Blade Accessories TRIZ Cases

Notches on gas-turbine airfoil pressure surfaces remove material while limiting radial boundary-layer separation and airflow losses.

Asymmetric splitter vanes divide turbine exhaust flow into smaller paths, reducing separation while improving de-swirling without enlarging the engine.

Longer axial-flow turbine blades can create supersonic inflow and shock losses; shaped leading edges and expanded passages help limit entropy rise.

Machinable sacrificial coating or plies let CMC stator vane mounts align trailing edges during re-staggering without harming structural integrity.

Varying positive and negative camber end angles along the guide vane axis manages local flow, reducing losses and improving efficiency.

Localized micro-riblet patches on a turbine airfoil’s suction side disrupt turbulent vortices and reduce skin-friction losses.

Rotating stall cells in low-flow turbine operation can fatigue blades; angled segmented struts block reverse flow and reduce shear-layer gradients.

An insert and thickened CMC portion reinforce turbine mounting areas against mechanical forces while retaining resistance to combustion heat.

A metallic leading edge protector shields composite turbine airfoils from bird strikes and erosion while preserving flexibility.

A buttress reinforces the turbine blade shank under high loads while forming a pocket that supports cooling flow and reduces blade mass.

Solvent diffusion through sealed CMC plies counters evaporation during extended layup, supporting consistent consolidation and dimensions.

Water in the balance piston cavity absorbs heat and builds pressure, reducing thrust-bearing load and extending service life.

An oxidation-resistant abrasive layer and oriented blade-tip surface reduce coating wear, frictional heat, and substrate oxidation.

Silicon-containing brazing joins separate CMC airfoils and platforms into robust static vane clusters for high-temperature operation.

Locally terminating inner fiber plies at the leading edge helps reduce interlaminar stress and thermal gradients while preserving airfoil thickness and strength.

A tortuous seal path fills rotor blade–disk joint gaps, limiting fluid leakage while preserving the mechanical attachment.

The wavy connection in a fibrous blade-platform preform removes a preferred deformation axis and stiffens aircraft turbine components.

Segmenting the airfoil into composite and metallic sections localizes impact protection while keeping the rotor airfoil lightweight.

A seal cartridge separates the blade root from the disk slot to limit heat transfer and mechanical stress at the turbine interface.

Interdigitated ceramic-matrix-composite panels use staggered gaps to absorb thermal expansion, limit buckling, and preserve aerodynamic continuity.

Carbide particles in a ductile metal matrix help protect airfoil leading edges from erosion and abrupt coating failure.