Engine Fuctions TRIZ Cases

Segmenting the vane into a metallic support and CMC airfoil reduces cooling air usage while maintaining structural integrity under aerodynamic loads.

Nonlinear feature extraction algorithms detect imminent compressor stalls by analyzing casing pressure signals for specific flow disturbances.

Spacer plates and lock washers enhance bearing surfaces to maintain bolt preload, preventing loosening caused by thermal expansion and creep deformation.

Sectored exhaust fairings enable independent removal to resolve complex assembly constraints while maintaining gas leak integrity.

Turbomachine airfoils use specific span and chord ranges to align natural frequencies outside engine operating speeds, preventing resonant stress.

A nested insulation sleeve resists thermal transfer at service line interfaces, reducing heat load on oil-wetted bearing compartments.

A downstream orifice in a turbomachine air duct circulates hot air to melt ice and clear clogged drain holes.

A turbine damage evaluation device uses real-time operational data to calculate material deterioration and predict failure risks.

Radial damping members prevent axial contact with downstream rotor discs, reducing wear on blade mounting feet and extending component lifespan.

Interlocking upper and lower bayonet blocks prevent turbine disk rotation, eliminating bolted stress concentrations and reducing assembly weight.

Flanged bushings support axial loads on a small-diameter shaft, increasing load capacity without adding thrust washers.

A method predicts ice accumulation on wind turbine rotor blades using system variable data and compensation calculations.

Keyed retention clips engage grooves in the shroud hanger to secure ceramic matrix composite segments, eliminating edge damage from interference fits.

Crowned nickel alloy sliders guide aircraft nozzle flaps along cobalt tracks, reducing Hertzian stress and preventing excessive component wear.

Variable pin density directs impingement cooling jets to critical zones, reducing thermal stress without increasing cooling air consumption.

A frangible cable fuse transmits mechanical actuation force from an emergency fuel shut-off actuator to the valve mechanism.

Segmented epicyclic gearbox reduces windage losses at cruise by disengaging idle units, improving fuel efficiency and reducing clutch wear.

Stacked tubes form an annular wall that shields exhaust gases while transferring heat to cooling air, eliminating bulky thermal blankets.

Extracting cooling air supply from the outer shaft bore into a dedicated plenum chamber reduces bearing weight and device complexity.

Variable tandem outlet guide vanes redirect fan exit air to minimize losses created by inlet distortions.

Radially outward turbine rotor eliminates concentric shafts, reducing engine weight and leakage while enhancing disc strength.

Heating leaked liquid fluid into gas at the pump-turbine interface reduces vibration amplitudes and prevents disc damage.

Time-domain reflectometry detects blade damage without stopping operations, resolving the trade-off between inspection precision and turbine uptime.

Nozzle assembly integrates a virtual impactor to accelerate cooling fluid, separating particles via inertia to prevent turbine component clogging.

Radial fluid circuit orientation reduces radial space requirements while accommodating Fan Blade Out displacements in turbomachine stator supports.

A refractory metal core assembly uses axially extending tabs and radially connecting ligaments to form cooling features directly during casting.

Axial standoff ribs and structural ties enable cooling flow through gas turbine engine components while preventing side wall bulge under thermal load.

A slurry chromizing process applies a coating containing a residue-removal agent to articles with internal passages.

Resonant acoustic excitation enhances heat transfer rates without increasing pressure drop across compact passages.

Uses cooled compressor discharge air to pressurize turbine bearings, eliminating external instrumentation air requirements and reducing power consumption.

Fluid supply ports generate a pressurized film that prevents contact during transient movements, reducing leakage and wear in turbine engines.

Removable panels on a turbojet intermediate case hub use retaining elements to hold base plates against internal faces for secure bleed line attachment.

Porous face sheets on acoustic cavities reduce wake-vane interaction noise while integrated cooling channels manage engine oil temperature.

Partial baffles reduce cross-sectional area within airfoil cavities, lowering pressure loss and weight while maintaining uniform temperature profiles.

An electrolyzer supplies high-pressure hydrogen and oxygen to a gas turbine combustor and cooling system, eliminating compressor bleed air extraction.

Drilling cooling holes orthogonal to the apogee eliminates surface scarring and positional variation while maintaining aerodynamic efficiency.

Sprayable thermal barrier coating powder mixture cures in situ within engine operating temperatures, eliminating disassembly and separate curing steps.

An adaptive-area hub adjusts inlet geometry to separate suspended particles from gas turbine airflow using inertial separation principles.

A lubrication circuit heat exchanger transfers thermal energy from an actuator device to prevent lubricant freezing during turning gear operation.

Higher pressure cooling steam prevents leak steam entry, maintaining thermal efficiency in single-flow turbines.

Axial recesses around orifices distribute thermal and centrifugal stresses homogeneously across the rotor disk web without adding mass.

External planetary gear train isolates backlash from engine shaft, reducing torsional resonance and power loss during intermittent accessory operation.

Radial cooling passages in ceramic matrix composite vanes remove heat from the trailing edge, eliminating complex axial holes and simplifying manufacturing.

Segmented metallic layers prevent crack propagation in high-pressure turbine disks, maintaining structural integrity under hot corrosion conditions.

Segmented carriers nest ceramic matrix composite blade tracks to minimize radial package space while managing thermal expansion.

A propulsion system uses an electric motor coupled to a fan to resolve the trade-off between fuel efficiency and rapid thrust response.

A non-contact displacement probe mounted in a vane cavity measures radial distance to turbine blade tips for precise clearance data.

Removing the spline ring between the ring gear and turbo fan shaft eliminates wear, deflection, and heat generation from windage.

Segmented intake holes and exhaust grilles resolve uneven cooling in large bypass ratio engines by balancing flow loss with uniform temperature distribution.