Leakage Prevention TRIZ Cases

A turbomachine lubrication system uses gravity and pressurization to convey air and oil mixtures toward a central separator.

Segmented mandrels remove without tapers to maintain uniform wall thickness and prevent wrinkles in ceramic matrix composites.

An annular intermediate-temperature space reduces thermal stress on gas turbine inner platforms.

An arcuate flange with a deep pin-receiving bore distributes stress on ceramic matrix composite segments, extending lifespan in high-pressure gas turbines.

A turbine engine tip clearance control system uses a rocker arm linkage to radially move blade outer air seal segments for precise gap management.

A ceramic abradable coating applied to the stator blade inner wall narrows seal clearance between the rotor seal fin and stationary components.

Independent sector pressure control counters vehicle motion to prevent bearing and blade tip contact during engine maneuvers.

Radial slots in nozzle seals create tortuous paths that inhibit fluid swirl and reduce rotor-dynamic instability caused by tighter clearances.

An elastically deformable flange secures ceramic matrix composite turbine ring sectors between annular supports.

A cover plate shields radial adjustment pins in a guide vane assembly, blocking axial clearance paths that cause parasitic gas leakage and efficiency loss.

Hollow glass or polymer beads decompose during sintering to form a porous ceramic layer that mitigates deflagration risks in turbine components.

Extended radially internal wall engages distributor recesses to prevent ring disengagement under thermal expansion, eliminating housing hooks and reducing mass.

Fibrous reinforcements and foam layers reduce porosity in the abradable layer, decreasing manufacturing time by 80 percent.

A pressure tank with a perforated wall separates gas from industrial seal oil using natural flow.

A rotary seal mounts on the rotor hub via a flexible medial web portion to isolate the sealing element from extreme thermal and pressure environments.

Oleophilic coatings retain lubricant at seal interfaces, reducing friction and heat accumulation during high-speed rotation.

Composite liner with force-distribution band prevents point loading during blade-off events.

Segmented ceramic matrix and dislocator phases resolve the contradiction between blade protection and efficient tip clearance in turbine engines.

Adjustable exhaust valves control inner casing cooling to reduce clearance sizes and prevent component contact during operation.

Spline seal slots on adjacent sealing members enable damage-free insertion and retention of spline seals, eliminating the need for additional tools or parts.

A unitary support structure with axially and radially extending portions retains a blade outer air seal in gas turbine engines.

A shroud design offsets circumferential segment edges between axial halves to block direct leakage paths across the structure.

Applying a silicon-based coating to ceramic and a non-reactive layer to metallic components prevents chemical reactions at the gas turbine sealing interface.

Segmented support structure controls radial thermal expansion to maintain optimal tip clearance and prevent blade rubbing.

Injecting sealing steam creates turbulence to prevent outer casing warping, avoiding efficiency losses from increased radial play.

A turbine seal support assembly employs a tangential spring mechanism to retract seal segments during low pressure conditions, preventing rotor scrub damage.

A blade outer air seal uses a spaced perforated wall to retain a vane segment for mechanical stability.

Moldable silicone rubber seals minimize airflow leakage and prevent component wear in high-temperature gas turbine engines.

Elastic elements interposed between flanges and CMC tabs accommodate differential thermal expansion, maintaining sector position without complex constraints.

A sensor system determines radial clearance by correlating blade passing signal characteristics with mechanical calibration data.

Radially arranged strip seals shield components from heat and pressure loads while a damping segment constrains flutter to prevent seal degradation.

A steam turbine flow shield deflects steam to reduce thermal gradients, allowing increased mass flow without increasing installation space.

A spring-loaded clip shim accommodates differential thermal expansion between the metallic carrier and ceramic blade track segment.

Passive flow regulators adjust hydraulic resistance in aspiration conduits to prevent rotor contact and leakage under varying pressure differentials.

A compliant coupling system secures a gas turbine shroud using biasing clips within a retaining ring channel.

Sloped slide blocks in a mechanical linkage convert lateral motion to radial seal adjustment, resolving slow reaction speeds in traditional pneumatic systems.

A radial-axial feed pipe conveys pressurized air to a gas turbine bearing housing, maintaining positive pressure when no internal source exists.

An intermediary sealing member fills the gap between the outer vane ring and casing, reducing steam leakage and improving drain recovery efficiency.

Bimodal hexagonal boron nitride and nickel alloy particles create a compliant air seal that reduces blade tip wear and gas permeability.

Radially compliant stationary elements adjust to shaft excursions, reducing leakage and wear in rotating machinery.

Hollow elastomeric seal accommodates thermal growth to minimize fluid leakage between the bypass passage and core engine.

Adjustable suction means recover air-oil mixtures in turbomachine enclosures, resolving low-speed insufficiency.

Oblique wing geometry bridges gaps between inner and side seals to prevent working fluid escape.

A floating support ring enables direct radial adjustment of blade outer air seal segments via threaded shafts.

Pre-assembling segmented shrouds outside the case enables secure hook engagement and rapid insertion.

A sealing segment ring uses multiple identical segments with distributed engagement sites to secure a radial gap between guide vane rows.

External air routing through bypass coolers reduces heat pickup at mid-turbine frame bearing seals.