Jet Propulsion Plants TRIZ Cases

Pivoting nozzle segments and hoop locking assemblies vary throat and outlet area to control exhaust flow across changing flight speeds.

Fixed-structure fluid actuators move the VAFN cowl without sleeve-mounted hardware, cutting weight, drag, and maintenance burden.

A three-stream mixer assembly blends low-pressure and exhaust flows to support larger fan diameters without added thermal or packaging burden.

Movable thrust reverser panels pivot and translate to redirect exhaust for reverse thrust while helping supersonic engines meet noise limits.

A segmented hinge and latch layout lets inner and outer thrust reverser structures pivot independently for easier access and operation.

An eccentric actuator shifted away from the locking interface cuts actuator count, mass, drag, and nacelle clearance constraints.

Longitudinal deflectors added to nacelle thrust reversal reduce orientation-system mass while preserving efficient upstream airflow redirection.

Deployable reverser panels redirect hot exhaust for reverse thrust while catches and retainers reduce noise and structural complexity.

Multiple rings and radial struts block views of hot engine parts while cooling passages reduce visible-surface infrared emissions.

Fixed-structure fluid-power actuators control VAFN cowl travel while reducing translating-sleeve weight, complexity, and maintenance.

Variable-pitch fan and deployable nacelle flow guides redirect bypass air, reducing thrust-reverser bulk and friction-braking demand.

Independently movable aft cowl components widen propulsor nozzle area without oversized, flutter-prone structures.

A translating core cowl section adjusts the discharge airflow cross-sectional area to optimize engine performance across varying flight conditions.

Integrating the ejection structure into the movable hood reduces overall mass and bulk while maintaining rapid deployment speed.

A symmetric cascade thrust reverser assembly uses mirror-image flow characteristics to redirect exhaust airflow for reverse thrust generation.

Flexible transmission shafts and mechanical coupling devices enable reliable electromechanical actuation of thrust reverser cowls.

A translatable structure within an exhaust duct varies throat constriction and flow diverting ports to control gas direction.

Axially translatable inner nozzle adjusts primary duct cross-sectional area to control gas stream flow in aircraft propulsion systems.

Segmented centerbody and rings mix cooling air with hot exhaust, reducing detectability without sacrificing engine power output.

Patterned rods transmit variable area fan nozzle position data to proximity sensors, detecting thrust reverser deployment skewness to prevent mechanical damage.

Real-time position feedback adjusts individual actuator speed profiles to prevent cowl jamming and deformation during thrust reverser deployment.

Inflatable bladder adjusts bypass duct cross-section via fluid pressure, reducing mechanical stress and fuel consumption during take-off and landing.

Direct cylinder connection to the secondary nozzle with dual-position locking eliminates mass transmission through movable cowls.

Spring-loaded locking mechanism holds thrust reverser doors at intermediate opening angle, removing continuous actuator stress during flight.

Movable flap covers actuator recess in aircraft nacelle main door to maintain external aerodynamic surface continuity during cruise flight.

Merges cascade and variable area fan nozzle panels to reduce device complexity and functional space while maintaining dynamic exhaust area control.

Nested telescoping push rod minimizes linkage obstruction in bypass ducts, enhancing airflow efficiency during thrust reversal operations.

Segmented louver slats vary fan nozzle exit area, resolving the trade-off between fixed geometry simplicity and variable efficiency in gas turbine engines.

Segmented exhaust ducts translate independently to accommodate mixed core and bypass streams, resolving adaptability versus reliability trade-offs.

A variable area fan nozzle assembly uses telescoping couplings and extensible actuators to move the nozzle between stowed and deployed positions.

A bifurcation passage with a valve diverts bypass flow to alter the effective nozzle exit area of a turbofan engine.

A fluidic thrust vectoring nozzle uses a disturbance generator to induce shockless flow separation on the divergent wall.

Closure member blocks duct outlet to redirect exhaust flow, eliminating cascaded vanes that increase weight and manufacturing cost.

Sliding movable vanes intersect fixed cascade vanes to vary reverse thrust, enabling aircraft movement from a stationary position without tow tractors.

A variable area fan nozzle adjusts bypass airflow direction and pressure to provide precise thrust reversal force control.

A thrust reverser system uses a translating cascade and pivotable blocker door to redirect fan airflow during deployment.

Segmenting the cascade into independent assemblies reduces mechanical complexity while maximizing exit area for superior deceleration.

A thrust reverser blocker door axially overlaps a fan ramp fairing surface to minimize inter-component gaps and streamline bypass airflow.

Angularly offset door pivots enhance thrust reversal performance by blocking access to the exhaust nozzle.

Metal-doped SiOC coatings seal microcracks via viscous flow to maintain thermal stability in corrosive gas turbine environments.

Perpendicular flange mounts annular acoustic panel to bulkhead without penetrating fasteners, eliminating air passages that degrade sound absorption.

A two-stage drive element axially displaces the rear engine cowling to position deflection elements and blockage doors within the structure.

Pivoting tapered nozzles redirect exhaust flow to counteract yaw moments during single-engine operation, maintaining aircraft stability without adding drag.

A thrust-oriented nozzle splits the main flow into two half-nozzles with fluidic injection for independent vector control.

Longitudinal frame walls redirect lateral airflow into internal channels to contain reverse efflux within the thrust reverser door structure.

A hydraulic control system manages pressure differences between central and spool valves to actuate thrust reverser doors.

Inhibition pin constrains the locking system to prevent thrust reverser deployment, eliminating manual pin installation and reducing assembly time.

Translating the cascade assembly toward the engine centerline eliminates dead zones in the forward portion, improving reverse thrust efficiency.

A thrust reverser blocker door fairing covers an internal actuation linkage channel to maintain a smooth aerodynamic surface.

Ground-based computer sequence verifies thrust reverser locking means functionality to detect hidden breakdowns before flight.