Engine Manufacture TRIZ Cases

A turbine bucket airfoil uses specific Cartesian coordinate values to define its nominal profile geometry.

Extending core fibres to the trailing edge positions cooling passages closer, resolving uneven temperature distribution in ceramic matrix composite aerofoils.

Dog leg turns in the trunk section reduce diffusion angles to prevent flow separation and recirculation zones.

Laser welding joins thermoplastic layers on a wind turbine blade leading edge erosion shield, reducing maintenance costs and extending service intervals.

Radial girders distribute loads from a metal base can to a reinforced concrete slab, reducing construction time and material transport costs.

An elliptical blade cross-section eliminates abrupt curvature jumps to prevent flow detachment and minimize thermal stress concentrations.

A film cooling structure uses a convex portion to form a throat and a diffuser part that expands rearward along the wall.

Segmenting contra-rotating turbine cavities eliminates the piston effect, reducing compressor penalties while maintaining effective purging.

Pivotable nacelle flaps straighten reverse airflow to reduce recirculation, addressing mass and drag trade-offs in high bypass turbojet engines.

Separating the diffuser from the turbine housing allows longer diffuser lengths and larger bend radii, reducing installation space constraints.

Offset rotor blades maintain full-face exposure to fluid flow, reducing structural complexity while operating in turbulent conditions.

Fixed geometric ramps at the nozzle throat and exit replace heavy mechanical actuators, achieving 30-degree vectoring angles without increasing engine weight.

A micro-turbine system converts pressurized waste gas into direct current power using a rotor and stator assembly.

Segmented shell halves joined at the trailing edge incorporate a flatback section while minimizing processing defects and maintaining structural integrity.

Variable pitch ratios in aircraft turbine blades resolve the trade-off between high efficiency and increased blade weight.

An asymmetric J-type airfoil increases natural frequency to prevent flutter while maintaining fluid flow efficiency in gas turbines.

Segmented internal lands and radial pins meter cooling airflow through slots to create a consistent thermal film that protects the trailing edge from oxidation.

Asymmetric hinge positioning prevents door interference with fixed structures while maintaining compact engine dimensions.

Segmented spline seals in a turbine shroud direct cooling air to reduce component temperatures while minimizing leakage losses.

An angled laminate skin on a composite airfoil dovetail mitigates bending stresses in turbine engines, ensuring durability without adding weight.

Pre-positioned collectors and insulating coatings prevent short circuits during wave bending of the outer mesh.

Asymmetric root turns in turbine buckets reduce stress concentrations by up to twenty percent while maintaining efficient cooling flows.

Varying cooling hole densities along the blade height directs medium flow to match thermal gradients, preventing overheating.

Detects eigenfrequencies by exciting rotor blade vibrations, identifying manufacturing imperfections that visual inspection misses.

A symmetric clip with five arcs redirects airflow to increase lift at lower velocities.

A turbine nozzle airfoil shape defined by Cartesian coordinates to enhance aerodynamic efficiency.

Alternating thick and thin portions on an aircraft nacelle air inlet lip separate upstream airflow into inner and outer streams.

Trip strips embedded in the minicore cooling passage network turbulate boundary layers to resolve heat transfer limits without excessive pressure loss.

Curved elliptical cross-sections reduce boundary layer effects from fuselage proximity, ensuring uniform airflow and improved fuel efficiency.

Contoured trench back wall guides coolant flow along the airfoil surface using the Coanda effect to enhance film cooling attachment.

Preloaded tie rods merge load paths and fastening functions, eliminating separate inner frames to reduce weight and assembly complexity.

An oil scoop captures centrifugally expelled fluid from a rotating shaft to deliver pressurized lubricant directly to bearing dampers.

Segmented radial circuits resolve inadequate cooling distribution by directing airflow through pin banks, establishing a near-surface thermal zone.

Control line guide restrains positioning line to align heavy wind turbine blades with rotor hubs without structural loading.

A rotor blade root insert integrates a metallic flange to distribute structural loads and provide reliable lightning protection.

A fan blade with a thickened root and smooth transition zone reduces structural stress from boundary layer distortion in gas turbines.

Angled injector ring collides liquid propellant streams to atomize fuel, resolving slow solid regression rates without adding system weight.

Profiled fork surfaces accommodate angular misalignment to reduce wear at the link-actuator interface.

A flexible mould restores aerodynamic shape on eroded wind turbine blades by containing injected resin during curing, avoiding costly platform deployment.

A corrugated disk web introduces deliberate detuning to stabilize turbomachine blades against flutter.

A wind turbine blade ice melting device uses a connecting conductor to align power leads on one side of the heating portion.

Segmenting the blade into a spar root, shell mainboard, and integral tip reduces bonding complexity while maintaining structural strength.

Pins and brackets align engine cases before bolt tightening, reducing thermal stress and eliminating tight tolerance requirements.

Semi-sectored annular flange with relief ports accommodates varying axial lengths of ceramic matrix composite ring sectors.

A turbine nozzle airfoil defined by scaled Cartesian coordinates for smooth aerodynamic interaction.

Defining the turbine arm profile via specific coordinates reduces manufacturing complexity while maintaining aerodynamic efficiency.

A tubular elastic intermediate element connects the inflow opening to the flow channel in an aircraft gas turbine.

Interlocked fused joints eliminate flash formation and mislocation issues in multi-wall ceramic cores.

Mould indentations embed fin inserts during resin transfer to create an integral leading-edge structure.

Tensile load carrying members attach to upper and lower flanges to suspend platforms, avoiding jacket wall welding that increases material thickness.