Engine Fuctions TRIZ Cases

Secondary tangential onboard injector reorients leakage flow to eliminate turbulent mixing losses and enhance turbine efficiency.

Porous airfoil coating filters dust from cooling air streams, preventing internal passage blockage and maintaining temperature control.

Complementary integral cover and base reduce vibratory stress in high-speed turbine blades, extending operational lifespan.

Bypass diverter valves route water between economizer and evaporator sections, reducing energy losses from suboptimal steam reheat.

A flexible support structure accommodates transverse deflection to maintain constant torque transmission during flight maneuvers.

Relief grooves in rotor discs suppress stress concentration to alleviate low-cycle fatigue without increasing manufacturing costs.

Segmented input shaft with annular bellows and U-shaped parts provides multi-directional flexibility while minimizing radial dimensions for compact integration.

A heat exchange unit cools compressed gas to enable efficient storage, recovering heat energy for later use during expansion without a combustor.

Turnbuckle assembly increases lateral stiffness of bypass duct heat exchangers.

Controller activates electro-mechanical clutch to link spools, preventing rotor lock and dual flameout risks.

Flow relief pathways equalize pressure distribution across bifurcated inlet duct legs, reducing distortion during yaw angles and reverse flight.

A thermal barrier coating on the backside of a ceramic matrix composite turbine shroud regulates heat transfer to adjacent metallic hardware.

Axially displacing a segmented outer sealing ring enables direct removal of the foremost gas turbine rotor.

Reinforcing ribs aligned with the principal axis of inertia reduce bending tendency and stress levels in high-speed turbine shrouds.

Segmented rail shield assembly reduces gas flow escape and thermal stresses by managing thermal expansion differences between components.

Merges drainage functionality into the core segment structure to eliminate complex tube bonding and galvanic corrosion risks in critical regions.

Resupply channels interconnect cooling passages to minimize pressure losses and reduce metal temperatures.

Thermal stress relief slots in the cold side wall accommodate relative thermal expansion, reducing structural stress while maintaining rigidity.

Over-pitching variable pitch fan blades eliminates swirl-induced drag during engine out conditions, reducing total drag by up to one-third.

Alternating rotor blade stages resolve thermal expansion and centrifugal force issues by maintaining symmetrical shape.

Segmented piccolo tube holes shift anti-surge discharge noise outside human hearing range while maintaining compressor surge protection.

A dynamic cooling system adjusts refrigerant flow to maintain optimal temperatures in hybrid gas turbine components.

Segmented angel wing voids create a swirling purge air curtain that restricts hot gas incursion into the wheelspace while reducing mixing losses.

Electron beam welding joins steam turbine nozzles with low heat input, preventing steam path distortion and eliminating costly post-weld stress relief.

Segmented dual planetary stages adjust rotational speed flexibility without increasing axial length or mechanical stress.

A tension-preloaded transverse stiffener constrains eigenmodes of vibration in a deployable rocket motor nozzle mobile segment.

Torque extraction system manages rotor vibrations via electric machine coupling.

Consolidating accessory drive systems reduces gearbox length while maintaining independent operation.

Segmented hydraulic actuators adjust vane angles to improve efficiency while trip valves ensure compressor protection during emergency shutdowns.

Radially biased sealing rings compress within a circumferential cavity to prevent fluid leakage through mechanical joints, improving axial blade retention.

A metal foam bushing connects ceramic matrix composite components to metal holders via a retaining pin.

A counter-rotating fluid generator uses automated positional control to optimize energy capture from bidirectional flows.

A gear integrated generator reduces mass and thermal growth issues by using a single-stage planetary gear with forced air cooling.

Continuous in-situ thermal management reduces assembly time lag and prevents component damage during interference fit.

A fuel circuit transports cryogenic hydrogen to a gas turbine combustor using heat exchangers and inert gas purging to prevent nozzle overheating.

A network structure processes operational data to determine feature confidence values and diagnose machine states.

A damage evaluation apparatus computes creep deformation velocity of steam turbine nozzle diaphragms using real-time sensor data and heat balance calculations.

A gas turbine engine heat exchange system adjusts oil flow through a fuel-oil heat exchanger using a bypass valve to manage thermal loads.

Rotation creates an air cushion that lifts the fixed component, allowing oil to cool the interface and prevent carbonization caused by friction.

Modular bearing support aligns the low shaft on the front frame, reducing misalignment loads and high cycle fatigue in compact turbofan assemblies.

Segmented heat shield blocks radiant energy transfer from hot fairings to casings, preventing frame material degradation.

Airfoils with defined span and chord dimensions achieve specific natural frequencies to avoid resonant conditions that cause vibrational stresses.

An oblique cooling hole through a suction side winglet cools the squealer rim while reducing tip leakage flow and pressure loss.

An abrasive grit coating on a cooled turbine blade tip resists wear from shroud rubbing while maintaining oxidation resistance.

Radial deflection means divert primary flow to mix with secondary flow, reducing temperature peaks and mixing distance.

Elastomeric pockets in stator vane assemblies absorb vibrations and resist displacement under high pressure loads, maintaining structural integrity.

Thermal isolation barriers in the bearing sump allow lubricant to operate at 550°F, resolving temperature reliability trade-offs.

Superfinished gear surfaces and inline filtration resolve viscosity trade-offs to reduce wear in wind turbine gearboxes.