Engine Manufacture TRIZ Cases

A combined circulating system recycles micro gas turbine exhaust heat using a piston engine to drive power generation.

A fan variable area nozzle uses a drive ring actuator to adjust the exit area for optimized thrust.

Segmented serpentine circuits deliver targeted cooling to hottest trailing edge zones, resolving uneven heat distribution in gas turbine blades.

An annular recess on the turbine rotor hub uses a major arc oval shape to minimize stress concentration while reducing rotational inertia.

An optimized turbine blade profile uses precise coordinate definitions to reduce turbulence and mechanical stress, improving durability under dynamic loading.

Canted knife edge seals generate vortices to restrict fluid flow, reducing combustion product leakage past rotating components.

A single-piece tubular frame minimizes air gaps in large wind turbine generators by eliminating assembly errors and reducing weight.

Service platform enables in-situ blade bearing replacement on floating wind turbines without large cranes or shallow water relocation.

Segmented trailing edge cooling channels with projection structures meter coolant flow through turbine airfoils.

Oval C-shaped composite guide rails reduce weight and free space in aircraft thrust reversers, enabling damping structures.

A windmill blade leading edge protector uses a conductive mesh with holes for adhesive penetration, securing the protector against moisture-induced detachment.

Segmented structural inserts with varying cell sizes enhance rotor blade stiffness and load-bearing capacity while minimizing weight penalties.

Embedded coil springs provide structural support for shape-changing foams, resolving force limitations that restrict practical morphing capabilities.

Corrugations on the suction wall redirect coolant flow to enhance impingement cooling, reducing temperature gradients and extending component life.

Curved strut covers reduce backpressure by guiding exhaust gas smoothly around structural supports.

Adhesive spacer elements define gap distance between blade shell parts, reducing adhesive weight while maintaining structural integrity of glue joints.

A variable inlet compressor uses electric boost assist motor power consumption to infer actual speed and pressure ratios for component health monitoring.

Movable support structure accommodates thermal expansion of offset transition ducts, preventing stress buildup and failure.

Optimized turbine vane profile defined by Cartesian coordinates reduces airflow turbulence and improves aerodynamic efficiency.

Dynamic air guide surfaces adjust orientation with the closing element position to maintain laminar flow and reduce turbulence in the bypass channel.

A master-slave linkage coordinates primary and secondary sleeve deployment using four-bar mechanisms.

Elongated slot perforations and segmented core layers reduce manufacturing complexity while maintaining noise attenuation performance in engine nacelles.

Bonding high-strength Inconel corrugated sheets with a copper core layer reduces thermal gradients and prevents deformation in jet engine components.

Segmented frames and pulleys lift internal components without removing the nacelle cover, reducing service time.

A resin barrier creates a delimited cavity between joining surfaces to eliminate air pockets and kissing bonds during wind turbine blade manufacturing.

A counter-rotating low pressure compressor and turbine use a gear system to drive inner and outer stages at different speeds.

Integrated guide flanges on wind turbine blade shells enable precise handling during post-moulding operations.

A composite turbine blade platform incorporates a radial stiffener strip to balance centrifugal forces and maintain aerodynamic regularity.

Attachable trailing edge profile elements adapt rotor blade geometry to site-specific load conditions.

Radially extending protrusions on a gas turbine disk rim turbulate cooling fluid flow to enhance convective heat transfer.

A method expands heated channel walls against honeycomb cell ends using pressurized gas to create a continuous diffusion weld.

Internal lifting via guiding holes reduces equipment complexity and operational costs during wind turbine maintenance.

Guided carts transport heavy transformers along internal and external rails, eliminating hoisting oscillations that damage nacelle components.

Porous attenuation structures absorb shockwave energy on turbine airfoils, reducing pressure losses and improving engine efficiency.

Preliminary laser penetration followed by hybrid arc remelting removes gas bubbles from deep welds, enhancing fatigue life and productivity.

Segmented lifting system reduces stress and rental costs by using a secondary structure to raise the main load above its center of gravity.

A lifting device adjusts its point of gravity using movable weight elements and connection points on the chassis.

A hollow ring collects and accelerates leakage air currents to cool the upstream distributor platform, preventing degradation of the low-pressure turbine area.

A U-shaped divider rib splits cooling fluid in a gas turbine vane passageway to create a double vortex flow structure.

A method for manufacturing acoustic attenuation panels from ceramic oxide composites using integrated molding of skins and cellular cores.

Interconnected ribs form a three-dimensional lattice on the shroud segment, increasing rigidity against centrifugal forces while minimizing added mass.

Leg members form an intake space between the rotary electric machine and engine housing to reduce system volume.

Radial cooling channels use metering orifices to control airflow, preventing hot gas backflow into film holes while maintaining engine efficiency.

An aero-brake feature on a turbine blade selectively disrupts axial gas flow to counteract Alford forces caused by radial misalignment.

Directly interfacing serial coaxial turbine stages reduce packaging volume and assembly costs while maintaining hermetic seals and reliable gas flow alignment.

Variable slot patterns in composite acoustic panel skins optimize noise attenuation through abrasive blasting fabrication.

A segmented bullnose ramp uses varying curvature profiles to induce controlled flow separation and reattachment in aircraft propulsion systems.

A pivotable airfoil root mount allows the blade to rotate within a slot, accommodating impact forces without rigid constraints.

Radial gap between shroud and heat shield creates thermal air barrier, reducing thermal stresses on strut interface without increasing metal thickness.