provided that the more heavily shrinking first brown compact section is an outer section and the second brown compact section is an inner section. The terms “outer” and “inner” refer here to the arrangement of the manufactured engine component inside an engine.

A further embodiment of the invention provides that the type and design of the metal powder used depend on the type and size of the metal powder particles, on the metal powder material and on the binder used. Differing metal powders in the meaning of the present invention are therefore already present when for example the binder used is different or is added in a differing degree to the metal powder particles used, even if the latter are of the same size and type. Differing metal powders in the meaning of the present invention are of course also present when for example the metal powder particles are of differing size and/or type.

A preferred exemplary embodiment of the invention is described in more detail in light of the accompanying drawing. In the drawing,

FIG. 1 shows a turbine blade provided with an inner and an outer shroud and assembled of three separately manufactured brown compact sections, and

FIG. 2 shows a schematic representation of the joining area of a brown compact assembled of two brown compact sections.

FIG. 1 shows, using the example of a turbine blade provided with an inner and an outer shroud, an engine component 1 of non-rotationally symmetrical design, joined together from three brown compact sections produced separately by metal injection moulding and then sintered and joined to one another in a sintering process. The three sintered brown compact sections form the airfoil 2, as well as an outer shroud 3 and an inner shroud 4 of the turbine blade.

For manufacture of the non-rotationally symmetrical engine component 1, in this case a turbine blade, separate green compacts of the outer and inner shrouds and of the airfoils are produced by metal injection moulding of a metal powder (feedstock) mixed with a thermoplastic binder. The binder is then removed from the green compacts by melting it out in a furnace (debindering), so that brown compact sections consisting of a porous material are now available for the airfoil as well as for the inner and outer shrouds.

As shown by the joint illustrated in FIG. 2 between two separately produced outer and inner brown compact sections 5 and 6, approximately dovetail-shaped projections 7 tapering towards the contact surface 10 are located on the contact surface 10 of the outer brown compact section 5 corresponding to the inner surface of the outer shroud 3, and approximately dovetail-shaped tapering recesses 8 are located on the contact surface 11 of the inner brown compact section 6 corresponding to the upper edge of an airfoil 2. In the same manner, a further outer brown compact section (not shown)—intended for forming the inner shroud 4—is also provided with such projections which engage in recesses (not shown) provided on the lower edge of the inner brown compact section 6. Instead of dovetail-shaped tapering projections, projections tapering in another manner to the contact surface 10 can be alternatively provided.

The connecting elements created in the metal injection moulding process in the form of projections 7 and recesses 8 engage positively in one another in the assembled brown compact 9. The outer brown compact section 5 is designed by means of the type and size of the metal powder particles, the metal powder material and the binder used in such a way that it shrinks more heavily during sintering than the inner brown compact section 6. This means that during subsequent joint sintering of the outer and inner brown compact sections 5, 6 positively connected to one another by means of the recesses 8 and projections 7, a firm connection between the recesses and the projections engaging therein is created and the zero gap dimension between the joining surfaces 10, 11 is maintained.

Due to the dovetail-shaped design of the differently shrinking connecting elements, the two brown compact sections 5, 6 are also drawn and pressed against one another, so that a close joint between the outer and inner brown compact sections 5, 6 can be achieved, and as a result of the sintering process an engine component of geometrically complicated structure and made of differing materials depending on the thermal load can be provided by metal injection moulding. As a result of the fact that the outer brown compact section 5 shrinks more heavily, the projections 7 of the brown compact section 5 draw the brown compact section 6 to the brown compact section 5, with the respective contact surfaces 10, 11 being pressed against one another. The corresponding force acting on the brown compact section 6 and leading to a contact pressure between the two brown compact sections 5, 6 along the contact surfaces 1011 is indicated in FIG. 2 by arrows F.

The contact surfaces 10, 11 provided adjacent to the projections and/ or recesses 7, 8 are designed substantially parallel in one embodiment, which includes their forming curved surfaces in the same manner. This ensures large-surface and intensive pressing during sintering.

The previously described exemplary embodiment focused on the manufacture of non-rotationally symmetrical components formed from two (or more) brown compacts designed with connecting elements each having different shrinkage behaviour. The invention is however not restricted to the exemplary embodiment explained in the above. Proceeding from the basic idea of the invention, i.e. to press together the brown compacts to be joined by their different shrinkage, it may be sufficient in the case of rotationally symmetrical components, even without the connecting elements 7, 8 mentioned, when an outer brown compact section enclosing the inner brown compact section has greater shrinkage, so that the separately produced rotationally symmetrical brown compact sections are firmly pressed against one another during sintering. Finally, it is also conceivable to use an additional and more heavily shrinking brown compact as a tool to enclose the brown compact sections to be connected and to press them firmly against one another during joint sintering.

LIST OF REFERENCE NUMERALS

• 1 Engine component
• 2 Airfoil
• 3 Outer shroud
• 4 Inner shroud
• 5 Outer brown compact section (outer shroud)
• 6 Inner brown compact section (airfoil)
• 7 Projection (connecting element)
• 8 Recess (connecting element)
• 9 Brown compact assembled from 5 and 6
• 10 Contact surface of outer brown compact section 5
• 11 Contact surface of inner brown compact section 6

Claims

1. Method for manufacturing thermally stressed engine components having a geometrically complex structure by metal injection moulding of metal powder mixed with a binder, by which method individual parts of the engine component are produced as separately moulded green compact sections and then as debindered brown compact sections which are joined together to form a two-part or multi-part brown compact and sintered in the assembled state, with the brown compact sections having differing shrinkage properties in the sintering process, depending on the type and size of the metal powder used, with at least one more heavily shrinking first brown compact section being automatically pressed against at least one second brown compact section during sintering of the assembled brown compact, characterized in that connecting elements in the form of positively engaging projections and recesses are provided at the joining surfaces of the brown compact sections to be joined and having differing shrinkage in such a way that during sintering of the assembled brown compact, the brown compact section with projections undergoes a greater shrinkage than the brown compact section with recesses.

2. Method in accordance with claim 1, characterized in that the engaging projections and recesses are given a dovetail-shaped design, with the brown compact sections being drawn against one another when sintering the assembled brown compact.

3. Method in accordance with claim 1, characterized in that the projections have a convex curvature and the recesses a concave curvature, with the brown compact sections being drawn against one another when sintering the assembled brown compact.

4. Method in accordance with claim 1, characterized in that when sintering the assembled brown compact, the brown compact sections are pressed against one another at contact surfaces provided adjacent to the projections and recesses on the brown compact sections.

5. Method in accordance with claim 4, characterized in that the contact surfaces, at which the brown compact sections are drawn against one another when sintering the assembled brown compact, are arranged substantially parallel to one another.

6. Method in accordance with claim 4, characterized in that in the case of rotationally symmetrical engine components the assembled brown compact includes an inner brown compact section and an outer brown compact section enclosing the former with greater shrinkage and with or without connecting elements, said outer brown compact section being pressed onto the inner brown compact section during sintering of the assembled brown compact.

7. Method in accordance with claim 4, characterized in that the assembled brown compact is enclosed by an additional brown compact with greater shrinkage separately produced and acting as a tool, with the brown compact sections being pressed against one another during sintering and the additional brown compact being removed after sintering.

8. Method in accordance with claim 4, characterized in that the more heavily shrinking first brown compact section is an outer section and the second brown compact section is an inner section.

9. Method in accordance with claim 4, characterized in that the type and design of the metal powder used depend on the type and size of the metal powder particles, on the metal powder material and on the binder used.