Efficient Propulsion Technologies TRIZ Cases

A foldable attachment hanger system supports a gas turbine cooling liner within an exhaust duct.

Segmented orifice plates create cross-impinging flow to reduce bleed air noise without increasing muffler weight.

Carbon nanotube strips replace bleed air systems, eliminating engine performance penalties while preventing ice buildup on composite nacelles.

A turbine shroud uses a strip seal to block gas flow between metallic carrier and ceramic blade track segments.

Movable studs redirect air around the combustion chamber during detonation, reducing drag while maintaining precise cycle control.

Captured nuts and attachment fasteners secure the fan track liner to the annular case, reducing maintenance time compared to adhesive bonding.

Axisymmetric composite parts with annular slots form resilient fastener tabs that attach directly to metal exhaust casing arms.

Segmenting the nozzle wall into fixed and translatable structures allows independent thrust reverser actuation, reducing radial dimensions.

Detects rotating stalls via static pressure variation and turbine outlet temperature thresholds to prevent compressor blade wear.

Varying effusion hole density matches non-uniform exhaust temperatures, reducing gradients and extending scroll durability.

An automated test processor controls an aircraft engine fuel switch to precisely stop fuel flow at a target speed.

A multi-piece seal accommodates differential thermal expansion between metallic carriers and ceramic matrix composite blade tracks in gas turbine engines.

Flexible deflector mechanism obstructs lateral openings in thrust reverser doors to redirect fluid flow and maximize counter-thrust force.

Elastomeric lamellar joints eliminate heavy mechanical bearings to reduce joint mass and maintenance requirements.

A thrust reverser grille uses injection molding to consolidate continuous and discontinuous fiber components into a single structure.

Interstage bleed system delivers warming air to inlet bleed heat components before activation.

Composite fan case with compliant layer maintains blade clearance despite thermal expansion.

Radial cooling protuberances increase surface area exposed to lubricant, reducing wall temperatures in compact bearing compartments.

A hybrid propulsion system for aircraft combines a hydrogen fuel cell unit and a gas turbine with an electric propulsion unit.

Transverse terminal surfaces with increased width shield phase terminals from lightning strikes and arcing while maintaining compact generator design.

A monobloc thrust reverser frame integrates deflection grids and actuator pathways into a single structural unit.

Contoured stator vane platform directs cooling fluid through angled holes to improve heat dissipation.

Distributed latch pins resolve the weight-strength trade-off by splitting reaction loads across multiple smaller components.