Engine Manufacture TRIZ Cases

Inclined translating cowl portions redirect bypass airflow to minimize pressure losses and fuel burn during forward flight.

A tethered underwater turbine array uses variable buoyancy to transition between submerged operation and surface maintenance.

Shock tube with dispersion holes forms auxiliary cooling passage to reduce compressed air usage and improve turbine blade thermal efficiency.

A counterweight system balances a wind turbine hub to enable blade mounting without external cranes.

Segmented cooling channels direct air through the turbine blade platform to reduce metal temperature, preventing thermo mechanical fatigue cracking.

Preassembled guide supports engage external rails to prevent outer tower contact with electronics, eliminating technician supervision needs.

A plug assembly uses a wedge to expand a cup into a press fit within a core run-out opening.

Defined aerodynamic profile reduces turbulence and stress distribution in gas turbine blades.

A gas turbine rotor nut and bolt arrangement uses a counterbore to permit limited eccentricity between the nut and protruding bolt end.

An exhaust diffuser uses an inner guide with inclined walls and multiple inflection points to shape steam flow.

Axial overlap of a thin deflecting blade against a thicker surrounding-flow structure reduces secondary flows and noise in turbomachine hot gas ducts.

Tapered tooth joints friction lock under compressive force to eliminate bolts and enable material optimization across gas turbine engine sections.

Copper wires in the mold flanges replace fluid conduits, eliminating corrosion and non-uniform heating.

Flanged bushings prevent walkout and provide definite load paths, resolving joint loosening issues in segmented wind turbine blades.

Fastback turbulators inside airfoil tip turns reduce dust accumulation while maintaining high cooling efficiency.

An inclined tower design counters rotor torque-induced heeling, maintaining wind alignment and reducing energy losses.

Chamfered suction side rail positions cooling hole outlets on inclined surfaces, preventing blockage during rub events and maintaining efficient heat removal.

Controllable wires stabilize horizontal blade orientation, reducing ground personnel exposure and improving safety during rotor hub assembly.

Segmented wear strips restore the turbine seal housing surface without welding, eliminating maintenance time and distortion.

Protrusion configurations on conduit surfaces reduce thermal gradients and alleviate structural stress from temperature differences.

A deflector within the cooling passage redirects airflow to minimize dust accumulation at film holes.

Elongated facesheet slots minimize airflow interference, reducing surface drag while maintaining noise attenuation in turbofan engines.

Closed-circuit cooling passages in a CMC airfoil platform transfer heat between internal cavities, resolving thermal management complexity.

An elastic seal strip assemblage maintains seal integrity under thermal stress by accommodating arbitrary gap changes between assembly components.

A motorized winch deflects loads via a guide rope to prevent tower collisions below the free lift height.

Specific Cartesian coordinate airfoil geometry increases power output while maintaining aerodynamic stability against flutter-induced vibration.

A cantilevered stator vane shroud uses a circumferential step area to constrain axial movement between adjacent vanes.

A segmented turbine housing assembly uses sheet metal scroll and exhaust parts connected by a gap to reduce weight and heat capacity.

Offset thrust bearing segments reduce material displacement to lower embossing force and tool wear.

Radially spaced guide profiles on turbomachine blades redirect leakage and boundary layer flows, reducing viscous energy losses at blade ends.

Prestressed curved metal sheets accommodate thermal expansion differences between ceramic matrix composite vanes and metal nozzles.

Dividing the composite root end into smaller segments lowers exothermic heat generation during curing and allows accurate drilling with simpler jigs.

A directional flow nozzle imparts rotational motion to heated gas within an annular channel, accelerating fluid velocity around the engine circumference.

A reverse flow gas turbine engine design with independently rotatable low pressure and high pressure spools minimizes the engine envelope.

Motorized tracks move a U-shaped platform along the mast, eliminating reliance on complex self-elevating barges.

Raised skeleton curve adapts blade geometry to circumferential depression flow changes, limiting fluid acceleration and restoring initial flow gradients.

Radial translation of the fan nozzle increases throat area without axial movement, reducing exhaust noise while preserving acoustic treatment surface.

Segmented triple pipe and annular guide plate prevent compressed air trapping by high-temperature surfaces, restoring recuperator heat exchange efficiency.

Conically tapering rib sealing structure balances leakage reduction with vibration control to prevent vibrational instabilities in turbine rotor blades.

A Y-shaped joint connects a gas turbine fan rotor to a compressor via legs with varying rigidity to isolate mechanical deflections.

Integral bosses form shiplap joints between turbine shroud segments, eliminating spline seals that cause leakage and assembly delays.

An integrated screw pump circulates oil to lubricate fan bearings, eliminating frequent maintenance caused by grease deterioration at high temperatures.

Solid rocket propellant grain uses transverse slots to create segmented combustion zones.

Undulating trailing edge surfaces with discrete cooling outlets reduce metal temperatures and lower cooling air requirements by enhancing film coverage.

Segmented plug walls with a thermal gap maintain interference fit at high temperatures, preventing seal damage and oil coking in gas turbines.

An inter-fan fairing reduces aerodynamic drag from supersonic flows while shielding the gas generator from foreign object ingestion.

Segmented rotating towers use climbing cranes to self-erect, reducing material weight and installation costs for taller structures.

Segmented trailing edge protrusions promote shear layer deformation to resolve insufficient mixing efficiency in high velocity fluid flow configurations.

An integrated turbine exhaust case merges deswirling struts with a mixer to reduce pressure losses while maintaining mixing efficiency.

Smaller stator vane angles increase inlet swirl, restoring pressure ratio and flow rate when high ambient temperatures reduce corrected speed.