Engine Fuctions TRIZ Cases

A translating carrier actuates thrust reverser doors and a deployable fairing along a track, reducing system complexity and weight.

A turbine rear stage ejector extracts upstream airflow to increase stage loading and alter energy distribution during operation.

Dynamic control adjusts fuel flow and ignitor timing to resolve prolonged start times at high altitudes.

A turbofan engine relocates a heat exchanger module into the inlet duct upstream of the fan assembly to utilize intake airflow for cooling.

An endwall slot aligned with the camber direction removes boundary layer flow, reducing secondary flow losses without disturbing mainstream efficiency.

Ceramic seal arc segments use distributed cooling to reduce thermal stress and prevent delamination.

Internal ducts convey hot air to heat an inlet cone, preventing ice formation without degrading composite blade strength.

Braking mechanism selectively transfers rotational energy to an electrical generator, reducing excess losses during non-peak flight times.

Curved turbine airfoil roots constrain circumferential rocking motion during turning gear operation, preventing premature disc and blade wear.

Rotating an aft plate assembly within a circumferential groove aligns ridges to reduce hoop stresses in gas turbine diffusers.

Segmented flexible support decouples interference fit from torque transfer, reducing weight while maintaining structural strength.

Segmenting the mounting system into a bearing ring and a thin-walled support ring reduces friction losses while maintaining secure radial guidance.

A rocket engine fault detection system generates confidence messages through hierarchical data fusion modules.

Segmented trailing edge cooling circuit balances heat load between pressure and suction sides, reducing cooling fluid needed for gas turbines.

Bleed air duct with pressurized air valve induces higher bleed flow from compressor mid-stage, enabling faster and more stable engine start.

Endwall chamber with conductive fixtures mitigates thermal stress in high-velocity trailing edge regions.

A platform trailing edge seal extends into the mateface gap between adjacent airfoil platforms to block hot gas flow.

Internal cooling channels with rib turbulators and pin fins lower hook temperatures, reducing thermal stress and allowing thinner designs.

A deflector in the cooling air circuit directs airflow to reduce particle accumulation on turbine engine platforms.

A steam turbine casing uses a soundproof cover with porous plates on the low-pressure side to absorb noise.

A reverse flow gas turbine core architecture with mechanically decoupled sections.

An estimation unit calculates internal clearance from external sensor data, avoiding high-temperature environments that cause sensor malfunction.

Flexible piping links a nose cone air inlet to a rotor hub manhole cover, venting hot air while preventing water ingress through segmented design.

A geared turbofan arrangement segments the low pressure spool into two compressor sections rotating at different speeds to drive the fan via an epicyclic gear.

External bearings isolate components from high temperatures and simplify maintenance by extracting the bearing assembly from the enclosed housing.

Segmented acoustic panel cell rows with folded sheets form resonant cavities to attenuate exhaust noise while maintaining manufacturing simplicity.

A strut-integrated oil supply assembly relocates tubes to a cooler compressor section using parallel conduit routing.

Pressurized inlet fan forces ambient air through a filter system to remove salt particles and reduce humidity, preventing corrosion in wind turbine generators.

A dual cooling circuit transfers waste heat to preheat intake air, removing moisture and salt to prevent generator corrosion without electric heaters.

Impingement cooling holes target trailing edge tips to resolve gas path migration effects that degrade serpentine cooling effectiveness.

Angled cooling channels prevent particulate debris trapping by directing coolant along non-chordal paths, enhancing heat absorption in gas turbine airfoils.

Detects planet bearing failures by comparing operational trends against baselines, preventing unnoticed damage during extended maintenance intervals.

Segmenting recuperators into parallel and series paths increases turbine inlet temperature, resolving compressor efficiency losses from high pressure drops.

Annular reinforcing ring connects longitudinal elements to transmit loads evenly.

Upstream annular deflector separates air and oil via centrifugal force, preventing oil transfer to downstream cavities and eliminating fire hazards.

A fairing element with a curved suction surface guides fluid flow around obstacles in turbomachines.

Angled dividers split cooling airflow into multiple paths within a tapered gas turbine chamber to maintain fluid structure.

An intermediary spacer eliminates stress concentrations in the rotor attachment by supporting the blade root during rotational installation.

Axially offset bushings reduce laminate strain and extend service life by optimizing load distribution.

A submersible turbine drives a fluid pump to transfer energy to a shoreline generator.

A cooled aerofoil design uses separate internal passages for pressure and suction surfaces to independently optimize cooling air flow conditions.

Flexible coupling in a star gear system manages speed differences and reduces device complexity.

A blade health monitoring method normalizes time-of-arrival data to determine static and dynamic deflection profiles for accurate assessment.

A wind turbine blade repair method uses a clamped reinforcement structure to secure the component during in situ maintenance.

Segmented hollow stator vane uses heating fluid to prevent condensation and a slit to remove coarse droplets, reducing rotor blade erosion.

Segmented borescope plug design accommodates thermal expansion and vibration through movable components, reducing shank stress and extending component life.

In-situ calibration corrects zero-load phase shift using a rigidity factor to resolve measurement precision limits in drivetrain control.

A turbine blade inspection system uses an illumination probe to shine light through internal passages for precise imaging.

Spanning a hatch contour across two adjacent cowls grants access to fixing points without removing the entire cowl assembly.

A circumferential shroud outlet path redirects radial cooling flow to the trailing edge, reducing mixing losses with tip leakage.