Ceramic-metal composite assembly

Abstract

A ceramic-metal composite assembly includes an intermediate member made of a material having a thermal expansion efficiency between those of the materials forming a ceramic member and a metallic shaft member. The intermediate member is metallurgically joined to the ceramic member while being mechanically joined to the metallic member to constitute a single unit.

Description

BACKGROUND OF THE INVENTION

1. Field of the Invention

The present invention relates to a ceramic-metal composite unit or assembly such as a ceramic turbocharger rotor, ceramic gas-turbine rotor, ceramic heating element, ceramic sensor, or the like which is used at a high temperature.

2. Disclosure Information

In recent years, ceramics have increasingly been used in various fields by the excellence of heat resistance, strength against thermal shock, mechanical strength at a high temperature, wear resistance, insulation, etc. However, the ceramics are not used alone but together with other materials such as metal so that they can show their excellent qualities.

An investigation has hereinbefore been made on how to unite a ceramic member and a metallic member with a view to obtaining a single unit or assembly having a high joint strength. This is because when the ceramic member and the metallic member are simply brazed together to constitute a single unit residual stresses are caused at the ceramic-metal joint portion due to the difference in thermal expansion efficiency between the ceramic material and the metallic material, thus causing decrease of the joint strength and therefore making it impossible to attain a sufficiently large joint strength.

This problem is pronounced when such a composite assembly is used at a high temperature.

To solve such a problem, it has been proposed to join a ceramic member and a metallic member by press fitting as disclosed in Japanese Patent Provisional Publication No. 62-191478.

To the same end, it has also been proposed to fit a ceramic member in a metallic member and fill the clearance between them by silver solder for thereby joining them together as disclosed in Japanese Patent Provisional Publication No. 2-149477.

In either of such prior art structures, the metallic member is made of an alloy such as Incoloy 903, having a low thermal expansion efficiency and consisting of Fe--Ni--Co alloy and precipitation hardening elements as Ti, Nb, Al, etc. However, by the use of such an alloy only, a favorable result cannot be attained. This is because there is a considerable difference in thermal expansion efficiency between the ceramic member and the metallic member, that is, the thermal expansion efficiency of Incoloy 903 used for forming the metallic member is for example 2.1 (.times.10.sup.-6 /.degree. C.) at 30.degree..about.400.degree. C., whilst the thermal expansion efficiency of silicon nitride used for forming the ceramic portion is 8.2 (.times.10.sup.-6 /.degree. C.) at 30.degree..about.400.degree. C.

As a result, when either of such prior art composite assemblies is used at a high temperature, the metallic member is expanded more than the ceramic member to make it impossible to retain a sufficient interference therebetween, thus causing a problem that the joint strength is lowered and in some case the ceramic member can be dropped off from the metallic member.

SUMMARY OF THE INVENTION

It is an object of the present invention to provide a ceramic-metal composite assembly which has a sufficiently large joint strength even when it is used at a high temperature.

It is a further object of the present invention to provide a ceramic-metal composite assembly of the above described character which has a sufficiently large interference at the ceramic-metal joint portion even when it is used at a high temperature.

It is a further object of the present invention to provide a ceramic-metal composite assembly of the above described character which is suited for adoption to a turbocharger rotor.

According to the present invention, there is provided a ceramic-metal composite assembly which comprises a ceramic member, a metallic member, and an intermediate member having a thermal expansion efficiency between those of the ceramic member and the metallic member, in which the intermediate member is chemically or metallurgically joined to the ceramic member whilst being mechanically joined to the ceramic member.

The metallurgical joining means for joining the ceramic member and the metallic member together can be brazing, diffusion joining or welding, joining by the use of oxide, friction welding, hot pressing, hot isostatic pressing, etc. More specifically, brazing by the use of an active brazing metal selected from the group of metals consisting of AG--Cu--Ti alloys, Cu--Ni--Ti alloys, Cu--Ti alloys, joining by heating by the use of a mixture of ceramic materials including Al.sub.2 O.sub.3, TiO.sub.2, SiO.sub.2, etc. and hot pressing by interposing between the joining portions a metal selected from the group of metals consisting of Fe--Ni--Cr alloys, Ni--Cr--Si alloys, Ni--Cr alloys and Nb are more desirable for such a metallurgical joining means.

