Continuous Combustion Chamber TRIZ Cases

Slit-mounted radial throttle pieces install without separating the tubular body, enabling circulating flows that suppress unburned carbides.

Segmented main and auxiliary valves control fuel flowrate across load ranges, reducing carbon monoxide emissions at very low partial loads.

A combustor deflector redirects compressor air through base holes to enhance cooling while maintaining flow stability and reducing thermal shock.

Capillary pressure from the porous barrier counteracts gravity to ensure uniform fuel distribution across the annulus at low flow rates.

A reverse flow combustor uses a curved dilution portion to mix fuel and cooling air efficiently.

Channels extending from a fastening device to the edge reduce cooling air consumption while maintaining hot side temperature.

Selective fuel passage purging bypasses the manifold, reducing air consumption and preventing nozzle coking while maintaining system pressure.

A gas turbine combustor uses a resistive element to trap fluid particles and dampen combustion vibration, stabilizing NOx reduction across frequency ranges.

Cross key connectors isolate metal fasteners in blind holes away from the combustion zone, preserving ceramic liner strength at high temperatures.

A wedge-shaped ceramic heat shield element redirects hot gas flow using its spoiler geometry to protect the supporting structure.

Counterbalance guide system transports heavy gas turbine transition pieces, reducing manual labor and safety risks during installation.

A single-piece combustor casing component reduces assembly time and enhances aerodynamic efficiency through additive manufacturing.

Nested plenums with distinct volumes adjust fuel distribution ratios to mitigate high-frequency resonance in hydrogen combustion.

An opening in the penetrating part creates a downstream cooling air film, preventing hot spots and extending wall lifespan without extra manufacturing steps.

Effusion cooling reduces thermal stress on the cap plate while pre-mixing the coolant with fuel to lower NOx emissions.

Protruding connecting ribs increase outer wall surface area within the annular space, reducing thermal stress and extending service life.

Circumferentially elongated swirler exits reshape conical flames to prevent liner touchdown and extend combustor service life.

A pilot fuel injector system uses a perforated plate and radial fuel pegs to mix air and fuel uniformly.

Threaded swirler mount prevents axial displacement without blocking cooling holes, reducing repair complexity.

An intermediate connecting element absorbs thermomechanical expansion differentials between ceramic and metal parts, reducing stress-induced breakage.

Nesting cellular parts in a single radial plane prevents slit distortion from welding, maintaining air flow integrity.

Segmented swivel and sliding pins reduce machining complexity and wear while maintaining precise clearance control.

A continuous combustion liner merges conical and transition sections to eliminate joint leakage paths in gas turbine combustors.

Axial fuel staging injector directs transverse fuel streams for thorough air mixing across combustion zones to reduce emissions.

A hemispherical dome assembly directs fuel-air mixtures through coaxial passageways to regulate flow velocity entering the combustion liner.

Segmented V-shaped gutters with side through-holes reduce pressure loss from high-velocity mixing while maintaining reliable flame stabilization.

A brazed joint uses a low melting point bonding material to attach a flange to gas turbine engine segments.

Spring-biased adaptor assembly protects igniters from thermal damage while enabling quick removal.

A volute wall defines a combustion chamber and flow passages segregate fuel flows to create a trapped vortex that stabilizes the primary zone.

Distinct alloy selection for the flange and premix tube shifts natural frequencies away from rotor speeds, preventing resonance stress concentrations.

A deformable fastener assembly manages thermal expansion in gas turbine engines through controlled deflection.

Partitioned internal channels prevent air-fuel mixture dilution between perforated plates, ensuring stable combustion and reduced NOx emissions.

Curved liner panel rails seat into a support shell furrow to eliminate dead regions and improve gas turbine engine durability.

Recycles gas turbine exhaust through a boiler to increase carbon dioxide concentration, reducing separation apparatus volume and power consumption.

Intermediary spring elements accommodate thermal expansion differences between materials, preventing localized contact stress damage.

Undulating trailing edge reduces pressure loss while maintaining vortex strength for efficient gas turbine fuel mixing.

A non-wetting coating prevents molten silicon from forming surface nodules on ceramic matrix composites.

Staggered air feed holes in the inner fastening flange disrupt vibration harmonics, preventing resonant breakage while maintaining cooling.

Dome wall cooling holes and air tubes extend service life and improve combustion efficiency by resolving structural complexity trade-offs.

An effusion cooled baffle reduces NOx emissions by splitting the flame into two zones, lowering peak temperatures while maintaining turbine inlet temperature.

Segmented swirler tubes rotate fuel and oxidizer streams to ensure rapid mixing, reducing residence time in low-oxygen combustors.

Targeted cooling passages purge internal cavities and reduce NOx emissions by minimizing excessive air consumption.

Replacing mechanical combustion with electromagnetic induction improves energy efficiency and adaptability across diverse transportation systems.

Segmented heat shields reduce hoop and vibration stresses on gas turbine engine manifolds, enabling easier repair and minimizing material waste.

An ELBO fuel circuit supplies supplemental fuel to stabilize combustion acoustics.

A gas turbine controller adjusts fuel flow proportions between supply means to optimize combustion parameters.

A gas turbine control system calculates exhaust temperature using compressor discharge and turbine exhaust pressure to maintain an optimal operating point.

A pneumatically actuated flow modulator aligns concentric tube apertures to control air entry into fuel nozzles.

Bolted annular segments form a double-wall combustion chamber, reducing manufacturing lead times and costs.

Segmenting the pre-mixer into planar and swirler zones reduces NOx emissions while maintaining gas turbine efficiency.