Power Plant Construction TRIZ Cases

Clamped bearing washers rotate freely to prevent deformation, eliminating heavy arms and reducing weight while maintaining structural integrity.

A non-axisymmetric gas turbine intake features an angularly offset medial plane relative to the engine central axis.

Unitarily forming engine mount beams with pylon structures eliminates separate bolted joints, reducing assembly labor and component weight.

A mounting beam assembly uses radial shear fasteners to distribute loads across a webbed structure.

A suspension arch links to a beam via a pivot link parallel to the engine axis.

Segmented connecting rods reduce radial footprint to expand secondary flow vein cross-section and enhance dilution ratio.

A gas turbine engine mounting system uses a mid-turbine frame to connect the rear mount and support bearing loads.

Rear-mounted shear pins and tension bolts secure the aircraft engine mount, eliminating front face access requirements for fitting fasteners.

Angular mounting components create focal points that minimize backbone deflection, improving fuel efficiency.

Segmented lateral flank joists in a jet engine mounting pylon distribute loads along specific paths, reducing weight while maintaining structural rigidity.

Segmented front plates reduce machining complexity and weight while maintaining structural strength for aircraft engine attachments.

Segmented propulsion units allow fixed-wing aircraft to operate in constrained spaces without sacrificing cruise range.

Sliding guide devices on a mast-mounted cradle allow thrust reverser components to move relative to the nacelle, reducing stress from engine displacement.

Segmented cover sectors pivot along parallel axes while guided by thrust inverter structures, reducing deformation risks from external air pressure.

An adjustable fulcrum position in the thrust link-lever counteracts bending moments, reducing engine deflection and blade tip rub.

A gas turbine mounting structure uses a slotted hole and pin arrangement to redirect vertical and lateral loads through a backup connection.

Segmenting the front engine attachment beam into three plates reduces machining complexity while maintaining structural strength.

Lateral links and a shear pin reduce the distance between the primary structure and the wing while reacting transverse loads.

Tiltable connection fittings resolve limited space constraints during engine mounting while maintaining reliable thrust transmission.

A build frame supports engine assembly before transfer to the aircraft wing, resolving alignment errors during heavy component installation.

Airfoil-designed drone fuselages tilt forward between 5 and 15 degrees to minimize energy expenditure, extending flight time beyond standard hovering limits.

An engine installation system uses pivotable links and variable-length members to position aircraft engines.

Longitudinal shearing pins and barrel nuts enable front engine attachment assembly within restricted axial space near large-diameter hubs.

Repositioning the attachment body's horizontal fixing surface upward between spars reduces aerodynamic drag and increases ground clearance.

Aircraft engine mounting apparatus redirects thrust loads through integrated channels and pins to maintain structural integrity.

Circular member with tubular members attaches aircraft engines to fuselages, resolving complex retrofitting contradictions.

Curved vertical section line of airplane suspension fairing provides inner space for engine mounting near wing leading edge.

Inboard-cambered pylon fairing reduces thrust loss and weight by managing shock waves near the wing attachment.

A structural strut assembly transmits axial and lateral forces between the engine casings and aircraft mast.

External fitting placement increases lateral separation for torque absorption without widening the caisson width.

Handle-operated transmission moves the access panel to resolve screw loss risks while maintaining aerodynamic continuity between the pod and attachment device.

Fuselage-mounted vanes support the engine casing of a rotational propulsion system, eliminating heavy pylon structures and reducing aerodynamic drag.

A metal fire seal system replaces elastomeric seals with a metal shoe and flexible tongue to withstand high temperatures and absorb nacelle movements.

Front attachment bracket transmits thrust loads along the engine axis using primary and secondary fixing points.

Rear engine attachment strut functions as a spreader beam via an articulated shaft system.

Asymmetric arms generate deforming torque to reduce banana deformation and manage blade loss loads.

Dual linking systems connect the frame to the fan and core cases, reducing support structure height and fairing size to lower aerodynamic drag.

Staggered access openings on aircraft engine pylon side panels consolidate maintenance entry points across multiple inter-rib spaces.

Secondary articulation halts rotation to reduce lever arm forces, simplifying the design and eliminating redundant safety paths.

Monolithic rear sub-structure replaces redundant backup lugs, saving 200 kg per pylon while maintaining structural integrity.

Flexible thermal barrier protects turbine engine auxiliary yoke from fire exposure while accommodating structural movements.

Offset orifice boomerang link filters transverse vibrations, reducing structural wear and passenger discomfort in aircraft engine mounts.

An adjustable offset mount uses graduated components to align model airplane engine thrust angles without shimming.

Segmented rear support with pre-formed energy absorbing zones prevents bulkhead fracture while maintaining nacelle weight.

An anti-rotation plate with a pin engages an axle notch to eliminate wear from friction and vibration in turboshaft engine suspension systems.

Planar parts with projections prevent insert rotation, eliminating heavy anti-loosening devices while maintaining structural reliability.

A blind installation pin assembly uses a pivoting paddle and spring-biased T-bolt to secure gas turbine engine mounts.

A rear mount assembly uses locking members to secure link rods through a bypass duct wall for precise core positioning.

An inclined motor mounting structure creates asymmetric force components that improve yaw control response speed and lateral wind resistance.