The mechanical joining means for joining the metallic member and the intermediate member together can be press fitting, shrink fitting and fastening with bolts or screws.

While the material for the metallic member can be a material of low thermal expansion efficiency such as carbon steel, alloy steel, heat resisting steel, stainless steel, Incoloy 903 or all of structural materials such as heat resisting alloys, Ni alloys, Cu alloys, it is more desirable such a material having a thermal expansion efficiency close to that of the intermediate member since the composite assembly can have a larger joint strength.

The material for the intermediate member is selected on the basis of an optional combination of a ceramic material and a metallic material which are selected from the above described materials, in such a manner that its thermal expansion efficiency is between those of the ceramic material and the metallic material. For example, it can be either a ceramic material or a metallic material such as W alloys, super hard alloys, composite material of Si3N4--TiN, Incoloy 903.

In this instance, shown in Table 1 are the thermal expansion efficiencies of the ceramic member, intermediate member and metallic member, and shown in Table 2 are desirable combinations thereof. In the meantime, those materials can be selected variously for constituting various combinations and therefore each cannot be limited to one of the ceramic member, metallic member and the intermediate member.

TABLE 1______________________________________ Thermal expansionSample efficiency(x10.sup.-6 /.degree.C.)No. Material Composition 30 .about. 400.degree. C. 30 .about. 700.degree. C.______________________________________1 silicon 10 wt % of Al.sub.2 O.sub.3, 2.1 2.6 nitride Y.sub.2 O.sub.3 ; the remainder is Si.sub.3 N.sub.42 alumina 5 wt % of SiO.sub.2, 7.0 7.7 CaO, MgO; the remainder is is Al.sub.2 O.sub.33 silicon 30 wt% of TiN; 2.8 3.8 nitride- the remainder TiN is Si3N44 Incolony 38 wt % of Ni, 8.2 10.7 903 15 wt % of Co, 0.7 wt % of Al, 1.4 wt % of Ti, 3 wt % of Nb; the remainder is Fe5 W alloy 5 wt % of Fe, Ni; 5.1 5.4 the remainder is W6 supper 10 wt % of Co; 4.8 5.3 hard the remainder alloy is WC7 heat JIS-SUH616 11.9 12.1 resisting steel8 alloy steel JIS-SNCM439 13.9 14.3______________________________________ TABLE 2______________________________________ Ceramic Intermediate MetallicNo. member member member______________________________________A silicon nitride W alloy alloy steelB silicon nitride super hard heat resisting hard alloy steelC silicon nitride silicon stainless steel nitride-TiND silicon nitride super hard Incoloy 903 alloyE alumina Incoloy 903 stainless steelD alumina Incoloy 903 stainless steel______________________________________

In the meantime, since the intermediate member and the metallic member are mechanically joined together, a metallic material is more desirable for forming the intermediate member when selected from among the materials having substantially the same thermal expansion efficiency. This is because the outer surface of the intermediate member made of a metallic material can be rough to some extent in assembly and therefore an increased flexibility in assembly is attained.

Further, the difference in thermal expansion efficiency between the intermediate member and the ceramic member is desirable to be equal to or smaller than 4.times.10.sup.-6 /.degree. C. and further desirable to be equal to or smaller than 3.times.10.sup.-6 /.degree. C.

Further, while the method of joining the intermediate member and the ceramic member has been described as above, an intermediate member made of a soft metal such as Ni, Cu, Fe or an intermediate member made of a heat resisting soft metal such as Ni--Cu alloys may be interposed between the intermediate member and the ceramic member in accordance with the necessity.

Such a ceramic-metal composite assembly can prevent decrease of the joint strength at a high temperature since the intermediate member has a thermal expansion efficiency between those of the ceramic member and the metallic member and can decrease the thermal stresses resulting when it is used at a high temperature.

