Engine Manufacture TRIZ Cases

Repositioning a movable insert in a primary mold forms blades of different lengths, eliminating separate molds and lowering production costs.

Radially translating seal elements accommodate thermal expansion without bulky hardware that interferes with fluid flow.

A wind turbine rotor blade joint uses pin joints and load bearing blocks with matched thermal expansion coefficients to maintain structural contact.

Parallel fan rotors spaced from the core axis reduce the operational envelope while delivering additional propulsion through bypass airflow.

Air-air heat exchanger cools bleed air to manage component temperatures while recovering thrust from spent exhaust flow.

A variable geometry inlet duct adjusts its axial length to expand acoustic treatment area and reduce engine noise propagation.

A bonded window cover joint assembly transitions inner skin layers to secure the access window.

Discontinuous curvature lines in a turbocharger guide vane resolve the trade-off between manufacturing simplicity and adaptability to different flow profiles.

Specific coordinate values define an optimized airfoil profile that reduces pressure and temperature losses during gas expansion.

A counter-rotating low pressure turbine architecture reduces engine length while maintaining high pressure core ratios.

A nozzle vane fin positioned near the trailing edge creates controlled axial force to prevent contact friction with shroud or hub surfaces.

Mold-aligned tooling pins enable precise pin hole alignment during resin infusion for wind turbine blade structural components.

An elastic couple rotor turning gear uses flexible supports to drive vertical hydroelectric rotors with stable concentricity.

Adaptor pieces match connection areas of separate blade sections, resolving manufacturing tolerance issues for reliable load distribution.

Segmented internal cooling circuit with tapered supply cavity increases overall cooling effectiveness to 0.8 while reducing parasitic flow losses.

Titanium front reinforcing frame intercepts heat from the air intake lip, protecting composite acoustic and outer panels from high by-pass ratio temperatures.

A constricted duct stabilizes coolant mass flow rate against unsteady pressure fluctuations, preventing ingestion into film cooling holes.

A convex radially outward facing contact surface on a snap arm distributes radial loads across a gas turbine cover plate.

Production method embeds hollow cylinder inserts with cone caps into composite structures before polymerization to form precise acoustic pathways.

Integrated compressor-to-turbine cooling channels manage thermomechanical fatigue by directing bleed air through segmented rotor structures.

A ceramic matrix composite turbine shroud segment defines a radially extending channel to deposit abradable material along its inner surface.

Symmetric diamond turbulators enhance heat transfer in gas turbine cooling passages.

Hooded cooling holes with internal vanes widen coolant distribution to reduce compressed air mass flow and improve engine efficiency.

A turbine rotor blade suction side fillet portion utilizes varying heights and widths to manage structural loads.

A thermally responsive flow meter adjusts cooling airflow via coil expansion and plate translation.

Annular base plate with a lower surface creates a central hollow for equipment accommodation without increasing foundation height.

A switching arrangement receives air traffic detection signals to independently control wind turbine marking lights.

Segmented wind turbine blade skin panels with integral bulkheads eliminate separate ribs to reduce component count and simplify assembly.

A spacer between the mast and translating cascades absorbs parasitic bending moments, preventing misalignment from relative displacements.

A conical screw connection uses a softer metallic sealing element to mold onto counterpart surfaces for reliable sealing.

Non-parallel tracks adapt to the mould width, reducing factory floor space while maintaining full gantry span at the blade root.

A protruding part on the heat shield reduces velocity distortion in the spiral channel, improving turbine efficiency while blocking thermal stress.

A rotor blade sealing arrangement forms a radially inward cavity to contain the tip and prevent turbulence.

Defined tip rail surface profiles using Cartesian coordinates reduce aerodynamic losses and improve system efficiency in turbomachines.

A forward facing step nozzle fluidly couples two cooling cavities in a turbine assembly to direct high velocity cooling air.

A turbine outlet diffuser channels post-combustion gases aft of the turbine wheel to the housing outlet.

Segmented transition layers wrap composite layer ends at the scarf joint, resolving stiffness mismatch between glass and carbon fiber spar caps.

Segmented ceramic cores create serpentine cooling passages in turbine vane platforms, resolving design complexity while maintaining stress resistance.

Segmented stator platform groove accommodates relative vane movement to reduce compressed air leakage between compressor components.

Apertured radial struts manage thermal gradients in CMC airfoils by directing coolant through varying wall thicknesses.

Nested reinforcement collars with pressure grouting increase overturning moment capacity while reducing construction complexity.

Nested serpentine passages redirect cooling air through offset circuits, maximizing heat extraction while maintaining compact structural complexity.

Directional film holes discharge cooling air through double compound angled configurations to protect turbine blade surfaces.

Segmented part-span shrouds with elliptical trailing edges reduce mechanical stress and vibratory loads on longer gas turbine rotor blades.

Droplets at the scoop inlet mouth trigger vortices to break up fluid flow, suppressing Helmholtz resonance caused by closed fan air valves.

A folding cover closes a nacelle ventilation opening while allowing airflow through the structure.

Multi-lobed cooling holes segment flow into distinct channels, preventing separation and reducing thermo-mechanical fatigue in gas turbines.

Elastic retention allows radial movement accommodation while preventing vibration transmission in heat exchanger mounts.

Segmented mounting with a thrust balance seal allows thermal expansion of the exit guide vane, preventing stress buildup and airflow disruption.

Segmenting the nacelle from the rotor allows a specialized elevator carriage to mount the unit on tower rails, reducing reliance on costly jack-up vessels.