Engine Manufacture TRIZ Cases

Optimized acoustic liner depth-to-gap ratio attenuates fan blade passage frequency noise in gas turbine engines.

Bus strips extend into segment gaps to maintain continuous heating at structural joints, preserving acoustic noise suppression performance.

A tower lifting system uses nested frusto-conical sections and internal hoists to erect wind towers without external cranes.

Integral damper springs in attachment liners stabilize unsupported stator airfoils, eliminating inner shrouds to reduce vibration and device complexity.

Intersecting ribs transition from flexible airfoil to stiff attachment geometries, managing thermal expansion and preventing structural crushing.

A gas turbine airfoil features a pressure side recess to adjust throat distance between vanes.

Asymmetrical filleted corners in cooling passages reduce thermal stress concentrations, extending gas turbine component life.

Variable width second connectors reinforce the joint between stacked tower elements, reducing buckling risk and simplifying on-site assembly.

Curved arm contact surfaces minimize wear on turbocharger unison rings, maintaining nozzle vane positional precision.

Guide rails and mounting carts shift the wind turbine gearbox axially, resolving complex maintenance access issues during roller bearing replacement.

Microgrooves on rotor and stator blades channel condensed water away to prevent erosion and reduce frictional resistance.

Segmented fan exit guide vanes provide structural support between the fan case and core engine, reducing noise without increasing device complexity.

Imidazole curing agents eliminate die sloughing and reduce pull loads in epoxy pultrusion, avoiding anhydride hydrolysis risks.

Cooling passages connect inlet ports to collection plenums, reducing thermal expansion and leakage in thick-walled turbine shrouds.

A two-dimensional variable-area plug nozzle uses convergent flaps to adjust exhaust area for high-speed flight vehicles.

Deployable external stoppers on a fastener shaft connect shear webs without internal access, eliminating safety risks from tight spaces.

A resonance chamber coupled to a secondary duct oscillates air at predefined frequencies to dampen flow disturbances in gas turbine inlet systems.

Segmented ceramic heat shield and metallic spar use rigid load supports to transfer loads while cooling passages manage high temperatures.

Segmented static sealing device limits hot air leakage and thermal conduction between distributor and external casing without weakening structural integrity.

Radial throat distribution along the blade span optimizes aerodynamic efficiency and cooling while managing geometric complexity.

Axial blade translation combined with pivoting prevents secondary flows and partial admission, maintaining stage efficiency across wide flow ranges.

Narrowing and expanding cavity width at 180-degree turns reduces pressure loss and fluid separation in serpentine cooling circuits.

Internal web divides turbine airfoil into cavities with radially distributed supply holes forming crossing impingement jets for enhanced heat transfer.

Tongue structure divides base body into partial spaces to tune absorption frequencies, resolving broad-spectrum noise gaps without complex manufacturing.

An arcuate air-oil cooler wraps around a gas turbine engine core to transfer heat from lubricant to airflow.

Notched leading edge and standoff-defined grooves direct cooling air to the stagnation point, reducing debris blockage risk at outlet ports.

Serpentine cavities and cover plate bulges direct cooling air through defined passageways to dissipate heat from gas turbine engine components.

Spiral centering spring beams utilize circumferential loops to reduce mechanical stress while maintaining compact axial dimensions.

Radially spaced inlets feed microcircuit cooling channels along the airfoil radius to deliver convective heat removal.

Radial ribs on a turbocharger heat shield disrupt centrifugal gas flow to create positive pressure, preventing lubricant oil leakage into the turbine housing.

Radial bolted joints on inclined flanges reduce gas flow disruption while simplifying turbine engine mounting operations.

Segmented trailing edge segment uses eccentric coupling to centralize force introduction, eliminating moment-induced stress during transport and assembly.

Removable annular rotor captures fan blade ends axially and transversely, distributing mass peripherally to reduce centrifugal forces and radial elongation.

Variable thickness and lean angles in the airfoil profile reduce secondary flow effects and thermal stresses.

A hybrid stator combines elastomeric sealing with rigid metal support to maintain rotor contact under load.

An optimized compressor turbine vane airfoil profile uses specific Cartesian coordinates to reduce flow separation, enhancing thrust capability.

Segmented blade cavities maximize heat exchange while limiting airflow consumption to maintain turbomachine performance.

Asymmetric louver airfoils stabilize high-angle airflow, preventing separation and reducing pressure loss in gas turbine offtakes.

Inverting cooling channel flow eliminates pumping energy consumption and reduces thermal stress in gas turbine blades.

Cartesian coordinate-defined airfoil profiles reduce flow separation on low-pressure turbine blades, increasing engine power capability.

Stepped peripheral sections on the rotor body eliminate intermediate sealing elements to prevent fluid leakage and ensure accurate blade placement.

A temporary support device holds a power control module while a tower section is assembled around it for integrated transport.

Pre-integrated inserts and connecting elements join rotor blade sections, eliminating costly post-manufacturing retrofitting and reducing local bending moments.

Merging crosshead components into a single wear-coated unit reduces maintenance frequency while integrated stay rods eliminate misalignment deflection.

Lateral slots in a turbine damper pin modify structural stiffness to tune blade natural frequencies, avoiding costly tooling rework.

Axial bearing removal device using push-pull rods and rail supports reduces stationary gas turbine repair downtime.

Blade outer air seals with cooling holes defined by Cartesian coordinates regulate temperature under extreme heat while maintaining structural integrity.

A turbine blade film cooling hole uses a meter section extending from tip to root and an enlarged diffused section toward the tip.

A turbine pipe core uses a sharply curved convex region to minimize mass while maintaining aerodynamic performance.