Further, since the intermediate member is metallurgically joined with ceramic member to constitute a united sub-assembly whilst the intermediate member and the metallic member are mechanically joined together by interference fit, etc., a sufficient interference in a radial direction between the intermediate member and the metallic member can be maintained even when each members are heated to expand since the difference in thermal expansion efficiency between the intermediate member and the metallic member is small. That is, a sufficient interference can be retained at the time of usage of the composite assembly at a high temperature, thus making it possible to prevent decrease of the joint strength with which the ceramic member and metallic member are joined together.

BRIEF DESCRIPTION OF THE DRAWINGS

FIG. 1A is a perspective view of a ceramic-metal composite assembly according an embodiment of the present invention;

FIG. 1B is a sectional view of the composite assembly of FIG. 1A;

FIGS. 2A-2C and 3A-3B are views for illustrating the method of producing the composite assembly of FIG. 1;

FIG. 4 is a view for illustrating the method of testing the assembly of FIG. 1; and

FIGS. 5 through 10 are sectional views of ceramic-metal composite assemblies according to further embodiments of the present invention.

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS

Referring first to FIG. 1, a ceramic-metal composite assembly according to an embodiment of the present invention mainly consists of a metallic member 2 made of heat resisting steel (e.g. JIS-SUH 616), a ceramic member 5 made of silicon nitride, and an intermediate member 6 made of Incoloy 903. The metallic member 2 is hollow cylindrical to have a bore 4. The ceramic member 5 has an outer diameter substantially equal to the diameter of the bore 4 and is integrally connected to the metallic member 2 by way of the intermediate member 6 which is fitted in the bore 4 of the ceramic member 2. The assembly 1 is provided with an intermediate layer 7 which is made of a soft metal and interposed between the ceramic member 3 and the intermediate member 6.

The ceramic member 5 and the intermediate member 6 are joined by heating, that is, joined chemically or metallurgically by way of the intermediate layer 7. On the other hand, the metallic member 2 and the intermediate member 6 are joined mechanically by press fitting the intermediate member 6 in the bore 4 of the metallic member 2. In brief, disposed between the ceramic member 5 having a smaller thermal expansion efficiency and the metallic member 2 having a larger thermal expansion efficiency is the intermediate member 6 having a thermal expansion efficiency intermediate between those of the metallic member 2 and the ceramic member 5.

In the meantime, the dimensions of each members are shown in Table 3. Of the members, the metallic member 2 is made of JIS-SUH 616 and machined after quenching and tempering according to the Japanese Industrial standards (JIS), whilst the intermediate member 6 be aged by heating at a temperature of 720.degree. C. for 8 hours and at a temperature of 620.degree. C. for 8 hours.

TABLE 3______________________________________Metallic member outer dia.: 16 mm, length: 25 mm, inner dia.: 9.94 mm (chamfering of bore end: C 3.0 mm)Ceramic member dia.: 11 mm, length: 20 mm (chamfering at an end: C 1.0)Intermediate member dia.: 11 mm, length: 5.0 mmIntermediate layer dia.: 11 mm, thickness: 0.5 mm______________________________________

The method of producing such a composite assembly 1 will be described with reference to FIGS. 2A-2C and 3A-3B in which the different scales are employed only for convenience of illustration.

Firstly, as shown in FIG. 2A, the intermediate layer 7 is formed between the ceramic member 5 and the intermediate member 6. The intermediate layer 7 is formed by laying one upon another and in the following described order from the ceramic member 5 side a Ti foil 7a of the thickness of 0.003 mm, a Cu foil of the thickness of 0.02 mm, a Ni plate 7c of the thickness of 0.5 mm and a Cu foil 7d of the thickness of 0.02 mm.

Then, the ceramic member 5 and the intermediate member 6 with the intermediate layer 7 being constructed and arranged in the above manner therebetween are heated in the vacuum of 10.sup.-5 torr and at a temperature of 1200.degree. C. for 1 hour, so that the ceramic member 5 and the intermediate member 6 are joined to constitute a single unit or united subassembly 10.

Then, the entire of the outer circumferential surface of the united subassembly 10 is ground by the use of a diamond grinder so that the outer diameter of the united subassembly 10 is sized to 10 mm. Further, as shown in an enlarged scale in FIGS. 2B and 2C, an end of the intermediate member 6 is machined to have a chamfer of 1 mm and a gradually slanted portion 12 slanted at an angle of 4.degree. at a location inside of the chamfer 11.

