US3411563A

US3411563A - Elimination of equiaxed grain superimposed on columnar structures

Info

Publication number: US3411563A
Application number: US482799A
Authority: US
Inventors: Donald G Fleck
Original assignee: TRW Inc
Current assignee: Northrop Grumman Space and Mission Systems Corp
Priority date: 1965-08-26
Filing date: 1965-08-26
Publication date: 1968-11-19
Anticipated expiration: 1985-11-19

Description

Nov. 19, 1968 D. G. FLECK 3,411,563 ELIMINATION'QF EQUIAXED GRAIN SUPERIMPOSED 0N COLUMNAR STRUCTURES Filed Aug. 26, 1965 Fig.5

INVENTOR. Dana/a Q l /ecv By La; I%.IK%TTORNEYS United States Patent 3,411,563 ELIMINATION OF EQUIAXED GRAIN SUPER- IMPOSED 0N COLUMNAR STRUCTURES Donald G. Fleck, Alliance, Ohio, assignor to TRW Inc., Cleveland, Ohio, a corporation of Ohio Filed Aug. 26, 1965, Ser. No. 482,799 1 Claim. (Cl. 164-69) ABSTRACT OF THE DISCLOSURE Method and apparatus for eliminating equiaxed grain defects from columnar castings wherein a secondary cavity is provided at the portion of the casting where such defects ordinarily occur, so that upon directional solidification any inclusions are carried into the secondary cavity by the advancing solidification front to form an appendage which can be readily severed from the columnar casting.

The present invention relates to the production of columnar structures from high temperature alloys. The invention is specifically applicable to the manufacture of turbine vanes consisting entirely of columnar grains. Such cast vanes have been found to possess greater fracture resistance and ductility under creep loading conditions than castings having equiaxed grain structures.

Columnar structures are formed by the unidirectional growth of dendrites during solidification. There is no exact relationship between the dendritic structure and the columnar grains, but each columnar grain is usually composed of more than one dendrite and the number may vary from a few to'several hundred. The interdendritic spacing is related to the solidification rate only. Columnar grain size, however, may be affected by factors other than the solidification process such as ordinary grain growth. Despite these differences, the most convenient approach for the examination of columnar structure formation is through the study of dendrites formed during solidification.

The primary requirement for the formation of a parallel dendritic structure is the presence of a unidirectional thermal gradient. This gradient is achieved by pre-heatin-g the mold, and using an open ended mold positioned on a chill block composed of a metal of very high thermal conductivity compared to the material of the mold. When the metal first enters the mold, the initial solidificationoccurs at the chill block, and may result in the formation of many fine dendrites having a random orientation. The initial freezing releases the heat of fusion, resulting in some temperature rise locally, arresting the chill zone formation. At the interface of the chill zone and the melt, the dendrites begin to grow into the melt at a rate dependent upon the amount and depth of the supercooling.

Initially, all dendrites at the chill zone-melt interface grow at equal rates, since equal supercooling is present. However, those oriented parallel to the thermal gradient are growing into an area of continuous supercooling. Those oriented un favorably cannot advance as rapidly in the direction of the thermal gradient, since only a component of the growth velocity is aligned with this gradient. The dendrites growing parallel to the gradient, since they have already undengone some growth, will give off a latent heat of fusion due to the freezing process. This heat of fusion increases the temperature at the base of the dendrites and decreases the amount of supercooling available for growth of the more unfavorably oriented neighbors. In this manner, the growth of 3,411,563 Patented Nov. 19, 1968 the misoriented dendrites is stifled, and only those aligned with the thermal gradient will undergo significant growth.

Comparative tests between equiaxed and columnar castings indicate that the columnar casting has marked advantages for certain applications. The high temperature strength and ductility of the columnar structures is generally superior to the equiaxed structure, and may be attributed to the preferential occurrence of gas porosity at grain boundary locations. In the equiaxed structures the gas porosity is distributed randomly, following a grain boundary pattern. As a result, intergranular fractures occur with low ductility. In the columnar structure the grain lboundaries are oriented parallel to the growth direction. Accordingly, the porosity has little or no influence on ductility. The improvement in ductility can be attributed to several factors. The segregation normally associated with equiaxed grains .is reduced by the columnar solidification process. The conditions necessary to form columnar structures are identical to those required for proper feeding. Thus, microshrinkage is almost completely eliminated. The primary reason for improved ductility, however, appears to be the elimination of grain boundaries perpendicular to the stress axis. This prevents the normally brittle intergnanular type of fracture, permitting a great amount of deformation to occur prior to failure.

