Gas Turbine Engine Compressor Blade Design in Siemens NX

Explore the gas turbine engine, an internal combustion system that uses air as the working fluid and converts fuel energy into mechanical power through inlet, compression, combustion, and exhaust sections.

Explore how a gas turbine engine generates power as air moves through intake, compression, combustion, and exhaust, and examine the blades’ role in energy distribution to the turbine and thrust.

Explore how compressor and turbine blades govern air intake and flow in a gas turbine, and how design and 3d modeling of industrial blade geometries underpin reliable engine performance.

Explore airfoil geometry and profiles, highlighting drag reduction for gas turbine blades and aircraft wings, and prepare to design blades with accurate geometry for low-drag performance.

Explore aerofoil geometry by defining the leading and trailing edges, upper concave and lower convex surfaces, and local thickness using circles to construct the blade profile and inspect data.

Draw aerofoil profiles from tabulated coordinates and radius data to create accurate leading and trailing edges in Siemens NX, using data import, arc constraints, trimming, and tangential relationships.

Prepare aerofoil data for blade design by organizing X, Y, Z coordinates in an Excel sheet, defining concave and convex sections, and using a datum line to generate 3D airfoil.

Import coordinate data from Excel into Siemens NX annex to build section one aerofoil. Create the leading and trailing edge from concave and convex data, ensuring a constrained, tangent profile.

Import x, y, z coordinates from the Excel data to sketch aerofoil section iii-iii, generate convex and concave profiles with leading and trailing edges, and fully constrain the NX sketch.

Create the fifth cross section of aerofoil section V-V by importing coordinates from an Excel sheet, editing in notepad, and building the blade profile in Siemens NX.

Develop the axial dovetail root for a gas turbine compressor blade in Siemens NX by sketching a half cross-section, mirroring it for symmetry, and trimming with angled planes.

Introduce a more complex project to generate a radial-slot compressor rotor blade for an aircraft in Siemens NX, detailing the radial root and the radial dovetail route.

Prepare aerofoil data by organizing section coordinates into an Excel sheet with X, Y, CC and CV values, to define heights for the compressor blade in Siemens NX.

Create aerofoil section two in Siemens NX using coordinates from an Excel file, importing convex and concave data to generate cross-section. Apply constraints and fix endpoints to finalize blade section.

Learn to sketch airfoil sections in Siemens NX by importing X, Y, Z coordinates from Excel, constructing four profiles at different heights, and applying geometric constraints and arcs.

Sketch the fifth aerofoil cross-section V-V by importing coordinates from Excel into Siemens NX, assemble all five cross-sections, and generate the blade's main body.

Analyze the radial dovetail root drawing and blade route drawing orientation, then create a plane and cross-section at 48 degrees to the airfoil axis in Siemens NX.

Orient the sketch plane at 48 degrees to the route symmetry axis to create the root cross section of a gas turbine compressor blade in Siemens NX.

Explore the fifth project as you model an impeller from a drawing, using section data to understand the profile, generate error files, and create the complete body.

Prepare aerofoil profile data for Siemens NX by organizing section coordinates in x, y, z in Excel, converting to the required data format, creating section files, and readying for import.

Develop the impeller's main body by sketching the cross section, constraining dimensions, applying radii and diameters, then revolve the profile to form a single blade body and the blade set.

Generate all compressor blades in Siemens NX using a circular pattern around the z-axis. Create 12 blades with a 360-degree pitch, then trim the lower portion in the next video.

Trim and unite blade bodies in Siemens NX by selecting faces and planes, using trim and cut operations, to assemble a final gas turbine engine compressor blade design.

Create the blade contour by sketching a circle on the body plane, constraining its center and diameter, and revolving the sketch from 0 to 360 degrees to generate the contour.

Create a rectangular keyway slot on the impeller slug, using sketching and linear dimensions to position it 12.5 from the axis, then perform a through extrude to cut the feature.