Further, as shown in FIG. 3A, the metallic member 2 which is hollow cylindrical is formed with a beveled portion 15 at an end of the bore 4 so that the beveled portion 15 constitutes a guide opening 16 for insertion of the integral unit 10 into the bore 4.

Then, as shown in FIG. 3B, the intermediate member 6 of the subassembly 10 is press fitted by 3 mm in length into the metallic member 2 through the guide opening 16 at a speed of 0.5 mm/min. to constitute the united assembly 1 shown in FIG. 1.

The united assembly 1 of this embodiment produced in this manner is small in the difference in thermal expansion efficiency between the intermediate member 6 and the metallic member 2 and therefore can retain a sufficient interference at a high temperature and therefore can attain a large joint strength. Accordingly, the assembly 10 is superior in durability to a comparable prior art assembly and has such a joint strength that is large enough to enable production of a large-sized composite assembly.

Then, for assuring the effect of this embodiment description will be made to test sample.

Various test samples made of different materials were prepared and tested for a dropping-off load at a high temperature in order to examine the joint strength of the composite assembly 1 of this embodiment.

The measurement of the dropping-off load were made by first placing, as shown in FIG. 4, the ceramic member 5 of the composite assembly 1 inside of an annular block 19 whilst allowing the metallic member 2 to abut upon the upper surface of the annular block 19, then pushing the subassembly 10 downward at a loading speed of 0.5 mm/min. and measuring the load by which the subassembly 10 were dropped off from the metallic member 2. The result of measurements is shown in Table 4.

Further, such comparative examples were prepared in which no intermediate member was used but the metallic member and the ceramic member were directly joined together by press fitting to constitute an assembly of 25 mm in length though the ceramic member and metallic member were made of the same materials with those of the above described embodiments. The result of measurement is shown in Table 4.

TABLE 4______________________________________Test Ceramic Metallic Intermediate Dropping-offsample No. member member member load (kgw)______________________________________Samples of this invention1 silicon W alloy SUH616 300 and more nitride (10 wt % of Al.sub.2 O.sub.3, Y.sub.2 O.sub.3 ; the remainder is Si.sub.3 N.sub.4)2 silicon W alloy Incoloy 903 300 and more nitride3 silicon super SUH616 300 and more nitride hard alloy4 silicon Si3N4- Incoloy 903 240 nitride 0TiNComparative examples5 silicon not Incoloy 903 140 nitride provided6 silicon not SUH616 0 nitride provided______________________________________

In the above table 4, the ceramic member is made of silicon nitride consisting of 10 wt % of Al.sub.2 O.sub.3, Y.sub.2 O.sub.3 and the remainder of Si.sub.3 N.sub.4. SUH616 is a heat resisting steel whilst being a material for quenching and tempering. Incoloy is a material for hardening by aging.

As will be apparent from Table 4, the composite assembly of this invention has a large dropping-off load of 240 Kgw and is therefore desirable since it can obtain a large joint strength at a high temperature, whilst the comparative examples have a small dropping-off load of 140 Kgw and is therefore undesirable.

FIG. 5 shows a ceramic-metal composite rotor 20 for a turbocharger according to a further embodiment of the present invention. The rotor 20 includes a ceramic turbine wheel 21 made of silicon nitride and having a stub shaft 21a, an intermediate member 22 made of W alloy and joined to the stub shaft 21a of the ceramic wheel 21 by way of a Ni plate 23 to constitute a united subassembly 24, and a metallic member 25 having a socket portion 26 in which the intermediate member 22 of the subassembly 24 is fitted. In the meantime, the socket portion 26 of the metallic member 25 has a wall surrounding the stub shaft 21a of the ceramic turbine wheel 21 and having an annular recess 27 so as not to directly contact the stub shaft 21a, i.e., so as to provide a space between the wall of the socket portion 26 and the stub shaft 21a.