While techniques for securing sound columnar castin-gs have been highly developed, there is a recurring defect which exists in such columnar castings and seems to be associated with the slow solidification process. This defect consists in areas of equiaxed grain structure which, because of their physical appearance, have been called freckles. These defects normally appear on the macroetched casting as a vertical streak of fine equiaxed grains, and usually occur in the portion of the casting which is the last to solidify. In the case of a turbine vane, this may occur on either the leading or trailing edge near the tip of the part, depending upon the configuration of the mold. The equiaxed grain is superficial in nature and stock removal reveals the underlying structure to be the desired columnar grain. Chemical analyses of these areas show them to be highly segregated. Radiographic examination reveals the segregation as well as microporosity associated with it. Consequently, the existence of this condition is undesirable for several reasons, (1) the equiaxed surface grain is a weak spot on the casting, from the standpoint of thermal shock, (2) the segregation of low melting constituents in this area creates a relatively weak area in the casting and (3) the microporosity associated with the defect can act to initiate cracks.

The presence of such equiaxed defects is particularly noticeable when the mold is heated by induction heating and presumably could be due at least in part to inductive stirring of the molten metal by the electromagnetic energy.

One of the objects of the present invention is to provide an improved method for eliminating equiaxed grain defects in columnar castings without interfering with normal columnar grain growth.

Still another object of the invention is to provide an improved method for casting superalloys and other high temperature materials under conditions of directional solidification, and isolating any equiaxed defects so that they can be readily removed upon removal of the solidified metal from the mold.

A further object of the invention is to provide a casting assembly for producing turbine vanes and the like, the casting assembly including a mold having a secondary cavity which forms an appendage on the casting in which any equiaxed defects will occur.

A further description of the present invention will be made in conjunction with the attached sheet of drawings in which:

FIGURE 1 is a view in elevation of a turbine vane produced accordingly to prior techniques and exhibiting the type of defects which the present invention overcomes;

FIGURE 2 is a view partly in elevation and partly in cross-section of a mold assembly which incorporates the improvements of the present invention;

FIGURE 3 is a side elevational view of a cast turbine vane produced according to the present invention; and

FIGURE 4 is a front elevational view of the vane of FIGURE 3 after removal of the appendage.

In FIGURE 1, reference numeral indicates generally a turbine vane composed of a superalloy or the like, and having a shroud portion 11, an airfoil vane portion 12, and a relatively massive root portion 13. When produced by the usual techniques of casting, particularly when involving induction heating, it has been found that a portion of the edge of the vane portion 12, such as indicated at reference numeral 14, provides an undesirable area of equiaxed grains which are objectionable for the reasons mentioned previously.

In accordance with the present invention, I make the casting oversized in the portion thereof in which the equiaxed defect tends to occur. The surplus metal is in the form of an appendage which can readily be removed by severing it from the body of the casting after solidification. Thus, any equiaxed defects are eliminated with the severing of the appendage, leaving the casting sound, homogeneous, and completely columnar.

The mold illustrated in FIGURE 2 is of the open ended, thin, relatively porous ceramic shell mold type. The mold is indicated generally at reference numeral 16, and provides an integral gate portion 17 which feeds a main casting cavity including an airfoil vane defining portion 18 and a root defining portion 19. The open end of the shell mold 16 is positioned on a chill block 21 consisting of a unetal having a high degree of thermal conductivity, such as copper. The mold, in accordance with the present invention, is also provided with a secondary cavity 22 contiguous with the vane defining portion 18, and located near the tip of the blade where, from experience, it has been found that the freckle type defect will mos-t likely occur.

While there are a number of ways of making the ceramic shell mold 16 for the purposes of the present invention, I particularly prefer that method for making refractory molds which is described in Mellen et al. US. Patent No. 2,932,864 of Apr. 19, 1960. In accordance with the procedure in describing that patent, a disposable pattern composed of wax, or the like, is dipped in an aqueous ceramic slurry having a temperature about the same as that of the pattern material to form a refractory layer of a few mils in thickness. A typical slurry may contain ceramic materials such as zirconium oxide, a binder such as colloidal silica, and a thickener and low temperature binder such as methyl cellulose. The initial layer while still wet is then dusted with small particles (40 to 200 mesh) of a refractory glass composition such as that known as Vycor which is a finely divided high silicon oxide glass containing about 96% silica and a small amount of boric :acid together with traces of aluminum, sodium, iron, and arsenic. The dusted wet refractory layer on the pattern can then be suspended on a conveyor and moved through a drying oven having -a controlled humidity and temperature, wherein the coated pattern is dried adiabatically.

