Leakage Prevention TRIZ Cases

Asymmetric spline seal geometry prevents inadvertent removal during thermal contraction while preserving sealing effectiveness.

Segmented rare earth silicate layers mitigate thermal strain and prevent spalling on unmachined ceramic matrix composite components.

A single fixture and end mill machine convex and concave shroud sides simultaneously, reducing machining time and errors from repositioning.

Folded tongues on the inner ring press against the radial partition, resolving insufficient socket space for hollow vane manufacturing.

Molding cylindrical fiber fabric into shroud segments eliminates complex stitching operations while maintaining high strength for gas turbine engines.

A ternary oxide coating on a nickel-based superalloy piston seal reduces friction and wear by forming solid lubricant nanoparticles under vibratory motion.

A mechanical iris adjusts blade tip clearance via pivoting leaves to optimize gas turbine performance.

Actuators deform a low-pressure casing end plate to adjust axial position, resolving thermal expansion differences between the rotor and casing.

Planar light sources and intersecting optical fibers suppress specular reflection errors during clearance measurement of rotating turbine components.

A modified inverse model control system uses variable gains to adjust integration time and tune dynamic response.

Cambered sealing plate decouples overlap clearance from overspeed clearances to prevent hot gas recirculation.

Segmented inner shrouds use protruding seal plates to reduce cooling air leakage from one-piece outer shrouds.

A turbine shroud uses a cross-key connection between a metallic carrier and ceramic inserts to accommodate differential thermal expansion.

A gas turbine assembly uses a movable element to regulate the clearance gap between rotor blades and stator vanes.

A static shroud sealing arrangement featuring a circumferential groove with a sealing ring and support structure that captures cooling air.

Merging the wear liner and seal into one component reduces gas turbine engine air leakage while simplifying assembly complexity.

Passive Z-bands accommodate seal ring thermal expansion relative to the fan casing.

Bimetal and shape memory alloy actuators adjust radial clearance between rotating and stationary turbomachine components during thermal transitions.

Segmented exit flow discouragers form tortuous paths that block hot gas ingestion and reduce cavity temperatures.

Segmented inlet assembly with plenum reduces pressure losses during cooling air distribution, preventing blade tip rubbing.

Bending the large-diameter portion against the probe wall eliminates sealing members, preventing fiber denting in high-pressure turbine environments.

Automated parameter download from sensor memory to the electronics interface resolves manual calibration bottlenecks while maintaining measurement accuracy.

Tapered band sections on CMC turbine vanes accommodate seal members, preventing fiber cut-off and maintaining structural strength.

Segmented geometry enables a sealing plate to act as a fuse by recoiling downstream during rotor overspeed, preventing casing contact.

Segmented cooling channels in stator heat shields transfer heat from hot gas surfaces to cooling fluids.

Dynamic seal adjustment uses electromagnetic reflection and transmission to resolve thermal expansion trade-offs while reducing system weight.

Internal passages route cooling air into seal slots to purge segment gaps, reducing leakage and improving turbine efficiency.

Angular features in the seal element connect pressurized cavities to reduce leakage and purge air requirements.

Axially acting spring force on inner ring compensates for thermal deformations, reducing leakage and wear in turbomachines.

Curved damping strip seals block air leakage and dampen flutter movement, enhancing turbine shroud longevity.

A turbine shroud assembly uses retaining elements with inclined portions to hold ceramic matrix composite ring sectors securely.

Axial seal members receive radial urging from forward and aft seals to dampen flutter movement, extending service life while maintaining sealing effectiveness.

A blade outer air seal uses partial ceramic coatings and internal cooling passages to manage heat distribution across the gas path surface.

A planar spiral inductive sensor measures blade tip clearance using impedance changes from rotating conductive structures.

An intermediary bumper absorbs gap variations between structural components, preventing excessive finger seal stress and leakage across lengthy distances.

A puller actuates air seal segments to maintain radial tip clearance in gas turbine engines.

Angled fin geometry reduces air heating and component damage by limiting contact surface area during axial movement.

Preformed annular slots in the stator coating guide rotor lips, limiting wandering and preventing costly repairs.