Jet Propulsion Plants TRIZ Cases

Integrating a duct burner into the bypass duct augments take-off thrust without increasing engine length or complexity.

Extracting the intermediate locking mechanism into a removable component reduces system mass and inertia while maintaining reliable torque control.

Asymmetric grid positioning ovalizes the cowl element, reducing nacelle height to improve ground clearance without sacrificing fan diameter.

A telescopic connecting rod mechanism pre-stresses a cascade thrust reverser flap to maintain a locked position during direct jet operation.

A motor-driven liner ring rotates to align openings, reducing excessive sync ring pressure at low speeds while managing cooling airflow.

A turbofan engine bloom mixer adjusts its mixing ratio via temperature-induced deflection of a corrugated partition wall, reducing fan flutter and noise.

Inflatable bladder system varies fan nozzle exit area, resolving weight penalties while maintaining thrust efficiency across flight conditions.

A variable area fan nozzle adjusts exit geometry to stabilize fan operation across flight conditions.

A thrust reverser uses tie rods to synchronize pivoting doors with a translating rear shell ring.

A moveable airfoil within a core cowl pocket adjusts discharge airflow cross-sectional area.

An eccentric ring mechanism adjusts displacement actuator anchoring positions within a turbojet thrust reverser system.

A roller-guided lock mechanism connects a thrust reverser blocker door to a translating structure without obstructing the bypass airflow duct.

A thrust reverser door uses a kicker frame to adjust effective length and redirect airflow for deceleration.

Segmented flexible fixing lugs with axial and radial stop elements resist ultimate loads without increasing assembly mass or stiffness.

Hub-mounted rotary couplers deliver fuel and control signals to tipjets, mitigating retreating blade stall to enable flight speeds exceeding 200 mph.

An exhaust duct eductor introduces ambient air to smooth the velocity gradient of the high-speed gas jet.

A nozzle assembly with pivotally mounted doors redirects airflow for reverse thrust generation.

An integrated turbine exhaust mixer combines deswirling struts within the wavy structure to reduce axial length while minimizing pressure losses.

A resiliently compressible radial spacer manages axial loads between the thrust reverser assembly and the fan case.

A thrust reverser device uses movable cowl and blocking flaps to manage airflow transitions.

Radial duct wall vents redirect centrifuged flow from Variable Pitch Fans, increasing reverse thrust volume while reducing lateral forces during landing.

Downstream-only grid connections eliminate rear frame thickness, reducing aerodynamic losses while preserving deflection efficiency.

Movable components in a gas turbine engine exhaust nozzle resolve the contradiction between low noise emissions during take-off and high efficiency at altitude.

Movable cascades and rotatable flaps accommodate the device in reduced space, reducing drag while controlling variable bypass flow.

An asymmetric deflector redirects exhaust airflow to prevent vertical tail supercharging, ensuring stable aircraft handling during crosswind landings.

Nested actuators within movable nacelle sections resolve device complexity while managing fan stability across flight conditions.

Segmenting actuation into a main and assist unit reduces power demand and system weight during deployment.

A reverse thrust actuation system integrates dual-state locking means to constrain nozzle panels and cowl positions simultaneously.

A thrust reverser locking assembly uses a movable member to inhibit nozzle inner wall deflection during high-thrust operations.

A variable area fan nozzle adjusts bypass duct exit area using a movable aft structure and sealing elements.

Deflecting radial seal panels enhances exhaust mixing, reducing jet noise without adding separate chevrons or tabs that increase device complexity.

A fan variable area nozzle uses a cam drive ring actuator to pivot flaps, reducing mechanism weight while optimizing thrust vectoring across flight conditions.

Passive coupler synchronizes thrust reverser cowl and nozzle movement via fluidic damping, eliminating complex mechanical alignment requirements.

An inclined rotation axis maintains angular trailing edges while varying throat area, eliminating asymmetric gaps and complex sealing requirements.

Outer doors lead inner doors during deployment via a threaded actuator, minimizing backpressure and noise while maintaining thrust redirection efficiency.

Cylindrical channel and external ring constrain actuator deformation during fatigue cycles.

Elastic member forms bellmouth at bypass outlet, guiding airflow and reducing turbulence during reverse thrust operations.

Monitoring method determines lock state using dual sensors and confidence index to reduce information processing complexity.

The nxSERN nozzle integrates a third stream exhaust using isentropic geometries and the Method of Characteristics to define optimal flow paths.

A variable area nozzle mechanism rotates about an off-body axis to adjust throat geometry without introducing vulnerable perpendicular edges.

A pivot door thrust reverser integrates a translatable cascade component to direct airflow forward.

Tilting beams and connecting rods drive thrust reverser doors, reducing mechanism complexity and weight compared to traditional heavy actuation systems.

Pliable cascade vanes fold into a small chamber, reducing engine nacelle weight and drag while simplifying manufacturing complexity.

A translating variable area fan nozzle assembly uses a deflector to constrain bypass flow exiting through an upstream path.

Replacing hydraulic systems with dual electric actuators reduces weight and doubles deployment speed while managing synchronization complexity.

A movable exhaust nozzle rotates between positions to block flow or direct gases vertically, resolving safety risks during ground operations.

Adding a curved flange to the aft end of a thrust reverser lower bifurcation wall mitigates flow separation and minimizes aerodynamic drag during operation.

A nacelle assembly integrates a translatable sleeve with cascade arrays to redirect bypass flow for thrust reversal.

Single actuator assembly with differential gears drives dual translating cowls, reducing mechanical complexity and maintenance costs in turbofan engines.