Power Plant Construction TRIZ Cases

Elastomeric isolation portions within a floating motor mount absorb vibrational energy, reducing noise and stress on unmanned aerial vehicle components.

An angularly offset pylon suspends a bypass turbojet engine from an aircraft wing using composite materials and link-and-hinge mechanisms.

Assemble aircraft mast primary structure with one side panel open to install internal systems before final closure.

Wedge clamping wedges eliminate bulky traction bolts and plate slippage by generating perpendicular friction forces between connecting plates.

A gear-driven gas turbine mount transmits thrust directly to the aircraft pylon through a rigid structural connection.

A compact mount system eliminates thrust links to reduce engine case distortion and improve thrust transmission efficiency.

An integral monolithic structure transmits nacelle maneuvering forces directly to the aircraft, reducing backbone bending and shop floor space requirements.

Separating the engine and proprotor vertically resolves conflicts between mechanical simplicity and maximizing wing surface area for lift.

Axial clevis mounts attach to the outer casing periphery, eliminating internal strain and preventing composite delamination.

Segmenting the front engine attachment beam into separate plates reduces structural complexity and production time while maintaining load-bearing capacity.

Eccentric rings compress tolerance gaps between mast and wing bores to secure fasteners without spigots.

Dynamic aft mount link shares loads to limit engine deflection during extreme maneuvers, reducing reinforcement weight.

Segmented angular sectors replace the entire annular groove, reducing maintenance duration and material wastage during aircraft engine repairs.

Thrust force take-up device uses a balance beam and additional fitting to transmit loads via pinned link rods.

Rigid connections in a statically indeterminate suspension maintain coaxiality during thermal expansion, resolving bending misalignment.

Attachment device merges fail-safe redundancy into the spreader structure, eliminating internal stop fittings and reducing pylon mass.

Bosses extending from rear flanges contact structural arms to handle thrust forces without increasing casing mass or complexity.

Integrated thrust pin linkage buffers opposing axial loads, reducing airframe stress during operational shifting.

Shear pin absorbs normal operation stress to protect the connection element and ensure fail-safe function reliability.

Modular supporting structure cradle maintains thrust reverser kinematics and mechanical strength while reducing propulsion unit installation time.

Offset link assembly with intermediate connector maintains engine alignment under thermal loads.

A rigid aircraft pylon uses a box rib extension to separate fasteners, transmitting lengthwise moments while minimizing aerodynamic disturbances.

Removing thrust links from the mount system minimizes engine case distortion and maintains optimal fan blade incidence.

A tangential pin support with three branches and ball joints simplifies the engine suspension structure.

Radial arms transmit turbojet forces to the aircraft structure, bypassing the cold-flow channel to reduce support mass and stress.

Inverted attachment topology reduces bulk by distributing engine load between internal nacelle support and external pylon.

Lattice-form lateral frames replace solid structures to cut manufacturing costs and weight without sacrificing strength.