Leakage Prevention TRIZ Cases

See how segmented seal layers with tension cable tensioners maintain sealing integrity despite

Intermeshing resilient seal blocks create a self-sealing cable port that maintains high ingress protection across varying cable sizes.

External shaping tools preload turbine engine housing flanges during bonding to prevent deformation and preserve nominal casing geometry.

A ductile inner ring and spaced outer ring absorb fragment impact and maintain turbine casing containment with lower weight and thickness.

Grooved adhesive joints between the turbine rotor and hollow spindle raise fixing force and help medical cutting tools stop quickly after air cutoff.

Rolling elements between the carrier and aft bearing cut seal friction and wear while limiting gas leakage and avoiding leakage airflow.

An oil discharge groove below the shaft axis drains lubricant away from the seal gap, reducing buildup and unintended leakage in turbochargers.

A sloped stationary-side end surface drains lubricant from the turbocharger seal gap, reducing buildup and unintended leakage.

A slotted, variable-thickness CMC hook attachment region relieves thermal strain and improves mounting accuracy in gas turbine components.

A spring-based turbine seal support retracts seal segments at low delta pressure and moves them inward as pressure rises to limit rotor scrub.

High-pressure compression and reactive sintering below 550°C create an abradable ceramic coating that balances erosion resistance and wear.

A stepped installation tool mounts an aircraft seal runner by interference fit, then releases axial preload to cut internal stress and extend life.

An extending sealing part bridges crossing seal gaps in gas turbines, simplifying assembly while improving sealing stability and efficiency.

Buffer air tandem seals let metallic carriers and CMC blade tracks expand differently while limiting leakage, wear, and misalignment.

Pressure-sensor feedback and a piezoelectric stack rapidly adjust turbine inter-stage and mid-seal clearance to cut pressure loss and wear.

A large single-radius support face lets CMC blade outer air seal hooks be formed more accurately while preserving mounting function at high temperature.

Circumferential notches let a gas turbine retention ring hold seals securely under vibration, then sever cleanly for easier removal.

Compressible brush bristles seal nacelle leakage paths while accommodating translation, helping turbofan casings cut performance loss.

A recessed dual-surface outer air seal improves first stage casing sealing by shaping the bleed air slot for compatibility and manufacturability.

Six spring-supported packing ring segments cut rotary contact force, reducing frictional heat, shaft vibration, and leakage during transients.

A spring-backed seal support and angled lip segments maintain rotor clearance under pressure changes, reducing rubs, wear, and airflow leakage.

Pressurized buffer air keeps turbine shroud carrier and blade track seals engaged despite differential thermal expansion, reducing gas leakage and wear.

A movable sled seal uses buffer air and spring bias to maintain turbine shroud sealing under differential thermal expansion while reducing wear.

A deeper slot and symmetrical oblong opening relieve peak stress in turbine nozzle mounting rails while preserving durability and manufacturability.

Pressurized fluid is injected downstream of the turbine during a shaft break to cut pressure differential and limit overspeed damage.

A shaft break mechanically triggers downstream pressurized fluid injection to cut turbine pressure differential and limit rapid overspeed.

A thrust bearing links shroud motion to rotor thermal growth, holding tip clearance to cut air leakage and avoid blade rub.

A stepped installation tool mounts a seal runner by interference fit, then axially disengages the runner mount to reduce preload and internal stress.

An angled elliptical vane inlet and conforming shroud plug seal the interface to prevent air ingestion and improve turbine airflow uniformity.

Dynamic valve control adjusts turbine tip clearance from engine parameters, improving fuel economy while avoiding rubbing and instability.

An angled elliptical vane inlet and conforming shroud plug seal the inlet case interface to prevent air ingestion and flow non-uniformity.

A monobloc intermediate casing integrates the structural arm and aerodynamic profile to cut turbomachine length and mass while easing assembly.

Large-radius BOAS mount hooks make CMC seals easier to form while maintaining fit tolerances and reducing turbine leakage.

Intermediate-expansion sealing elements limit wear and gas leakage between CMC rings and metal casing parts in high-temperature turbines.

A staged seal, pressure-balancing line, and separator keep working fluid out of gearbox oil while supporting integrated speed reduction.

Split abradable linings on the fan case and air inlet cover variable-pitch blade contact zones while reducing engine size and easing blade removal.

Injecting pressurized fluid downstream of the turbine rapidly cuts shaft-break pressure differential to limit overspeed and disc burst risk.

A spring-backed seal support lets turbine seal segments shift radially with pressure changes and rotor vibration to cut rubs, wear, and leakage.

A low-porosity hafnon, zircon, or rare earth disilicate coating balances blade-tip abradability with resistance to CMAS infiltration and spallation.

A low-porosity hafnon or rare earth disilicate coating uses softer dislocators to stay abradable while resisting CMAS infiltration and erosion.

Movable outer air seal segments and a compliant air seal maintain blade tip clearance, cutting leakage while limiting blade contact.

A stepped, conformal OAS interface maintains sealing and bleed air flow control while staying manufacturable after compressor casing treatment changes.

A vented ring seal uses guided airflow and through-openings to stabilize temperature, reduce clearance variation, and limit turbine leakage.

Independent electric-machine control of turbine spools maintains blade tip clearance, reducing rub events without slowing thrust response.

Hot and cold fluid flows adjust an aircraft engine’s active surface to maintain blade tip clearance during temperature transients.

A voluted hook-shaped discourager forms a recirculation zone that returns hot gas to the turbine flow path, protecting disk-cavity durability.

Engine gas loads can deflect low-density abradable seals and increase rotor contact; radial-wall casing support limits deflection and rub heat.

A circumferential web plate uses flexible seals between the transition piece and turbine nozzle to limit oxidant leakage during thermal movement.

Flingers redirect dust-laden airflow away from aspiration conduits while shielding the seal from thermal distortion.

Elastic springs mount low-ductility ceramic matrix composite shrouds to resiliently urge the ring into a concentric position within the support member.

Pre-formed epoxy pieces replace manual paste application, reducing engine downtime and improving seal quality reproducibility.