Efficient Propulsion Technologies TRIZ Cases

Segmented protective and soundproofing panels reduce manufacturing complexity while extending service life through distributed impact energy absorption.

Axially forward positioned aft hooks intercept hot gas before cavity ingestion, reducing mechanical stress and improving turbine efficiency.

Thermal compaction of the silicate sol creates an alkali-resistant glass-ceramic layer that withstands dishwasher cycles without cracking or leaching.

Segmented CMC staves attach to metal rings to relieve thermal stresses from coefficient mismatch while enabling individual repair.

Segments metal frame skeleton from lightweight composite fairings to resolve the trade-off between structural integrity and maintenance accessibility.

Longitudinal segments assemble into a fan case wall with integrated strengthening ribs, resolving transportation constraints for remote engine maintenance.

Hollow struts channel hot combustion gas to drive tip turbine blades, eliminating reduction gears and shock wave noise.

A monolithic CMC hanger and retainer system constrains shroud segments to eliminate thermal stress from coefficient of thermal expansion mismatch.

Metallic wear liner protects ceramic seal segments in gas turbine assemblies.

Retractable screw inside a hollow body protects thrust reverser doors from damage while enabling flexible positioning during assembly.

A vapor phase deposition process deposits metallic aluminum and zirconium on metal parts using an activator.

Scheduling booster compressor variable stator vanes adjusts core flow and temperature.

A transport vessel uses an electromagnet to generate a homogeneous magnetic containment field for hyperpolarized media.

Composite annular covers integrate pressurization channels to maintain rigidity and prevent seal damage from vibration.

Radial crevice mounts link turbojet cold stream flow paths to exhaust casings, reducing connecting rod mass and mechanical strength issues.

HIBET calculates optimal battery and fuel requirements for hybrid-electric aircraft flights.

A pressure wall couples to a blade outer air seal using fluid sealing engagements and defines a metering orifice between plenums.

Segmented wing fans with variable pitch outermost units resolve the contradiction between vertical takeoff stability and forward flight efficiency.

A gas turbine control system coordinates fuel flow and exhaust nozzle positions to optimize thrust.

Cut-outs in the movable cowl avoid interference with wing slats, allowing increased cascade exposure to enhance braking thrust.

Segmented battery pods decouple charging from flight operations, resolving turnaround time constraints.

Segmented ceramic matrix composite wall elements suspend between outer casing and support structure, reducing mechanical load transfer.

A tilting coaxial rotor electric propulsion system uses a pivotable secondary mast and elastomeric bearing to control thrust direction.

Merging inlet and containment cases eliminates attachment joints, reducing weight while maintaining structural integrity.

Outer band hooks engage turbine case grooves while protruding portions fit shroud slots, minimizing high-temperature gas leakage.

Thermal oxidation forms a protective layer that enables selective alkaline pickling, preventing substrate damage during primer removal.

A lubrication-driven gas turbine actuation system supplies pressurized fluid to variable geometries.

Metallic strut transfers load between ceramic matrix composite nozzle fairing and support rings while accommodating differential thermal expansion.

Axially-extending arcuate seal teeth create a tortuous labyrinth path within the thrust reverser transcowl to restrict fan bypass air movement.

Integrally joined shroud frame and honeycomb seal block combustion gas leakage to reduce thermally induced deformation.

Segmented reinforcement members localize damage propagation during blade-out events, preserving structural integrity without compromising acoustic smoothness.

I-shaped stiffening ribs reduce weight while maintaining load-carrying capacity in gas turbine fan casing clipping members.

A turbine shroud combines a metallic carrier segment with a ceramic matrix composite blade track to manage high temperatures.

A distributed gas turbine engine control system uses remote interface units to provide local closed-loop parameter control.

Water displaces liquid fuel from unused flow paths to prevent combustion gas backflow and coking during multi-fuel switching.

Air extraction reduces engine weight while maintaining reverse thrust force through improved flow attachment.

Alternating fins with curved profiles minimize flow separation at trailing edges, reducing weight and improving reverse flow efficiency.

Direct zirconia deposition removes underlayers, cutting complexity while maintaining anchoring strength.

A protection device compares required mechanical power against a threshold to authorize engine shutdown during rotorcraft overspeed events.

Grit blasting creates perforated acoustic liners that reduce skin friction and drag while maintaining noise attenuation.

A sliding pin mechanism accommodates thermal expansion differences between a ceramic matrix composite center body and a metallic attachment ring.