Leakage Prevention TRIZ Cases

An abradable seal with 1-10 micron pores blocks airflow paths to prevent aerodynamic efficiency losses and blade tip damage.

Sealing element tracks slot geometry between adjacent airfoil platforms to trap cooling air within the engine core.

Electric heating devices on stator parts dynamically adjust rotor clearances to resolve passive control inefficiencies across operating modes.

A slanted and parallel fiber bundle optical sensor detects reflected light intensity to measure tip clearance in rotating machinery.

An aerodynamic seal assembly uses bellows springs and a secondary shoe to maintain a thin fluid film between rotor and stator components.

Elongated pins reduce edge loading stresses on ceramic matrix composite seal segments, enabling high-pressure turbine applications.

Hollow cavity with stiffening ribs reduces nozzle segment flange weight while maintaining structural integrity and sealing efficiency.

A semi-annular seal body with tabs engages a rotatable stator vane to reduce gas leakage between the platform and the moving component.

A radially protruding boss portion extends axially forward from the end wall to structurally support the blade outer air seal.

Series direct acting valves adjust airflow area based on temperature feedback to stabilize heat load and prevent overheating damage.

Variable thickness ceramic plies form cooperating features that restrict gas flow, preventing outer shroud degradation where traditional laminate seals fail.

A steam turbine rotor disk features a dedicated passage redirecting leakage steam to the downstream side.

Three-dimensional weaving creates integrated stiffening elements that reduce hub ratio while maintaining mechanical strength under centrifugal forces.

Purge air holes in angel wing seal flanges create counterclockwise swirls that push away hot combustion gas vortices.

A thermal screen with an insulating cavity delays stator heating to maintain radial clearance during transient operations.

A turbine casing uses a protrusion on the front vertical flange to house a circumferential seal device for tight cross-part joints.

Segmented flow control assemblies meter cool air into specific zones, contracting the case assembly to shrink the gap between BOAS and turbine blades.

Continuous flexible profiles modify inner shroud stiffness at segment junctions, reducing destructive vibratory modes without increasing mass or inertia.

Annular gap with varying radius and labyrinth seals reduces compressed air leakage in gas turbine fluid bearings.

An elastically deformable annular support absorbs turbine casing distortions to maintain constant radial clearances between ring sectors and the impeller.

Segmenting the seal into a disposable strip and minimal sealant reduces engine weight and simplifies maintenance by avoiding lengthy cure times.

Dynamic packing seal clearance adjusts to thrust pressure, stabilizing turbine operation and reducing mechanical stress on fittings.

Segmented sealing assembly prevents exhaust blowby and thermal degradation while maintaining compact axial length.

Axial dovetail attachments on ceramic matrix composite blade outer air seals reduce thermal lockup and improve sealing efficiency.

A labyrinth air seal uses a control ring to maintain minimal clearance between stators and fins during thermal expansion.

Merging sealing functions into component segments eliminates tolerance chain leakage and reduces assembly complexity by removing separate sealing parts.

A rotor ventilation circuit adjusts gas flow to control thermal expansion and minimize clearance with the stator.

Complementary fittings enable axial separation between diffuser and turbine nozzles, shortening the combustion section while maintaining structural integrity.

Low-pass filtering reduces valve wear by removing engine speed oscillations during cruise phases.

Nested seal members float within passages to maintain sealing effectiveness despite thermal expansion differences.

A thin nickel base superalloy seal sheet provides enhanced strength and fatigue resistance for gas turbine engine components.

Segmented heat shields with flexible mounting reduce thermal stress on bearing supports, extending power turbine life under high temperatures.

A pressure-activated seal uses gas differential to push a ceramic-metal composite into contact with adjacent components.

Integrating axial abutments into the composite envelope via simultaneous molding eliminates costly post-manufacturing mounting operations.

A circumferential stop ring provides seal lands to engage seals between a turbine fairing and structural frame.

Axial sealing via a flexible member minimizes out-of-round conditions and lowers stress on the diffuser skin caused by thermal gradients.

A segmented bearing cavity baffle redirects reversed buffer air flow away from the gas path to prevent oil contamination.

Segmented interstage seal minimizes spacing between rotor wheels by eliminating mid-rotor supports and spacer wheels.

Sheet metal sealing elements fill gaps between inner ring and bearing bodies, preventing air recirculation that reduces turbomachine efficiency.

A spring seal assembly with V-shaped legs compresses between arcuate vane support segments to provide a tight seal.

A radial position control assembly uses a differential thermal expansion support ring to maintain optimal clearance between engine components.

Variable pitch stator vanes modulate high pressure turbine rotor acceleration to prevent blade rubs during engine transients.

A turbine assembly uses a divergent flow chamber to produce laminar fluid flow from multiple nozzles.

Columnar microstructure gaspath layers bond to seals, relieving thermal mechanical stresses that cause cracking under high temperature gradients.

A clearance control assembly manages radial blade tip gaps using a baffle-defined chamber to adjust thermal expansion.

A heat shield partitions the gland carrier chamber to insulate the turbine casing component from direct steam contact.

A one-piece annular box structure baffle supports rotor disks with integrated static seals.

A turbine seal ring uses segmented internal parts and an annular cooling channel to manage thermal expansion.

Governing ring with clearance control cavities manages thermal expansion of gas turbine vane carriers to minimize leakage flows and improve efficiency.

A blade outer air seal segment uses a composite alloy body to manage thermal expansion differentials.