Jet Type Power Plants TRIZ Cases

A three-stream gas turbine uses an on-shaft electric machine to generate electrical power while improving thrust and fuel burn efficiency.

A continuous embedded rotor magnet with alternating polarity cuts rotor mass and magnet thickness while sustaining flux at higher speeds.

Crossed clevis connections between wing and pylon fittings cut vertical bulk while preserving force transfer and damage tolerance.

Redirected bypass airflow creates suction at the nacelle inlet leading edge, preventing separation, noise, and vibration in short turbofan nacelles.

Offset aircraft engines and a shared ballistic protection element contain radial drive-body debris, reducing engine-to-engine damage without heavy armor.

Braking the low-pressure shaft with an electric machine prevents compressor instability during thrust reversal while recovering energy.

A segmented removable and fail-safe beam connection cuts engine attachment height while preserving load transfer and aerodynamic efficiency.

A detachable crossbeam link and standby safety path cut engine mount height while preserving force transmission reliability in aircraft.

An elastically deformable rear engine attachment filters turbojet core vibrations while still transferring useful loads to the pylon.

A rear shock-absorbing engine mount uses elastically deformable elements to improve aircraft engine force transfer and damping.

A single-plane pin, shackle, and reaction-rod layout removes the rear mount to cut turbojet pylon weight while improving load transfer.

By nesting the front engine mount into the pylon, this case cuts vertical bulk, preserves force transfer, and adds backup load paths.

Articulated front and intermediate link rods cut engine attachment bulk in the bypass flow, easing aerodynamic cowling design.

By moving engine support from the wing to the fuselage or truss, this case cuts wing weight, preserves cabin space, and reduces drag.

A thrust link placed below the engine centerline counteracts gravity and torque loads, reducing core bending in aircraft engine mounts.

Multiple engine mounts converge at the center of thrust to distribute propeller loads, cut mount stress, and help prevent ground strikes.

A ring-mounted strut reacts thrust at or below the engine centerline to cut bending, weight, drag, and back pressure.

An asymmetric nacelle inlet lip uses local thickness variation to preserve downstream flow orientation and resist crosswind deformation.

A fan-driven plenum switches compressed air between ejectors and nozzle vanes, supporting VTOL hover and cruise with less propulsion complexity.

An inverted mid- and aft-truss strut reacts thrust at or below the engine centerline, alleviating bending in wing-mounted aircraft engines.

This case uses lateral pivots and paired connecting rods to transfer forces and moments while reducing aerodynamic protrusion.

A pylon and articulated rod layout distributes propulsion moments at the propeller center to limit engine casing overload.

Movable ducts ingest boundary layer air from wide fuselage surfaces into the engine, reducing drag while maintaining airflow control.

Replacing heavy rigid thrust reversal gates with pneumatic flexible sails reduces moving mass while maintaining effective counter-thrust capabilities.