Engine Fuctions TRIZ Cases

A jet pump recirculates condensate using feedwater pressure energy to maintain temperatures above the sulfuric acid dew point.

A scroll compressor balance weight portion aligns the centrifugal force center with the rocking bearing to prevent biased contact.

Segmented root support brackets eliminate enclosed ring complexity, enabling safe crane-free blade handling.

A steam turbine drain structure uses a dedicated pan and connection pipe to route discharge water into existing plant piping.

A dual-engine aircraft system uses a gearbox to combine sustainer and booster power outputs.

Straight cooling holes communicate directly with a central main cavity to simplify gas turbine ring segment manufacturing.

A turbine shroud load-distribution system uses a compliant member to manage mechanical loads between the metallic carrier and ceramic blade track segment.

Segmenting the turbine sealing ring into two independent units reduces mechanical stress from thermal expansion and prevents rotor clearance leaks.

Varying blade bolt lengths distribute loads evenly across the pitch bearing, reducing stress on stiffener plates and extending component life.

Two upstream and downstream tabs engage recesses in the disc to limit deformation from thermal gradients.

Recessed parts in the hook section lower stiffness for thermal expansion while a seal member prevents air leakage through the gap.

Rotor blade roots guide swirling cooling air into an annular space, eliminating external pipelines and reducing turbine weight.

Diaphragms reduce pressure and speed of collected airflow before insertion into exhaust openings, minimizing acoustic impact.

Integrating multiple baffle components into a single structure eliminates assembly complexity while maintaining debris containment.

A vane segment design uses a pin mount with an anti-rotation stabilizer rod to secure the support platform.

An expansion-and-contraction member installs on a protruding portion outside the narrow bearing box, enabling rotor lifting in shortened steam turbines.

A removable rotor grasping element frictionally engages a smooth exterior circumference to enable controlled turning via a drive linkage.

Segmenting the housing into distinct chambers reduces differential pressure across the inner wall, lowering material costs and fabrication complexity.

A geared turbofan turbine assembly merges three rotors into a single section to drive the fan and compressors.

An inward concave web section shifts the fan hub center of gravity rearward, reducing airfoil stresses while maintaining structural integrity.

A self-powered shower lighting system converts flowing water into electricity to illuminate the bathroom area without external wiring.

An asymmetric rotor end seal resists economizer flow leakage back to suction plenums, enabling earlier radial port closure while maintaining axial sealing.

Relocating latches to the forward end frees lower bifurcation space and improves maintenance access.

Bushing-based gear carriers reduce component movement under high thermal loads by eliminating tolerance issues in bolt connections.

A heatshield stiffening structure extends between hooks to block coolant jets and ensure even cooling distribution.

Segmented laser projection and display tools measure frame angular misalignment, reducing assembly time and cost.

Heated fuel drives multiple actuators without thermal degradation, enabling sustainable aviation fuel integration.

A ceramic matrix composite airfoil vane uses a bias member to urge engagement with a metallic support spar.

Segmented radial coupling members align tangentially to restrict blade flapping motion, resolving thrust fluctuations during speed control.

Membrane separation splits syngas into CO-rich and H2-rich streams, enabling 28% higher power output while capturing CO2 emissions.

Asymmetric clearance between rotor disc projections and annular grooves accommodates thermal expansion while preventing excessive compressive stress.

Flat pads with axial grooves manage turbine case thermal expansion, reducing blade-to-shroud clearance and assembly costs.

A hydroelectric drive system uses a switch to connect the motor directly to AC mains for emergency operation.

A turbine shroud cooling system uses thin-walled tubes to protect blade track segments from high temperatures.

A monitoring method estimates pump tripping risk using tank filling levels and ship motion data.

Segmented support portions distribute retention force evenly around the circumference, preventing sleeve deformation and dislocation in jet engines.

A water-cooled fixture preserves rotor shaft bearing hardness while induction heating relieves turbine wheel weld stresses.

Heat shield directs cooling air through slots and flow restrictors to cool rotor discs, reducing engine efficiency loss from excessive cooling off-take.

An insert with higher temperature capability protects a turbine wall from oxidation and fatigue while cooling airflow channels reduce heat exposure.

An oscillating heat pipe transfers thermal energy from a gas turbine engine core to an external fluid using phase transitions.

A dehumidifying system removes moisture from compressed air streams using desiccant or condensation components.

Coordinated vortex generators align with serrated trailing edge waveforms to energize boundary layers and delay flow separation on wind turbine blades.

Stacked panels with bonded ribs create tortuous cooling passages that accommodate thermal growth without external manifold expansion.

A method converts low-quality heat into high-speed gas flows using a working medium that absorbs ambient energy and undergoes phase change.

A turbine blade tip clearance control method estimates thermal state using a free-space temperature sensor during engine shutdown.

Segmented pedestals with varied orientations enhance heat transfer coefficients, mitigating thermal stress and extending component lifespan.

A leading edge insert member features axial-extending rib roughened cooling channels to optimize convective heat transfer within gas turbine engine airfoils.

A hybrid through-flow gas turbine engine integrates an electric motor and generator to drive a propeller via reduction and accessory gearboxes.

New guide vanes feature cooling air bores positioned radially inward to redirect airflow and counteract pressure maxima at leading edges.

An auxiliary lubrication system with a dedicated tank and pump supplies reserve fluid to critical engine components during flight maneuvers.