The steps of dipping, dusting, and adiabatic drying are then repeated using air at progressively lower humidities for succeeding coats. For example, the first two coats can be dried with air having a relative humidity of 45 to 55%. The third and fourth coats can be dried with a relative humidity of to 45%, the fifth and sixth coats with a relative humidity of 25 to 30%, and finally the last coats with a relative humidity of 15 to 25%.

The first layer is preferably applied at a thickness of about 0.005 to 0.020 inch, and the fine refractory particles rare dusted onto the wet layer with sufiicient force to embed the particles therein. It is preferred that the dusting procedure used provide a dense uniform cloud of fine particles that strike the wet coating with substantial impact force. The force should not be so great, however, as to break or knock off the wet prime layer from the pattern. This process is repeated until a plurality of integrated layers is obtained, the thickness of the layers each being about 0.005 to 0.020 inch.

After the mold is built up on the pattern material, the pattern is removed by placing the fiame in a conventional steam autoclave operated at temperatures of about 300 to 350 F. After removal of the pattern material the green mold is ready for firing at temperatures on the order of 1500 to 1900" F. The resulting shell molds are hard, smooth, and relatively permeable, and measure on the order of A to A inch in thickness.

When the molten metal is poured into the mold 16 through the gate 17, assuming the mold to have been properly preheated, directional solidification will occur starting at the chill plate 21 and progressing upwardly. The metal also fills the secondary cavity 22 to provide an appendage 23 attached to the vane portion of the cast-ing. The secondary cavity 22 does not feed the casting in the same sense that a conventional riser feeds a part, but rather by virtue of its configuration and location provides a place other than the casting itself for the advancing solidification front to deposit these undesirable defects and constituents.

While the conditions of casting do not form any part of this invention, it should be realized that such casting will normally take place under vacuum conditions.

After solidification of the mold under controlled cooling conditions conducive to the formation of a completely columnar structure, the shell mold is broken away, leavring a casting as shown in FIGURE 3, including the appendage 23 integral with but severable from the airfoil vane portion 24 of the cast turbine vane 26. The finished casting has a shroud portion 27 and a relatively massive base 28. It is then relatively a simple matter to cut off the appendage 23 as illustrated by the dotted lines in FIGURE 4, leaving the casting sound, homogeneous, and exhibiting proper columnar structure in the entire area.

A comparison was made between molds embodying the secondary cavity and those not including the cavity. The test Was made on a six piece mold in which four of the six castings had the appendage, and two did not. The four which had the appendage were all acceptable upon microetch inspection, and the two castings without the appendage were found to be rejectable for freckles. All six parts were then X-rayed, and the four castings which had been made with the appendage were all acceptable by X-ray analysis, while the two cast without the appendages were both rejectable for porosity and segregation in the trailing edge of the vane portion.

While I have described a particularly preferred embodiment of the invention, as applied to a cast article of specific geometry, it should be understood that the process and apparatus of the present invention have applicability to other shapes produced by the columnar casting technique.

I claim:

1. The method of producing a columnar grained casting of a turbine blade which has a tendency to form equiaxed grain defects along a portion thereof which comprises providing a mold having a main casting cavity conforming to the shape of the turbine blade and having a vertically disposed gate portion arranged to deliver molten metal into said casting cavity, said cavity having a contiguous secondary cavity axially displaced from the vertical axis of both said gate portion and said main cavity and positioned at one upper edge of the portion of the casting cavity which forms the airfoil portion of the casting, pouring molten metal \into the main casting cavity until both the main cavity and said secondary cavity are filled with molten metal, rapidly abstracting heat from the bottom of the main casting cavity upwardly to thereby provide an advancing solidification front leading to directional solidification of the casting, continuing the abstraction of heat until the casting is directionally solidified and any segregating constituents are deposited and solidified in said secondary cavity to form an appendage to the casting, and severing said appendage from said casting.

References Cited UNITED STATES PATENTS Williams 29529 Koch et al. 164127 Ahlen 29529 X Chandley 164127 X Parsons 29--529 X Madono 164-127 Hartman et a1 16469 X Pekarek 253-77 Hein 164-859 I. SPENCER OVERHOLSER, Primary Examiner.

15 V. K. RISING, Assistant Examiner.