Power Plant Construction TRIZ Cases

Segmented link members eliminate preload requirements by absorbing assembly tolerances while maintaining structural redundancy.

Engine attachment uses a single end fitting with a stop ring to secure the mounting pin.

Positioning hydrogen fuel pipes inside structural tubes minimizes pylon cross sections and improves aerodynamic performance.

Radial centering features on bushings align the through-axle to prevent damage during installation of turbine engine suspension systems.

Continuous warp yarns form arcuate portions in multilayer woven composites, distributing mechanical forces to enhance strength without adding weight.

Intermediary wearing parts absorb contact forces between connecting rods and yoke walls to control tilting and prevent structural wear.

Distributed bolt row reduces secondary moments and bulk, enabling closer pylon positioning to wing box.

An integrated afterbody mount case with radial spokes connects the nacelle to the pylon.

A pivotable shackle assembly with linked components adjusts geometry to maintain equal load distribution across engine case lugs.

Segmenting the nacelle load support into articulated parts minimizes air flow disturbances caused by engine-induced deformation.

Angle brackets form L shapes on lateral panels to align with transverse frames, eliminating shim measurement and reducing manufacturing costs.

Segmented planar wings absorb thrust forces and filter engine vibrations, reducing bending moments on the aircraft structure.

A suspension beam joins plates via an elastomer layer to dampen transverse vibrations in aircraft turbine engines.

Hollow tubes in the accessory frame supply coolant directly to mounted components, preventing overheating from uneven air distribution.

A single plane mounting system secures a gas turbine engine using discrete linkages to transfer thrust and torque loads.

Diagonal link rods in aircraft pylon transverse reinforcers lower mass and simplify forging by replacing bulky titanium geometry with segmented braces.

Horizontal connecting pin arrangement increases side access to engine mounts, resolving maintenance bottlenecks in compact thrust take-up devices.

A gas turbine mounting system uses a thrust ring and linkage assembly to distribute static and dynamic loads across the engine structure.

Curved fairing vents air parallel to engine exhaust flow, reducing drag from airflow separation.

Segmented pylon blade transfers engine loads to wing panels through direct shackle connections.

A turbomachine suspension assembly uses a nested ball joint housing to pivot a cylindrical part within limited radial space.

Articulated connecting rods replace solid beams to reduce weight and manufacturing complexity while maintaining structural integrity.

Height adjustable table and tilt adjuster support equipment brackets to position heavy components at inaccessible fixture points.

Dual thrust load recovery rods with a second mechanical connection featuring play transfer loads only during failure events.

A turbine exhaust case mount uses a yoke with neck and support links to secure the engine structure.

Three-link front engine mount reduces thermal stresses on the primary structure while accommodating supplementary equipment.

Direct aft mount transmission eliminates thrust links that cause engine case distortion, maintaining optimal blade tip clearances for improved fuel efficiency.

Slit top spar and bolted link attach the primary mounting pylon to the wing airfoil box, resolving space restrictions from larger engine diameters.

Extraction of battery packs into dedicated pods with insulation and venting reduces fire suppression weight while protecting critical airframe components.

Segmented composite pylon design with double-shear connections manages high temperatures and reduces manufacturing complexity.

Inclined fixing elements link an aircraft engine to a pylon, enabling assembly when the internal link system is already in place.

Segmented suspension lugs connect turbine engines to structural pylons via integral C-clamps and locking mechanisms for secure mounting.

A gas turbine liner hanger cable assembly supports the liner relative to the duct using a ball-and-mount configuration.

Vertical drive unit arrangement improves directional stability and enables modular servicing.

A hinged cradle supports fan cowls while decoupling from the engine mounting structure to maintain nacelle geometry.

Integrates a pylon box between wing boxes to reduce vertical space constraints while maintaining load transmission strength.

Segmented pylon connectors with frangible joints resolve stiffness requirements without increasing wing box weight.

Tangential connecting rods align with radial fictitious planes to reduce annular casing deformation and improve mechanical stability.

Segmented pylons separate flammable fluids from ignition sources while reducing engine bending and specific fuel consumption.

Rear-access fork system immobilizes aircraft engine shear pins, eliminating the need for difficult front attachment body access during maintenance.

A blind fastener assembly uses a pivoting paddle to secure components in confined spaces without specialized tools.

Segmented housing isolates elastomeric elements from engine heat, reducing thermal degradation and extending operational life.

Segmenting fixed engines from the rotating pylon eliminates complex mounts and improves maintenance access.

Integrated double stop limits spreader travel in aircraft engine linking devices, eliminating time-consuming manual adjustments during assembly.

Segmented beam and rod elements reduce manufacturing complexity while backup safety fixing points ensure reliable load path redundancy.

An interleaved stiffener connects aircraft engine links to resist transverse bending forces.

Segmented pylon structure uses transverse shackles to secure wing panels, reducing bulk while absorbing thrust loads.

Stiffeners extend between yokes to redistribute mechanical loads in turbomachine casings.

Upper radial lifting points on aircraft drive units enable direct clevis engagement without disassembling front cowls.