Engine Manufacture TRIZ Cases

Tangential drive axes orient accessory power takeoffs around the engine center, eliminating intermediate lay shafts that inflate envelope size.

Replacing fragile cylindrical rods with an elliptical ceramic core stabilizes the structure, preventing breakage and enabling robust cooling hole formation.

A chordal seal uses a curved face to maintain contact with adjacent flowpath components during engine operation.

Segmented trailing edge passages with variable pin dimensions reduce temperature gradients while minimizing aerodynamic losses.

Welding thermoplastic resin at joint interfaces eliminates bond-line failures and reduces manufacturing complexity in wind turbine rotor blades.

Imaginary hole patterns prevent shroud trimming from removing cooling passages, resolving manufacturing efficiency versus cooling reliability.

Integrated cutting tool geometry forms stress relief notches at tooth roots to minimize hoop stress concentrations and extend component life.

Inwardly positioned surfaces extend sliding lengths on Oldham coupling key portions, reducing surface pressure and preventing seizure in scroll compressors.

Serpentine cooling channels increase surface area to drop temperatures by 40 Kelvin while preserving core strength in thin-section airfoils.

Segmented convex parts on exhaust pipe protrusions reduce thermal stress by redirecting high-temperature gas flow away from critical tip regions.

Rounded particles fill honeycomb core cells to create a septum layer that reduces non-linearity and backpressure across wide frequency bands.

A thermoplastic resin insert joins rotor blade components through heating and cooling cycles to create a welded interface.

Convex pressure-side contours maintain constant passage cross-sections during thermal burn-back, preserving aerodynamic efficiency and flow capacity.

T-shaped partitions generate axial-flow near-wall passages that increase primary cooling surface area while reducing thermal gradient stress.

An integrated outlet guide vane assembly merges airfoil trailing edges into bifurcation leading edges using non-zero lean and sweep angles.

Curved doors redirect exhaust flow obliquely, reducing stopping distance by minimizing impingement on the auxiliary power unit inlet.

Two-stage curing prevents element displacement and telegraphing marks on porous layers, ensuring structural integrity.

Segmenting the main passage into multiple unit passages distributes high-pressure cooling air, reducing stress concentration on passage walls.

Unity aspect ratio passages in turbine airfoils prevent Coriolis-induced flow reversal, boosting cooling effectiveness from 0.5 to 0.8.

A turbine blade platform groove channels cooling air along the lower surface to enhance heat transfer at the trailing edge connection.

Varying core material density along the transition area increases strength in high-load zones without adding weight.

Remote platform positioning eliminates collision risks from displaced centers of gravity while maintaining structural integrity.

Radially extending intermediate wall joins concave and convex side walls to distribute stress and reduce creep distortion in internally cooled turbine blades.

Self-powered rotating drums capture particles via adhesion forces, preventing component erosion while maintaining gas turbine efficiency without pressure loss.

Spherical recesses on the casting core align airflow for homogeneous distribution while simplifying mold geometry and reducing injection defects.

Porous honeycomb seals prevent hot gas escape through thermal gaps, maintaining efficiency despite thermal expansion friction.

Assembly box extends six o'clock rails to fan casing, reducing nacelle length and mass while maintaining continuous force passage.

Oil diffuser device decelerates fluid flow through an expanding passage to restrict leakage along a rotating shaft.

Housings transmit loads to the tower, eliminating support plates and reducing nacelle weight.

Asymmetric modular chambers absorb acoustic energy at fan flutter frequencies, suppressing aeromechanical instability within limited propulsion space.

A locking spacer assembly secures adjacent turbine blades using a mid piece and pins.

Nested corrugated structures extend sound wave trajectories through resonance chambers to attenuate low-frequency noise within space constraints.

Non-axisymmetric endwall contouring mitigates vortex formation from boundary layer separation, reducing energy losses in gas turbine engines.

A rear-mounted wash manifold delivers atomized fluid to gas turbine engine components using a curved delivery segment and retention system.

An axial turbine engine vane combines an icephobic leading edge with downstream hydrophobic surfaces to reduce frost accumulation caused by turbulence.

Segmented blade portions connect via a nested spar bridge joint, reducing transportation costs while maintaining structural integrity.

Converging nozzles accelerate cooling air to form fluidized curtains that block hot combustion gases from entering the rotor wheelspace.

An omega stiffener interposed during winding boosts casing stiffness, resolving weight reduction trade-offs.

Cylinder locking devices restrict hydraulic cylinder movement to prevent blade tip clearance control failures and extend component life.

A segmented support structure moves one blade shell half to join the stationary second half, enabling direct assembly without intermediate transfer steps.

An adjustable aircraft engine bleed air inlet uses movable elements to vary the cross-section area and a wedge-shaped flow guide to separate boundary layer streams.

Segmented diffuser sections manage high-velocity steam to suppress shock waves and peeling, enabling efficient static pressure recovery.

Cooled turbine exhaust case assembly introduces cooling gas into a forward outer diameter ring plenum to provide film cooling.

Segmented nacelle floors with dual openings enable direct transformer lift, while the base seals leaks without extra mechanisms.

Non-axisymmetric surface contours on gas turbine vane platforms counteract static-pressure distortions to reduce purge air requirements.

Stationary flanks on the fixed structure cover door cavities to optimize aerodynamic continuity and reverse thrust efficiency.

A lobed gas discharge fairing protrudes into a turbofan bypass duct to define distinct thermal air regions.

Segmented accessory gearbox design allows tower shaft extraction while keeping the main unit mounted, reducing disassembly complexity.

A hollow connecting piece joins juxtaposed acoustic panels, eliminating non-acoustic zones at the junction to maintain continuous sound absorption.

Segmented impingement baffles direct cooling air at turbine nozzle outer bands, reducing inter-segment leakage and extending service life.