Leakage Prevention TRIZ Cases

Offsetting foil sector edges blocks hot gases from casing rails, preventing thermal deformation and extending turbomachine service life.

Direct CMC sector retention eliminates metal casings, reducing weight while managing thermal expansion differences.

Segmented airfoil members pivot to adjust airflow direction while maintaining airtight radial seals, reducing leakage around variable stator vanes.

Flexible metallic seals accommodate thermal expansion at the offset transition duct interface, preventing gaps and leakage to maintain seal integrity.

Shell support structure with interior passageway for heating or cooling medium to match thermal growth rates.

An inward-extending deflector blocks hot gas leakage through sector gaps, reducing casing overheating and extending rail lifespan.

Compressed gas enters the seal member through an inlet and flows into the blade gap, using pressure differential to adjust clearance and prevent rubbing.

A radial turbine nozzle employs a movable first end wall to maintain positioning accuracy despite thermal expansion of the back plate and turbine housing.

Simulation program models gap size dependence on operating parameters to activate rotor adjustment without physical measurement.

A refractory metal precursor forms an oxide layer that prevents silicon diffusion, protecting metallic structures from high-temperature degradation.

Segmented turbine housing isolates bearing components from exhaust heat using a shield ring, reducing thermal stress on the bearing housing.

A multi-layer porous ceramic coating protects gas turbine components from mechanical damage.

Polyethylene assembly tools prevent seal yielding during snap ring installation by vaporizing at operational temperatures to eliminate residue.

An inward pointing extension on the seal land secures the blade outer air seal, preventing airflow leakage between rotating blades and the engine casing.

Autonomous clearance adjustment via passive flow modulation enhances gas turbomachine efficiency without external control complexity.

A seal assembly uses a lift channel and biasing element to create pneumatic lift force on the rotor.

Spring-loaded brush seal prevents high-pressure gas leakage by dynamically adjusting contact pressure against thermal expansion of rotor components.

Controlling cantilevered arm stiffness manages interface pressure, reducing wear and thermal degradation while maintaining seal tightness.

A compressor clearance control system uses a casing heat exchanger to transfer thermal energy from turbine exhaust gases.

A multi-layer abradable coating prevents thermal runaway in gas turbines by using a ceramic fuse layer that spalls off during high rub interactions.

An orifice through the generator enables axial oil circulation, bypassing radial injection obstacles caused by downstream positioning.

A hinged seal pivots to accommodate assembly tolerances, decoupling sealing stability from stress concentration in gas turbine nozzles.

Alternating wiper segments with distinct cross-sectional profiles reduce prolonged contact with the abradable member in rotating turbine assemblies.

A hybrid turbomachine seal uses hydrostatic and hydrodynamic forces to lift a sealing member from a rotating face.

A blade outer air seal assembly moves radially with the rotating blade using a pressurized fluid system to maintain consistent biasing force.

An integral half vane structure merges a ringcase, inner shroud, and stationary vanes into a single monolithic component.

Segmenting the casing cavity with an axial seal prevents pressure equalization, reducing hot gas leakage and cooling air loss in aircraft engines.

A guide vane flange uses a beveled partial surface to position the sealing carrier without contact.

A gas turbine mid-turbine frame case boss uses a bushing system to create a sealed piston seal interface.

A shroud assembly uses purge gas cavities to cool turbine components without external forced air.

A dual pressure regulating valve switches bleed air mass flow to heat aircraft components.

A steam turbine system regulates net thrust using leak-off lines and control valves to manage pressure on a stepped rotating shaft.

Pull-off biasing means maintains air pressure balance across the seal, preventing oil fouling and reducing maintenance costs.

Axial tabs create a locking space that eliminates hardcoating needs while reducing fluid leakage in turbine engines.

An integrated clearance control ring merges with a blade outer air seal assembly, eliminating complex bolted flange arrangements and reducing assembly time.

Angled pin holes in stator shroud portions enable secure press-fitted assembly, resolving space constraints from high vane counts.

Machined slit grooves in the porous ceramic abradable layer dissipate frictional heat and discharge debris, preventing seizure while maintaining zero clearance.

Surface-mounted optical paths measure rotor blade clearance without radial bores, eliminating casing leak paths and simplifying calibration.

An elastic catch section secures a turbomachine sealing element, reducing mounting forces and preventing plastic deformation of the safeguard.

A blade outer air seal uses a functionally graded transition region to stabilize the rub surface interface.

Grinding forms smooth seal slots in gas turbine components, while cover plates enclose end gaps to reduce air leakage and assembly damage.

Turbulators on turbine bucket seals modify purge air swirl velocity, creating a curtain effect that restricts hot gas incursion and reduces mixing losses.

A deformable adjustment pin establishes a force fit to lock stator stages, eliminating complex key blocks and reducing assembly time.

Segmenting the mid-seal into two labyrinth seals at smaller radii reduces potential leakage area across the sealing interface, minimizing hot gas ingress.

Segmented inner ring segments and a movable seal carrier adjust sealing gap widths dynamically, eliminating leakage caused by thermally induced deformations.

Layered ceramic matrix composite blade outer air seal injects silicon carbide to resolve stiffness and densification trade-offs.

An asymmetrical receiver cavity and lug prevent unwanted rotation, reducing wear and minimizing cavity leakages in gas turbine engine piston seal rings.

Shrink-fitting a metal clamp ring onto a ceramic shroud reduces thermal stress and minimizes gas leakage.

Piezoelectric actuators replace slow thermal systems to modulate blade tip clearance, preventing rub events and reducing mechanical stress on engine components.