In production of the ceramic-metal composite rotor 20, the turbine wheel 21 and the intermediate member 22 of 10 mm in diameter with a Ni plate 23 being interposed between the stub shaft 21a and the intermediate member 22 are joined by heating to constitute the subassembly 24. On the other hand, the metallic member 25 made of heat resisting steel (JIS-SUH616) is treated by a predetermined quenching and tempering process so as to be as hard as HRC 34 and is formed with the socket portion 26 of 9.94 mm in inner diameter. The intermediate member 22 of the subassembly 24 is press fitted in the socket portion 26 of the metallic member 25 to constitute the composite rotor 20.

The composite rotor 20 was installed in a turbine housing and subjected to a rotation test in which it was rotated at a speed of 100,000 rpm and at an exhaust gas temperature of 950.degree. C. for 50 hours. By this test, a favorable results was obtained, i.e., no cracks or breakage and no movements at the joining portions were found.

FIG. 6 shows a ceramic-metal composite rotor 30 according to a further embodiment though its lower half is omitted for convenience of illustration. This embodiment differs from the previous embodiment of FIG. 5 in the material forming the intermediate member 31. The intermediate member 31 is made of a super hard alloy which has a litter smaller thermal expansion efficiency than W alloy. The intermediate member 31 is joined to the turbine wheel 33 by way of the Ni plate whilst being press fitted in the metallic member 34.

Accordingly, this embodiment can produce substantially the same effect with the previous embodiment of FIG. 5.

FIG. 7 shows a ceramic-metal composite rotor 40 according to a further embodiment. The turbocharger rotor 40 differs from the previous embodiment of FIG. 6 in that an annular recess 41 is not provided to the metallic member 42 but to the subassembly 46 made up of a turbine wheel 43, Ni plate 44 and an intermediate member 45.

This embodiment can produce substantially the same effect to the previous embodiments of FIGS. 5 and 6.

FIG. 8 shows a ceramic-metal composite rotor 50 according to a further embodiment. This embodiment is substantially similar to the previous embodiment of FIG. 7 except that the metallic member 51 consists of a socket portion 51a formed with a socket recess 52 and made of Incoloy 903 and a shaft portion 51b made of alloy steel (JIS-SNCM439).

To obtain the metallic member 51, the socket portion 51a is first joined to the shaft portion 51b by friction welding and then aged by heating at a temperature of 720.degree. C. for 8 hours and at a temperature of 620.degree. C. for 8 hours. Thereafter, the shaft portion 51b is hardened by high-frequency induction hardening. Finally, the socket portion 51a is finished to complete the metallic member 51.

This structure enables usage of the rotor 50 at a higher temperature than the previous embodiment of FIG. 7 since the difference in thermal expansion efficiency between the intermediate member 53 and metallic member 51 is small. Except for this, this embodiment can produce substantially the same effect to the previous embodiment of FIG. 7.

FIG. 9 shows a ceramic-metal composite rotor 60 according to a further embodiment of the present invention. This embodiment is substantially similar to the previous embodiment of FIG. 8 except that the metallic member 61 consists of a socket portion 61a formed with a socket recess 62 and made of Incoloy 903 and a shaft portion 61b made of alloy steel (JIS-SNCM439), which socket portion 61a and shaft portion 61b are joined together by electron beam welding. The shaft portion 61b has an end extending through the socket portion 61a to partially define the bottom of the socket recess 62.

This embodiment can produce substantially the same effect to the previous embodiment of FIG. 8.

FIG. 10 shows a ceramic-metal composite rotor 70 according to a further embodiment. This embodiment is substantially similar to the previous embodiment of FIG. 5 except that the subassembly 71 consists of a turbine wheel 72 made of silicon nitride, Ni plate 73, a composite material plate made of Si3N4--30TiN and an intermediate member 76 made of W alloy.

This embodiment makes it possible to use the rotor 70 at a higher temperature than the previous embodiment of FIG. 5 since the composite material plate 74 has a thermal expansion efficiency between those of the silicon nitride and W alloy.

Claims

1. A ceramic-metal composite rotor comprising:

(A) a ceramic wheel having a stub shaft;

(B) a metallic shaft having at an end a socket portion;

(C) an intermediate member made of a material having a thermal expansion efficiency between those of the materials forming said ceramic wheel and said metallic shaft;

said intermediate member constituting an extended part of said stub shaft and being fitted in said socket portion of said metallic shaft;

(D) metallurgical joining means for joining said intermediate member to said stub shaft; and

(E) mechanical joining means for joining said intermediate member to said socket portion of said metallic shaft.

