Engine Fuctions TRIZ Cases

Geometric tuning of turbomachine airfoils shifts resonant frequencies outside the operating range to reduce high-cycle fatigue and extend component life.

Electromagnetic induction heating reduces thermal stress during startup by eliminating temperature gradients between engine components.

Aircraft cooling system uses a water separator and turbine to dry air before expansion.

Temperature-independent shroud rings prevent fluid leakage and contact damage by decoupling radial dimensions from thermal expansion.

A modular blade cradle uses reversible connection interfaces to adapt quickly to different wind turbine blade types.

A gear pump bleed mechanism directs carryover fluid from the discharge side to the inlet side through passages in the gear teeth.

Stepped finger retainers consolidate retention functions into single components, reducing assembly time and part count while maintaining secure coupling.

Ceramic matrix composite airfoil uses a chemically bonded insulating layer to thermally isolate the reinforcement rib from internal cavity heat.

A magnetized damper pin interacts with a rotor magnetic field to maintain slip capability in rotary machinery.

Segmenting structural and aerodynamic vanes allows independent optimization of mechanical strength and airflow efficiency in gas turbine assemblies.

Arcuate retention clips secure airfoils to shrouds through segmented leg engagement.

Reservoirs store lubricant to maintain flow during main system interruptions in geared turbofan engines.

Segmented cavities distribute cooling air to prevent component failure under high temperature flows.

A segmented air inlet lip design separates the de-icing pipeline from the structural wall to enable independent component replacement.

A gearbox mounting configuration uses a frame member extending through the assembly to support rotating components forward of the unit.

Grain-oriented iron laminations in the generator stator reduce magnetic flux resistance and lower core losses.

A tank ullage duct routes gaseous hydrogen to maintain liquid storage pressure, preventing cavitation in aircraft fuel pumps.

A steam turbine cooling unit uses a coolant steam path along the superheated steam supply tube to deliver high-pressure, low-temperature steam for efficient heat transfer.

A controller selects calculation algorithms based on steam turbine clutch status to estimate base load.

An integrated electromechanical device merges the gear box and electrical machine into a single unit with shared structural support.

Shunt coupling with an ejector device maintains water pressure while generating electricity from mains flow.

Linkage system positions fitting outside bypass flow path, reducing thrust specific fuel consumption by eliminating airflow obstruction.

A bushing assembly uses a reduced-diameter band and groove to block radial movement relative to the housing.

A turbine starting controller predicts rotor thermal stress using acceleration rate variables to determine optimal control transitions.

A nacelle reverser flap uses a guided element and groove to coordinate translation with rotation.

An epoxy adhesive bond secures the thrust ring while a snap fit prevents ejection under pressure, resolving reliability issues in single-use motors.

A magnetic-foil bearing system integrates a cooling circuit to deliver compressed air directly to stator and rotor components.

Acute corner support columns in sheet-metal turbine housings minimize wake generation and resonant stress on rotor blades.

A turbomachine airfoil element uses precise resonance frequency tuning to manage vibratory stresses.

Segmented front ring with rail coupling decouples hot and cold zones, reducing thermal distortion in gas turbine vane carriers.

Segmenting the cooling layer into replaceable porous strips reduces maintenance costs while preserving transpiration cooling efficiency.

Segmented turbine nozzle rings with radial slip joints accommodate thermal expansion, reducing thermomechanical fatigue in high-stress vane interfaces.

Segmented stack nut design compensates for thermal gradients to maintain uniform axial clamp force and prevent rotor warping.

Single roller bearings absorb complex loads to reduce gearbox thickness while maintaining misalignment capacity through optimized contact angles.

A thermal barrier coating method applies variable thickness based on predicted temperature profiles to optimize gas turbine component insulation.

Segmented blade outer air seal reuses cooling air through rib passages, lowering temperatures and extending operational life.

Emptying pump conveys transmission oil through lubrication circuit to wear components, eliminating external drain pumps.

Mechanical valve supplies lubricant only when zero teeth engage, reducing wear and maintenance costs.

A nitrogen buffer layer separates gaseous oxygen from liquid oxygen in rocket engine tanks.

Pedestals and a coversheet form an unobstructed cooling path that directs fluid onto the airfoil edge, solving inadequate tip cooling in gas turbines.

Inlet air heating system uses a dedicated heat transfer assembly to route cooling tower fluid thermal energy into the compressor airflow loop.

Metal reinforcements at connection fillets reduce stress concentrations and increase critical buckling force in composite turbine blades.

A viscoelastic coating applied to integrally bladed rotor disks dissipates vibratory energy through localized thickness variation.

Mounting a heat exchanger directly on the compressor housing reduces thermal inertia and leak risks by eliminating external oil lines.

Replacing mechanical switches with magnetic sensing improves reliability and reduces cost for air turbine start systems.

On-ground detection disables safety interlocks to restore reverse thrust availability and reduce landing distances.

Unmanned aerial vehicle positions electrode near receptor to create electrical arc, verifying continuity without manual rope access or costly setup.

A rotor blade tip retaining device separates solid particles from moisture to prevent drainage clogging and lightning-induced vapor pressure bursts.

Threaded connections replace bolts on turbomachine exhaust cases, eliminating scalloped flanges and reducing assembly mass by 500 grams.