Abstract A rotor for a gas turbine engine has a wrought superalloy disk with ceramic blades. The rotor is formed by placing ceramic blades in a fixture with their ceramic blade roots extending inwardly and between the upper and lower rims of a disk or disk halves. The facing upper and lower circumferential rims are cut away to provide for the ceramic blade roots. Said disk or disk halves being of a wrought superalloy having a fine grain size microstructure which can be placed in a superplastic condition. A compliant layer material is placed between the ceramic blade roots and the rims of the disk, and the disk and compliant layer are then heated so as to place the disk in a superplastic condition and pressed into intimate contact with the ceramic blade root, and if disk halves are being used, they are bonded together at inner mating surfaces. The rotor is then heat treated to return the disk to its normal condition of high strength and hardness. The compliant layer can be a thin layer of material inserted between the blade root and disk, or it can be a material applied directly to the blade root or disk slot such as by plating, sputtering, or flame spraying.
Method of forming a turbine rotor having a superalloy disk with ceramic blades, including the steps of: 1. forming ceramic blade members having a root section with an enlargement thereon, 2. holding said ceramic blades together with the root sections projecting radially inward, 3. placing a compliant layer around said root sections, 4. forming two disk halves of a wrought superalloy having a fine grain size microstructure which can be placed in a superplastic condition, 5. contouring the outer circumference of each disk half to accommodate the ceramic blade root and compliant layer, 6. aligning said disk halves so that the contoured circumferences will contact the compliant layer, 7. placing said disk halves in a superplastic condition, 8. pressing said disk halves together while they are in said superplastic condition to place the contoured circumference, compliant layer and blade roots in surface-to-surface contact placing the blade roots in compression.
Claim 2
Dependent Claim
149 words
Method of forming a turbine rotor having a superalloy disk with ceramic blades, including the steps of: 1. forming ceramic blade members having a root section with an enlargement thereon, 2. holding said ceramic blades together with the root sections projecting radially inward, 3. placing a compliant layer around said root sections, 4. forming two disk halves of a wrought superalloy having a fine grain size microstructure which can be placed in a superplastic condition, 5. contouring the outer circumference of each disk half to accommodate the ceramic blade root and compliant layer, 6. aligning said disk halves so that the contoured circumferences will contact the compliant layer, 7. placing said disk halves in a superplastic condition, 8. pressing said disk halves together while they are in said superplastic condition to place the contoured circumference, compliant layer and blade roots in surface-to-surface contact placing the blade roots in compression.
Claim 3
Dependent Claim
30 words
A method as set forth in claim 1 including the following step (9) heat treating said disk halves to return them to their normal condition of high strength and hardness.
Claim 4
Dependent Claim
27 words
A method as set forth in claim 1 wherein step (8) said disk halves are diffusion bonded at a meeting surface located inwardly of the outer circumference.
Claim 5
Dependent Claim
32 words
A method as set forth in claim 1 wherein step (7) the disk halves are heated to a temperature which is greater than the temperature of the environment of their intended use.