Engine Fuctions TRIZ Cases

Positive displacement pump drives check valves via differential pressure to manage fuel flow and evacuation in gas turbine engines.

Nanoparticle-based auxiliary lubrication prevents catastrophic failure during primary system malfunction.

Cross-beam and axial beam structures distribute weight to lift fully-assembled gas turbine casings without disassembly.

A turbine disc cooling circuit uses a sealing joint nested in a groove between the annular flange and retaining member to prevent air leakage.

A recooling unit transfers thermal energy from gear oil to generator air or fluid.

A side link mounting system with strategically positioned apertures and fasteners restricts rotational movement of auxiliary components.

Relocating damper mass from blade platforms to a rotor disk pivot support reduces bending stress on ceramic matrix composite turbine blades.

Labyrinth seals and pressurized air barriers control oil leakage at axial ends, optimizing lubrication reliability in geared turbofan gear reduction systems.

Acoustic field sensors measure pressure waves from rotating blades to determine propeller speed, bypassing drive shaft correlation issues in open rotor engines.

A segmented locking spacer uses a rotating arm to engage dovetail grooves for radial assembly.

Segmented aft bearing assembly enhances low-pressure shaft stability at high speeds without exceeding radial space limits.

Movable aperture covers on the spinner hub resolve structural strength versus maintenance access trade-offs by dynamically adjusting opening sizes.

Discharge holes connect segment gaps to the exterior surface, extracting cooling air from internal cavities.

An ultrasonic measuring device detects screw bolt length under axial preload to verify prestressing states without mechanical intervention.

A mechanical brake in the low speed accessory gearbox halts fan rotation during shutdown.

Segmenting the solid mounting rail into a lattice structure with varying thickness reduces stress concentrations at the outer platform.

Oxy-firing gas turbines capture exhaust carbon dioxide for reservoir injection, resolving the trade-off between power generation and greenhouse gas emissions.

Two speakers along the rotor blade plane reduce acoustic power while minimizing weight and cost.

A turbine bearing trip detection method uses correlation coefficients between temperature and operating parameters to identify abnormal conditions.

Circular supporting rods hold circumferential fibers to prevent root end ovalization during injection molding of long wind turbine blades.

A segmented wind turbine tower uses variable diameters to shift vortex shedding frequencies away from natural resonance points.

Two transverse springs provide discrete chocking forces at the slot front, preventing fretting damage during low-speed rotation and stationary conditions.

An integrated baffle merges with the combustion chamber body to dampen transverse vibrations.

An open cavity deflector redirects cooling gas streams to improve thermal homogeneity and reduce aerodynamic losses in turbomachines.

Angel wing voids interrupt purge air flow to reduce mixing losses and thermal stresses in turbine buckets.

Machining cooling cavities on green state ceramic matrix composite cores resolves manufacturing difficulties from material brittleness.

Segmenting the electric match and seal from reusable ceramic isolators reduces replacement costs in high pressure testing.

An asymmetric discontinuous cross-section damper pin dissipates vibrational energy to tune resonant modes without altering existing blade designs.

Integrated test method for aircraft thrust reverser electrical converters using field-oriented control.

Segmented pressure and suction walls manage high entry temperatures to improve gas turbine engine reliability.

A turbine rotor blade features a T-shaped fitting with anti-twist segments to maintain stable cover contact.

A compressed air energy device uses a common housing for an air turbine and exhaust gas turbine to generate mechanical power.

A dog clutch attachment system secures a turbomachine spinner to the rotor using radial teeth and rotation-proofing pegs.

Placing heat exchangers between adjacent turboshaft engines improves thermal efficiency while minimizing head losses caused by elongated gas paths.

A controller estimates transient heat transfer rates from exhaust gas temperature to adjust combustor operation.

A vane cover with an impingement gap and slot seals a radially extending flange on a ceramic matrix composite platform.

A rigid connection between the air intake lip and acoustic panel back skin forms a main force propagation path.

A turbofan engine bearing arrangement distributes radial and thrust loads across multiple spools using segmented rolling element units.

Electromagnetic shield across modular blade joints diverts lightning current to prevent voltage flashovers at connection points.

Segmented impingement ribs direct cooling air to manage heat flux at non-leading edge stagnation lines without complex internal geometries.

A steam turbine bypass passage directs high-pressure steam to the low-pressure stage, reducing pressure regulation valve size while ensuring cooling.

A hybrid power generation system combines supercritical CO2 Brayton and steam Rankine cycles to optimize heat transfer across temperature zones.

A synchronous generator rotor integrates a liquid cooling system to maintain optimal temperatures.

Platform cooling circuit with impingement pockets and serpentine channels directs airflow across gas turbine components.

Segmented umbrellas on rail tethers aggregate power output while periodic recovery strokes maintain consistent delivery.

A noise signature proximity warning system dynamically adjusts motor RPM and pitch to reduce acoustic emissions.

Dual nuts separate tensioning from support, preventing thread deformation during gas turbine assembly.

A segmented turbine nozzle box divides inlet flow into independent arc sections to ensure uniform steam distribution across the passage.

Cooling cavities overlap the fillet portion to reduce centrifugal load, extending blade life while managing rotational speed constraints.

Tapping high-pressure air and passing it through a heat exchanger lowers its temperature while maintaining pressure for effective blade outer air seal cooling.