Composite turbomachinery rotor

Claim 2

A turbomachinery blade comprising an airfoil section fabricated of a plurality of bonded filament laminates and a pair of hollow inserts, each insert having a generally semicylindrical outer arcuate surface, and wherein said laminates extend from the airfoil section, pass between said inserts and then are divided into two portions, each portion being wrapped essentially 180° around the outer arcuate surface of one of said inserts before being led back into the airfoil section, thereby forming a generally cylindrical, rotatable root for the blade.

Claim 3

A turbomachinery rotor comprising: a rotatable hub having a generally cylindrical groove in the periphery thereof; and a blade having an airfoil section fabricated of a plurality of bonded filament laminates and a pair of hollow inserts, each insert having a generally semicylindrical outer arcuate surface, and wherein said laminates extend from the airfoil section, pass between said inserts and then are divided into two portions, each portion being wrapped essentially 180° around the outer arcuate surface of one of said inserts before being led back into the airfoil section, thereby forming a generally cylindrical rotatable root for the blade, and wherein the root is received within the groove for rotation therein with respect to said hub.

Claim 4

A turbomachinery rotor comprising: a rotatable hub having a generally cylindrical groove in the periphery thereof; and a blade having an airfoil section fabricated of a plurality of bonded filament laminates and a pair of hollow inserts, each insert having a generally semicylindrical outer arcuate surface, and wherein said laminates extend from the airfoil section, pass between said inserts and then are divided into two portions, each portion being wrapped essentially 180° around the outer arcuate surface of one of said inserts before being led back into the airfoil section, thereby forming a generally cylindrical rotatable root for the blade, and wherein the root is received within the groove for rotation therein with respect to said hub.

Claim 5

The turbomachinery rotor as recited in claim 2 wherein the laminates comprise boron filaments embedded in an aluminum matrix.

Claim 6

The turbomachinery rotor as recited in claim 2 wherein the groove is relieved at the entrance thereof such that the entrance width exceeds the blade airfoil thickness thereby permitting circumferential rotation of the blade within the groove.

Claim 7

The turbomachinery rotor as recited in claim 2 wherein the laminates comprise a plurality of high strength, elongated filaments embedded in an organic resin binder.

Claim 8

The turbomachinery rotor as recited in claim 5 wherein the laminates comprise graphite filaments embedded in an epoxy resin binder.

Claim 9

A turbomachinery rotor comprising: a rotatable hub having a generally cylindrical groove in the periphery thereof; a blade having an airfoil portion and a root portion, said blade including a pair of laterally separated, hollow inserts, each having a generally semicylindrical arcuate surface; and a plurality of composite filament laminates extending from the airfoil portion to the root portion, said laminates passing between and bonded to said inserts wherein substantially half of said laminates are wrapped essentially 180° around the arcuate surface of each insert and back into the airfoil portion to provide a generally cylindrical profile to the root portion, and wherein the root portion is received within the groove; and bolt means having a head, a threaded end and a shoulder of larger diameter than the threaded end, the bolt having an axial slot extending from the threaded end and through the shoulder to separate the shoulder into two portions, each shoulder portion inserted within, and of substantially the same contour as, the hollow interior of one of said inserts.

Claim 10

A turbomachinery rotor comprising: a rotatable hub having a generally cylindrical groove in the periphery thereof; a blade having an airfoil portion and a root portion, said blade including a pair of laterally separated, hollow inserts, each having a generally semicylindrical arcuate surface; and a plurality of composite filament laminates extending from the airfoil portion to the root portion, said laminates passing between and bonded to said inserts wherein substantially half of said laminates are wrapped essentially 180° around the arcuate surface of each insert and back into the airfoil portion to provide a generally cylindrical profile to the root portion, and wherein the root portion is received within the groove; and bolt means having a head, a threaded end and a shoulder of larger diameter than the threaded end, the bolt having an axial slot extending from the threaded end and through the shoulder to separate the shoulder into two portions, each shoulder portion inserted within, and of substantially the same contour as, the hollow interior of one of said inserts.

Claim 11

The turbomachinery rotor as recited in claim 7 wherein the length of the shoulder portion exceeds the thickness of the hub at the groove.

Claim 12

The turbomachinery rotor as recited in claim 7 further comprising plug means inserted in the axial slot at the threaded end of the bolt means for preventing collapse thereof.

Claim 13

The turbomachinery rotor as recited in claim 9 further comprising a nut threaded onto said bolt means and cooperating with the head thereof to entrap the disc therebetween.