Blisk

A blisk (portmanteau of bladed disk) is a turbomachine component comprising both rotor disk and blades. It consists of a single part, instead of an assembly of a disk and individual, removable blades. Blisks may be integrally cast, machined from a solid piece of material, or made by welding individual blades to a rotor disk. The term is used mainly in aerospace engine design. Blisks may also be known as integrally bladed rotors (IBR).

Blisk manufacturing has been used since the mid-1980s. It was first used by Sermatech-Lehr (now known as GKN Aerospace) in 1985 for the compressors of the T700 helicopter engine. Since then, its use has continued to increase in major applications for both compressors and fan blade rotors. Examples include the Rocketdyne RS-68 rocket engine and the General Electric F110 turbofan.

The F-35B variant of the Joint Strike Fighter uses blisks to achieve STOVL.

Engine manufacturer CFM International is using blisk technology in the compressor section of its Leap-X demonstrator engine program, which has completed full-scale rig testing.PowerJet SaM146 engines used on Sukhoi Superjet 100s are also equipped with blisks.

General Electric's TechX engines will also use blisks. The GEnx already uses blisks in some stages.

Instead of making bare compressor disks and attaching the blades later, blisks are single elements combining the two. This eliminates the need to attach the blades to the disk (via screws, bolts, etc.), thus decreasing the number of components in the compressor, while at the same time decreasing drag and increasing efficiency of air compression in the engine. The elimination of the dovetail attachment found on traditional turbine blades eliminates a source for crack initiation and subsequent propagation.

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