Engine Manufacture TRIZ Cases

Integrated capsular skin with apex channels attenuates low-frequency aircraft noise while simplifying industrial manufacturing.

A turbine rotor blade fixing structure uses a mechanical latch with bent portions to secure blades without welding.

A multi-sectional acoustic septum extends vertically within honeycomb cells to increase effective acoustic length and target specific frequency ranges.

Position selector locks variable nozzle airfoils into preselected clocking positions, eliminating complex actuated linkages and reducing maintenance costs.

Segmented radial modules minimize pressure loss and thrust reduction by eliminating elaborate piping while maintaining thermal stress resistance.

Segmented K-shaped CMC sectors connect via rigid gaskets and spring holders to reduce cooling needs while maintaining sealing integrity.

A turbine nozzle suction side bulge modifies local fluid flow to enhance root reaction, reducing secondary swirl that degrades diffuser performance.

Interdigitated turbine section accelerates combustion gases via rotating airfoils, eliminating nozzle guide vanes and reducing cooling air consumption.

Specific Cartesian coordinates position cooling holes on the airfoil to mitigate high temperatures while minimizing engine efficiency penalties.

Upstream strut placement reduces axial length and weight while maintaining mixing efficiency in turbofan engines.

An inflection point in the aft body curvature produces subsonic shock pressure recovery, reducing blockage penalties while maintaining structural strength.

Varying wall angles along the diffuser length matches energy-rich and energy-poor flow conditions, preventing separation and improving pressure recovery.

A pivoting instrument bar rotates on a nacelle axis to enable internal maintenance, eliminating crane operations and personnel climbing hazards.

A shroud recess redirects and traps impeller fragments, transferring kinetic energy to resolve weight and containment trade-offs.

Endwall convex portions alleviate pressure gradients to reduce secondary-flow loss caused by clearance leakage.

A turbine blade manufacturing method adjusts airfoil thickness distribution to achieve a safety factor of at least 1.5.

A variable thickness refractory metal core forms cooling passages with tailored cross-sectional areas to optimize thermal performance in gas turbine components.

Merging the splitter ring with the outer band eliminates custom fasteners, reducing assembly complexity while maintaining attachment strength.

Segmented grooves and bumps on rotor discs redirect low cycle fatigue cracks toward the gaspath surface, preventing radial propagation to the bore.

Segmented bearing covers protect rotor blade hubs from environmental exposure while simplifying assembly and maintenance access.

Internal fins integrated into the airfoil root dissipate vibrations via friction, reducing flutter and extending blade life without adding weight.

Specified Cartesian coordinates define the turbine blade airfoil profile, resolving complex strain modeling challenges while ensuring stress-resistant designs.

Differential port sizing utilizes the Coanda effect to prevent flow separation and maintain efficiency during radial expansion.

A core nacelle with selectively exposed grooves changes the fan exhaust nozzle cross-sectional area to manage airflow dynamics.

A turbine airfoil internal cooling channel uses a flow splitter feature to increase coolant velocity near pressure and suction sidewalls.

Elliptical through bores in turbomachine rotor disks minimize material load and extend service life under high mechanical stress.

Variable width pultrudate layers reduce material waste and improve fatigue strength by optimizing load distribution in wind turbine rotor blades.

Dual-wall heat shield design with an internal air gap limits thermal transfer to the turbocharger bearing housing.

Concentric high and low rotor towershafts minimize axial length and weight while maintaining critical speed margins.

A concave indentation on the fan disk periphery directs ingressing water downward away from the nose cone.

An annular acoustic attenuation structure uses composite skins and partitions where fiber reinforcement extends into the skins to join components.

Segmented wedge-shaped sealing fins improve reliability by reducing hot gas ingress and wear on the sealing device.

Segmented turbine modules and universal interfaces enable maintenance access without exposing bearing compartments to ambient contaminants.

Electromagnetic signal devices in bushings align rotor blade segments, resolving the trade-off between assembly simplicity and mechanical precision.

Segmented standard panels with universal flanges reduce mold complexity and simplify logistics for large nacelle canopies.

Shield prevents hot air recirculation to reduce turbine casing thermal expansion and maintain blade clearance.

Secures load carrying structures against tilting movements to reduce unbalanced tower loadings and material costs.

A fiber-reinforced plastic membrane bonds to wind turbine rotor blades to restore structural integrity and extend service life.

Composite blisk blade inserts bridge bulb and disk grooves to maintain secure retention under centrifugal forces.

Segmented serpentine channels distribute cooling air across leading and trailing edges to resolve uneven temperature distribution in turbine blades.

Predetermined film hole placement stabilizes airflow and improves cooling efficiency by separating turbulent surface flow from laminar passage flow.

Tensioned cables guide loads parallel to towers, preventing collisions during high wind operations.

Tapered mould inlays customize blade root diameters, reducing dry spots and improving resin distribution efficiency.

Segmented cooling openings leverage centrifugal forces and film layers to eliminate hot spots, extending blade lifespan while reducing fluid consumption.

A flute in the concave rounded portion of a turbine blade root increases flexibility to distribute mechanical loading more uniformly.

A turbine bucket airfoil profile defines a throat with varying gap width between adjacent blades to enhance fluid flow.

Segmented cover creates shear layer to cool high-temperature bleed air injected during failed valve conditions.

A magnetic shim system positions impact liner panels on fan casings, resolving axial alignment accuracy against assembly time.

A counter rotating turbine uses a reversing reduction gear assembly to drive components at independent speeds.