Engine Fuctions TRIZ Cases

A turbine shroud segment uses a crossover wall with holes to accelerate coolant flow through its core cavity.

Robotic application of passive strain indicators reduces manual placement time and error while ensuring precise measurement on complex turbomachine geometries.

Rib turbulators and subsidiary protrusions direct cooling fluid to reduce reattachment length and improve heat transfer in turbine blades.

Rub depth indicators on turbine shroud segments enable visual clearance measurement without disassembly.

A hybrid heat engine system converts thermal energy into electrical power using a hydraulic ram mechanism.

A mullite-based bonding layer paired with a yttrium disilicate top coat prevents volatilization and reduces thermomechanical stresses in SiC/SiC composites.

A turbine stator blade design uses contact parts and coolant flow paths to manage thermal loads.

Adjusting the nozzle exit area increases mass flow rate to restart the engine at high altitudes without relying on starter assistance.

Shielded sidewall cavities maintain low-temperature cooling air for outer diameter portions of gas turbine engine airfoils.

A vent passage isolates bypass air flows in the core case, creating pressure differential for impingement cooling without degrading duct performance.

Non-uniform shroud rails tune frequency modes to resolve the trade-off between aerodynamic performance and structural distress.

Angled impingement holes direct cooling air through a leading edge trench, improving heat transfer while simplifying ceramic core manufacturing.

Fuse elements in stationary vanes decouple during rotor overspeed, allowing vanes to obstruct blades and limit terminal speeds.

An ultra-long pre-stressed tensioning element joins segmented wind turbine blades, eliminating fatigue cracks and frequent maintenance checks.

Angled intake lining holes attenuate acoustic waves and prevent icing using compressed gas, resolving the trade-off between reliability and device complexity.

Electromechanical actuator adjusts blade outer air seal position to minimize aerodynamic losses from tip leakage during rapid throttle maneuvers.

Epicyclic transmission selects output for separate displacement members, reducing structural stress from misalignment.

Dual-mode engine operation enables precise in-flight performance assessment.

Heat-shrink sheaths mechanically bond spacer devices to electrical harnesses, preventing abrasion from vibration in turbomachines.

A wave power generator uses a retractable chain to drive an electrical device through gear pulleys.

A vaneless transition duct connects counterrotating turbine stages, removing static flow correcting vanes from the gas path.

Applying auxiliary power to gas turbine spools prevents compressor stall by maintaining stable rotor tip clearance during transient acceleration events.

Thermal storage preheats gas turbine intake air to boost part-load efficiency and flexibility.

Aircraft power transmission casing houses an integral lubricant reservoir to direct fluid flow to critical components.

Hydrophobic sound absorbing fiber batting and vibration isolation pads suppress noise transmission within wind turbine monopole towers.

Varying curvature radii at column-to-plate junctions reduce stress concentrations, resolving manufacturing complexity trade-offs in wind turbine gearboxes.

An annular wire barrel routes wire bundles through a turbomachine rotor shaft via dedicated thru-holes.

Annular flange projections with interior and exterior transition curves increase structural thickness.

Scavenge valve reduces parasitic losses from shaft seal friction by dynamically adjusting flow resistance based on differential pressure.

Plenums route cooling fluid from upstream channels to downstream microchannel slots, solving inadequate cooling of the aft frame's critical rear surface.

Measuring trailing edge wake pressure estimates airflow velocity distribution, resolving the trade-off between detection accuracy and system complexity.

Separate lubricant circuits supply bearings at matched temperatures, reducing heat exchanger weight and complexity.

A dynamic testing method adjusts operating point sequences using distance coefficients and the traveling salesman problem to maximize test coverage.

Segmented hemi-elliptical valve portions reduce angular travel to minimize impact stress while maintaining minimal pressure drop across the seat.

A rotating regenerative heat exchanger prevents carbon deposits and ash contamination on turbine blades by separating combustion from the compression chamber.

Deployable rotating flow control devices extend from the nacelle leading edge to mitigate flow separation and distortion at high angles of attack.

Stowing blocker doors within the nacelle eliminates flow perturbations and aerodynamic drag from protruding components.

A conical heat shield uses integrated axial, circumferential, and radial retention features to secure the component without fasteners.

A centering tool holds pitch link rod ends at a fixed radial angle during in-situ length adjustments.

Uniform gaps between tank walls and ducts reduce heat conduction to adjacent components.

Forecasting thermal conditions via sensor data prevents unnecessary flights caused by solar radiation heating, ensuring accurate damage detection.

Segmented oblong channels mitigate trailing edge tip corner burning by concentrating cooling air at high-stress zones while minimizing mixing losses.

Spring-loaded tool secures the high-pressure shaft for aircraft engine maintenance.

A dual-wall heat shield with internal thermal insulation blocks radiative heat transfer between ceramic and metallic components.

Vertical air intake reduces dust and rain ingress while directing cooling airflow through generator gaps for efficient heat dissipation.

A feather seal assembly directs cooling airflow along a mate-face area using an integrated directional passage and tab structure.

A recessed groove allows X-ray imaging to detect incomplete penetration while preserving base metal strength.

A bevel gear transmission decouples the high-pressure turbine from disturbance torques, preventing rotor oversizing during electrical faults.

Directing oil-laden breather air into the secondary flow channel prevents visible residues and engine soiling while maintaining system simplicity.