Engine Manufacture TRIZ Cases

A co-bonded acoustic liner uses a thermoset plastic septa film to dampen sound while maintaining structural integrity.

Interchangeable winding core sections vary longitudinal extent and diameter, reducing production costs for variable rotor blades.

Angled core gas turbine engines mount propulsors at skew angles to prevent fragmentation interference between adjacent units.

A replacement motor mount displaces a wind turbine pitch motor to avoid damaged bearing regions, enabling in-situ repairs without removing the rotor.

Mechanical interference fits join turbine diaphragm components, eliminating welding defects and reducing manufacturing costs.

Scalloped turbine platforms with bulges and bowls redirect flow to reduce secondary vortex strength, lowering pressure losses at blade junctions.

Synchronized nozzle vane angular positioning aligns injector heads with dilution air holes to maintain uniform thermal exposure across the turbine outlet.

Inwardly bent stiffening elements reinforce hydraulic machine volute casing segments to distribute mechanical stress peaks at transition points.

A cable-stayed tower design reduces bending loads on existing foundations to support replacement wind turbines.

A manually operated linear actuator with a power screw mechanism lifts heavy wind turbine components inside the nacelle without electric supply dependency.

Double-tapered scarf joint aligns tapered recesses in blade modules, reducing assembly complexity while maintaining structural integrity.

Screen attenuates acoustic waves from ventilation openings, reducing noise without increasing engine mass.

Step parts and seal fins form minute clearances to generate counter vortices that reduce leakage flow rates in steam turbines.

Segmented standoffs meter airflow volume between the airfoil and baffle, resolving the trade-off between cooling effectiveness and structural space constraints.

Optimized parallel groove depths and spacing reduce sensitivity to manufacturing variations while maintaining structural stiffness in wind turbine blade cores.

Asymmetric flute angles prevent nesting in evaporative cooling packs, maintaining open air flow passages and heat transfer efficiency.

A mixing system with wraps and links directs momentum change to blend exhaust and air streams.

Internal four-bar linkages eliminate external drag links to reduce bypass airflow losses and improve engine efficiency.

Compressible elements mechanically engage turbine blade tip shrouds, eliminating pre-twisting stress on ceramic matrix composite rotor blades.

Precise Cartesian positioning of film cooling holes optimizes thermal protection while managing manufacturing precision requirements for gas turbine components.

An expanded portion and grooved outlet in a turbine blade cooling hole reduce injection rate and kidney vortices to improve film cooling effectiveness.

Transverse flow passages in unidirectional reinforcement eliminate stitching barriers, resolving the trade-off between stability and resin permeability.

An insulating layer with lower thermal conductivity than the composite layer delays temperature rise during fire events to maintain structural strength.

Deforming sealing tab creates planar contact to reduce radial leaks and wear while maintaining mounting ease in high-pressure turbine nozzles.

A trailing edge pattern with interstices containing a porous barrier obstructs fluid flow to reduce noise.

Segmented pivoting blades replace heavy reversal doors to reduce weight and eliminate bypass flow obstruction.

Optimized bearing stiffness and positioning shift the core shaft resonance frequency away from operating speeds, preventing whirl mode damage.

Reducing incremental EDM steps increases the diffuser included angle beyond ten degrees, preventing boundary layer separation and improving cooling efficiency.

A flow guide redirects cooling fluid from sidewall voids into a pedestal bank to improve heat transfer distribution in turbomachine components.

A turbocharger nozzle assembly uses a rotating ring-shaped body to block or open flow passages, directing air to turbine blades.

Optimized fillet radius and chute length in the core reduce stress concentrations, preventing breakage during turbine blade manufacturing.

Encapsulated phase change materials release latent heat to delay ice formation, preventing structural cracking from volume expansion.

Serpentine cooling path directs heated coolant into a radial cavity to warm the hollow body, reducing thermal stress from underutilized flow.

Hydraulic actuators axially move the inner turbine casing to dynamically adjust rotor-stator clearance.

I-beam ceramic blade track reduces thermal growth mismatch stress between composite and metallic materials.

A brazed thermal management article uses a substrate groove to attach a fluid duct, enabling precise temperature alteration of the component surface.

A turbine blade airfoil features a relief notch at the cooling outlet corner to support thermal expansion.

Elliptical film cooling elements eliminate stress concentration from circular inlets, preventing deformation while stabilizing vortex flow for uniform cooling.

Extending perforated honeycomb acoustic treatments into unducted areas attenuates noise radiation without increasing drag or fuel burn.

Segmented wishbone baffles maintain high heat transfer coefficients across complex airfoils without increasing flow restrictions.

Segmented through fasteners with circumferential ridges secure the hub while eliminating preload loss from soft material relaxation.

Segmented serpentine passages with dog-legged pedestals maintain film coverage and reduce thermal stress on turbine blades.

Frictional locking anchors acoustic septum caps in honeycomb cells, resolving bonding strength and noise attenuation trade-offs.

A turbine rotor blade airfoil features an asymmetric tip geometry that compensates for thermal expansion differences between upstream and downstream sides.

Segmented cooling modules enable pre-assembly testing and rapid removal, reducing nacelle disassembly time during repairs.

Segmenting the spar cap into pultruded sections reduces manufacturing complexity while improving resin impregnation quality.

Segmented support members secure a rotor hub and appendages at a predetermined height, eliminating crane instability and reducing maintenance duration.

Configurable brackets relocate tensioners to eliminate heavy pulley handling, reducing installation time and labor costs.

Varying nearest-neighbour spacing on a dome diffuser screen reduces peripheral stress concentration and prevents rupture in gas turbine bleed assemblies.

Separate radial and axial jigs constrain the turbine rotor to prevent misalignment without opening the gland part.