Engine Fuctions TRIZ Cases

A probabilistic control system tunes gas turbines by adjusting power output and operating conditions based on measured ambient parameters.

Internal and annular flow passages in tubular spokes recirculate coolant to prevent bearing misalignment caused by differential thermal growth.

Scalloped retaining ring surfaces distribute contact forces across curved segments, preventing cover plate cracking at the end gap.

A gas turbine vane uses a pressure-side lip to direct cooling air discharge before the trailing edge.

A gas turbine starter calculates torque setpoints from rotational speed measurements to regulate engine rotation during startup.

Spool lock and lift system support compressor rotor assembly for direct removal from engine, eliminating external crane requirements.

Segmented cooling channels within a turbine rotor blade platform direct coolant through nested supply and return paths.

Segmented cascade array vanes join thermoset strongbacks via thermoplastic coatings, reducing manufacturing complexity while maintaining structural integrity.

Porous material fills serration gaps on wind turbine rotor blades to shift noise frequencies higher for faster ambient dampening.

Mobile door controls ventilation rates to cut fuel consumption while directing extinguishing fluid for compact fire suppression.

Segmenting the main oil tank with an actuated supplementary unit resolves space constraints from increased idle gulp volumes.

Metallic spar support transfers aerodynamic loads from ceramic matrix composite vanes, resolving structural strength limits at high temperatures.

A corrugated bushing absorbs engine vibrations through elastic deformation to protect the gearbox coupling.

A partially constructed lower reservoir enables early energy generation and storage during the building phase of an underwater pumped-storage power plant.

C-shaped metallic retaining clip radially secures ceramic matrix composite blade outer air seal segments to turbine support structure.

Cylindrical leg portion prevents cooling flow recirculation in turbomachine seal support structures.

Deformable locking inserts replace staking to prevent rotor deformation during blade replacement.

Crushable spacers and bushings manage unbalanced rotor loads in turbomachinery flanges, maintaining centerline alignment.

Segmented cavities eliminate flow balancing issues from sensitive wedge angles, enabling lower angles for better aerodynamic efficiency.

Integrating an acoustic absorption device into the rear cascade-support structure reduces noise emissions while maintaining aerodynamic efficiency.

A heat shield segment features a radially elevated section along its curved profile to reinforce structural integrity.

Removable annular flange holds CMC ring sectors via attachment hooks, reducing mechanical stress from metal heat expansion.

A gas turbine inlet duct hood directs airflow through a scarfed aperture and secondary outlet to manage mass flow.

A belt drive mechanism uses flexible members with segments under zero tensile load during operation to reduce wear and noise.

A turbofan engine uses an adjustable convergent-divergent thrust nozzle to manage airflow dynamics.

Multi-radius transmission decouples complex wave dynamics from generators, resolving the contradiction between high power output and device complexity.

Real-time temperature monitoring drives dynamic motoring adjustments that reduce thermal gradients and minimize rotor distortion during cooling.

Multi-layered porous acoustic structure with woven textile layers increases mechanical strength while reducing mass and maintaining aerodynamic performance.

Discharging coolant as a free jet across the duct cross-section improves temperature uniformity and reduces consumption compared to standard film cooling.

Impingement holes deliver targeted cooling air to predicted hotspot positions on the airfoil surface.

A controller predicts wind turbine battery lifetime using ambient air temperature data to schedule replacements based on actual degradation rates.

Ceramic matrix composite airfoils use embedded pins to increase heat transfer coefficients within cooling cavities.

Snap ring and relief groove replace locknuts, eliminating high torque safety risks.

A nanofriction power generation device uses spiral channels and vibrating hollow balls to convert wave energy into electrical current.

Rotor-mounted guide flanges direct lubrication liquid away from hot zones, preventing ignition risks while reducing machine volume and weight.

A hydraulic cylinder vent discharges trapped air via a check valve, resolving compression inefficiencies that reduce power generation output.

Ablative gas blocking device erodes predictably to maintain optimal nozzle expansion, reducing thrust loss and instability across varying altitudes.

Density gradient in ceramic matrix composite blades lowers centrifugal stress at the root, reducing overall mass and improving gas turbine efficiency.

A turbine assembly uses a sliding connection between ceramic matrix composite components and a metal casing to accommodate differential thermal expansion.

Integrating a planetary drive inside a hollow input shaft reduces nacelle weight and size while maintaining high-speed conversion.

A fuel gas compressor uses thrust-balancing discharge gas to heat the fuel stream before it reaches the dust collection device.

Air-cooled turbine blade featuring a wishbone-shaped architecture at the transition point between internal flow circuits and trailing edge pin bank.

Reuse salvaged engine-run cooling baffles on new airfoils to cut repair costs while maintaining serial number traceability.

A gas turbine control system blends secondary gases with primary fuel to maintain combustion stability and reduce natural gas consumption.

Diverting working fluid from the high-pressure turbine to the low-pressure turbine stabilizes compressor rotation speeds in two-shaft gas turbines.

Unitary ceramic matrix composite stator vane maintains continuous reinforcement fiber fabric throughout its structural sections.

Segmenting compressor units from turbines allows multiple intercoolers to reduce shaft length and torsional stress while improving efficiency.

Axial and circumferential ribs on a solid cooling sleeve distribute thermal loads uniformly, reducing high cycle fatigue and manufacturing complexity.

A computer-implemented method selects an engine control profile from a directory based on operating and contextual conditions.

A gas turbine controller detects shaft failure using compressor speed signal continuity and pressure data to initiate a controlled shutdown.