Blisk model for CAM (free CAD download file) (video)

Designed in Siemens NX8

A blisk (or bladed disk) is a single engine component consisting of a rotor disk and blades, which may be either integrally cast, machined from a solid piece of material, or made by welding individual blades to the rotor disk. The term is used mainly in aerospace engine design. The word is a portmanteau of blade and disk, the two components it replaces in turbomachinery. Blisks may also be known as integrally bladed rotors (IBR).

This model is made for my colleague who is working CAM and he needed blisk model for his CAM project (you can see movie of CAM processes in this post). This is not model of real blisk as it is designed by edit of real turbo engine blade and merging it with custom disk, it is designed to be machined from a solid peace of material. This blade is only for show of CAM processes needed for machining this kind of model.

Two jet engine blades

Designed in Siemens NX6

two jet engine blades

The project was made for the Serbian Army at the Military Technical Institute. These two blades are designed using only CMM measuring. Characteristics of these two blades is that they are twisted around curved line with different air profiles across span, which make them little complicated to design in CAD without paper documentation.

Jet engine compressor double blade segment

Designed in Siemens NX6

Jet engine compressor segment

Design of compressor segment consisting of two blades. It is fuel injection segment with fuel spray nozzles. Design was made based on paper documentation and measuring the existing segment in MTI CMM laboratory.

Jet engine turbine fin 3

Designed in Siemens NX  

fin in work view

The project was made for the Serbian Army at the Military Technical Institute. Fin was designed based on paper documentation and the points obtained by measuring the existing wings in MTI CMM labaratory. Special attention was paid to the accuracy of shape and position of the control profiles, as well as the shape of wing root.

Jet engine compressor fin with horizontal reinforcement

Designed in Siemens NX

fin in work view

The project was made for the Serbian Army at the Military Technical Institute. Fin was designed based on paper documentation and the points were obtained by measuring the existing wings in MTI CMM labaratory. Special attention was paid to the accuracy of shape and position of the control profile, position and shape of the horizontal reinforcement, and the shape of wing root.

Jet engine turbine fin 2

Designed in Siemens NX

jet engine fin 

The project was made for the Serbian Army at the Military Technical Institute. Fin was designed based on paper documentation and the points where obtained by measuring the existing wings. Special attention was paid to the accuracy of shape and position of the control profiles, as well as the shape of fin root.

Jet engine turbine fin 1

Designed in Siemens NX

jet engine fin

The project was made for the Serbian Army at the Military Technical Institute. Fin was designed based on paper documentation and the points where obtained by measuring the existing wings. Special attention was paid to the accuracy of shape and position of the control profiles, as well as the shape of fin root.