2. A ceramic-metal composite rotor according to claim 1, wherein said ceramic wheel is made of a material consisting of Si.sub.3 N.sub.4, said metallic shaft is made of heat resisting steel, and said intermediate member is made of W alloy.

3. A ceramic-metal composite rotor according to claim 1, wherein said ceramic wheel is made of a material consisting of Si.sub.3 N.sub.4, said metallic shaft is made of heat resisting steel, and said intermediate member is made of supper hard alloy.

4. A ceramic-metal composite rotor according to claim 1, wherein said ceramic wheel is made of a material consisting of Si.sub.3 N.sub.4, said socket portion of said metallic shaft is made of Incoloy 903, and said intermediate member is made of super hard alloy, said metallic shaft having a shaft portion made of alloy steel and joined to said socket portion by friction welding.

5. A ceramic-metal composite rotor according to claim 1, wherein said ceramic wheel is made of a material consisting of Si.sub.3 N.sub.4, said socket portion of said metallic shaft is made of Incoloy 903, and said intermediate member is made of super hard alloy, said metallic shaft having a shaft portion made of alloy steel and joined to said socket portion by beam welding, said socket having an axial opening whilst said shaft portion having an axial protrusion fitted in said axial opening.

6. A ceramic-metal composite rotor according to claim 1, wherein said metallurgical joining means comprises joining by heating said ceramic member and said intermediate member in a vacuum while interposing therebetween an intermediate layer consisting of a sheet of Ni.

7. A ceramic-metal composite rotor according to claim 1, wherein said metallurgical joining means comprises joining by heating said ceramic member and said intermediate member in a vacuum while interposing therebetween an intermediate layer consisting of a sheet of Ni, a plate of a composite material consisting of Si3N4--3OTiN, and a sheet of Ni.

8. A ceramic-metal composite rotor according to claim 1, wherein said mechanical joining means comprises press fitting.

9. A ceramic-metal composite rotor according to claim 8, wherein said socket portion of said metallic shaft has a wall surrounding said stub shaft of said ceramic turbine wheel, said wall having an annular recess for providing a space between said wall and said stub shaft.

10. A ceramic-metal composite rotor according to claim 9, wherein said socket portion of said metallic shaft has a wall surrounding said stub shaft of said ceramic turbine wheel, said stub shaft having an annular recess for providing a space between said wall and said stub shaft.

11. A ceramic-metal composite rotor as claimed in claim 1, wherein said metallurgical joining means (D) is selected from the group consisting of brazing; diffusion joining or welding; joining by the use of an oxide; friction welding; hot pressing; and hot isostatic pressing.

12. A ceramic-metal composite rotor as claimed in claim 11, wherein said metallurgical joining means is brazing by the use of an active brazing metal selected from the group consisting of Ag--Cu--Ti alloys; Cu--Ni--Ti alloys; Cu--Ti alloys; and a mixture of Al.sub.2 O.sub.3, TiO.sub.2 and SiO.sub.2.

13. A ceramic-metal composite rotor as claimed in claim 11, wherein said metallurgical joining means comprises hot pressing by interposing between said ceramic wheel shaft (A) and said intermediate member (C) the joining portions of a metal selected from the group consisting of Fe--Ni--Cr alloys; Ni--Cr--Si alloys, Ni--Cr alloys and Nb.

14. A ceramic-metal composite rotor as claimed in claim 1, wherein said mechanical joining means (E) is selected from the group consisting of press fitting, shrink fitting and fastening with bolts or screws.

15. A ceramic-metal composite rotor as claimed in claim 1, wherein said ceramic wheel (A) is made of a ceramic material selected from silicon nitride and alumina.

16. A ceramic-metal composite rotor as claimed in claim 1, wherein said metallic shaft (B) is made of a material selected from the group consisting of alloy steel, heat resisting steel, stainless steel and Incoloy 903.

17. A ceramic-metal composite rotor as claimed in claim 1, wherein said intermediate member (C) is made of a material selected from the group consisting of tungsten alloy, super hard alloy, silicon nitride--TiN and Incoloy 903.