Engine Fuctions TRIZ Cases

A three-spool gas turbine engine uses a variable area turbine section to regulate expansion ratio and control rotational speeds across independent spools.

Segmented vanes with varying platform openings resolve manufacturing complexity while improving airflow directionality in gas turbine engines.

A turbofan engine calculates thrust using compressor exit pressure and temperature data.

Bonded elastomeric grommets on rigid inserts seal stator vanes, reducing air leakage without increasing device complexity.

Merges oxidizer and fuel pumps into a unified structure, eliminating separate piping and reducing manufacturing complexity.

Segmenting surge events into onset, peak, and termination phases enables accurate cycle counting without false positives or double-counting errors.

A pump-driven ejector system removes fluid from a chamber using extracted motive flow, eliminating external high-pressure sources.

Software algorithms process existing vibration signals to detect asymmetric icing, eliminating the need for dedicated hardware sensors.

A gas turbine rotor assembly uses composite reinforcement members within annular hub flanges to distribute centrifugal loads.

A variable breaker pivots between protrusion and accommodation positions to restrict swirl-induced vibration without sacrificing turbine output.

Pre-assembled mechanical docking guide with laser and camera aligns turbine engine to generator, reducing downtime.

Variable saw-tooth geometry minimizes noise while maximizing energy capture by adapting spike dimensions to local flow conditions.

An elastic wedge mechanism fixes turbine blades to rotor disks, eliminating vibration and noise caused by thermal expansion gaps.

A twin-shaft gas turbine uses variable inlet guide vanes to manage compressor stability and shaft rotation speed.

Grooves and structural coatings form cooling channels on turbine blade fillets to direct coolant near heat sources.

Radial placement of the electric machine reduces axial length while maintaining electrical power generation capability.

Asymmetric tip structures reduce parasitic drag and vortex formation, increasing annual energy production by up to 3%.

A motor-driven compressor in the evacuation duct creates negative pressure to draw air from a ventilated lubricated chamber.

A segmented heat exchanger configuration distributes thermal management across main and sub units to fit within constrained engine volumes.

Segmented inlet bellmouth sections allow a rail-mounted apparatus to service bearings from below, eliminating heavy overhead crane requirements.

Independent blocking flaps reduce thrust during descent while maintaining aerodynamic stability and preventing counterthrust.

A pneumatic pressure sensor measures valve movement duration to detect deterioration.

Segmenting the insert into a bonded body, expansion sleeve, and threaded section resolves the contradiction between connection strength and design flexibility.

A suction-based active clearance control system uses a downstream valve to manage fan bypass air flow through an annular manifold.

Axially translating air inlet lip extends annular grilles to capture transverse airflow, reducing separation risks under high angles of attack.

A translating sleeve and pivotally mounted blocker door use a delay mechanism to manage deployment.

Segmented modules with decoupler units isolate local circuits, preventing structural stress propagation and maintaining reliability during flow variations.

Segmented counter rotating turbine components route partial torque via a reversing reduction gearbox to lower fan rotor speed and weight.

Segmented journal pin chambers maintain constant oil flow and prevent bearing failure in turbomachine gear systems.

Segmented skin cores with trip strips enhance convective heat transfer, maintaining cooling redundancy when external walls sustain damage.

Segmented rare earth silicate layers with thick sacrificial zones shield CMC blades from rub-induced wear and steam penetration.

Third disk legs contact tie bolts to transfer torque between compressor and turbine sections.

Segmented ceramic-matrix composite shrouds use axial pins and compressive radial clamps to lower rotating mass while maintaining structural integrity.

Flexible arms accommodate thermal expansion differences between ceramic vanes and metallic supports to reduce leakage.

A bimodal rocket igniter uses switching devices to route propellants through buffer tanks for reliable combustion.

A management system predicts pitting corrosion propagation in steam turbine rotor dovetails using operation data and user interface inputs.

Predicts turbine engine fuel flow using current sensor data to selectively initiate operational tests, preventing combustor blowout risks during testing.

An auxiliary reservoir within the annular structure collects gear lubricant via a gutter and channel to supply an auxiliary pump.

A retaining part extends into a disk groove to bear radially on a bulb slot, increasing bearing area while maintaining disk tooth strength.

Porous hook-and-loop fasteners reduce trailing edge noise by shifting frequencies while maintaining lift without complex geometry.

Alternating turbine rotor blades use a shared bearing assembly to maintain consistent clearances, reducing weight and vibration.

A power source control device amplifies adjusting power instruction values using an external coefficient to manage generator rotation speed.

Segmented hub geometry reduces turbulence and flow losses caused by forward-positioned struts in gas turbine engines.

Float arm drives a pulley system to rotate an alternator shaft, reducing device complexity and cost for portable power.

A dual-wall impingement cavity directs cooling jets through internal holes to enhance heat transfer on gas turbine airfoils.

Segmented drainage pipes channel cooling fan water to the outer wall, preventing dirty air ingress that corrodes the generator.

Segmenting the blade interior with a shear web reduces heater size and energy consumption while maintaining reliable deicing coverage.

Cables suspend holonomic crawlers on a cart to inspect complex blade surfaces, reducing manual labor and safety risks.

An air pouch and first cooling holes in a turbine ring segment shield wall improve cooling performance while simplifying production.