Continuous Combustion Chamber TRIZ Cases

A fuel nozzle manifold integrates circumferentially separated flow channels within a thick-walled stem to simplify fluid distribution.

Segmented seal assembly uses a main spring to load a shield member against turbine vanes, resolving plastic deformation risks in existing designs.

Quench air jets cool combustion gases downstream from the primary zone to minimize high temperatures that generate NOx emissions.

A knitted metal wire mesh evaporator body distributes liquid fuel through controlled porosity and thermal conductivity.

An aluminum nitride interlayer bonds a silicon carbide ceramic matrix composite to an aluminosilicate anticorrosion coating.

Resonator housing design positions exhaust orifices near maximum temperature areas to reduce thermal gradients while minimizing cracking risks.

Tapered pins with contoured sections guide bundled tubes into cap plate apertures, resolving time-consuming manual alignment challenges.

Segmented injectors in this pintle-swirl device prevent high-temperature gas recirculation, protecting the tip while optimizing the fuel mixture ratio.

A fuel injector joint employs a rotatable adaptor to align with thermal expansion axes, enabling field repair without compromising structural integrity.

A gas turbine combustor ignition improving part reduces the low-temperature air layer between pilot and premixed flames.

Direct surface contact coupling between cold and hot shells enables relative movement in gas turbine can combustors.

Capillary-driven wicking structures direct molten braze to precise joints, preventing alloy plugging of narrow nozzle passages.

A spring-loaded crossover tube assembly connects turbine engine cans using a wave spring biasing member to allow collinear movement.

Segmented injectors create lean mixtures upstream and stable combustion downstream, reducing NOx emissions while maintaining engine efficiency.

Integrally cast ceramic matrix composite combustor dome and liners eliminate seams, reducing attachment complexity while maintaining uniform thermal expansion.

Sol infiltration bonds splat interfaces in a first ceramic layer before depositing a second dense layer, reducing thermal stresses on gas turbine components.

Flow management device modifies annulus areas to ensure uniform fuel/air mixture composition and reduce nitrogen oxide production.

A method defines modified safety zones around primary holes to virtually remove and reintegrate multi-perforations for optimized hole distribution.

Dynamic frequency adjustment attenuates shifting acoustic resonance, stabilizing combustion and reducing emissions.

Cone-shaped pin augmentors increase surface area and promote turbulence to enhance heat transfer on combustor liner panels.

Segmented liner panels with radial and axial supports accommodate thermal expansion, preventing buckling and enabling independent segment replacement.

Segmented pins in a slideable anchoring assembly reduce installation clearance requirements while maintaining robust thermal expansion accommodation.

Coaxial dual swirler nozzle with inner and outer vanes creates turbulent flow for improved fuel-air mixing.

Increasing outer port discharge coefficients compensates for pressure loss from fuel injector wakes, optimizing air flow and thermal profiles.

Reverse passages deflect mixed gas flow by 180 degrees inside the mixing chamber, ensuring uniform concentration distribution to reduce NOx emissions.

Flow management device adjusts annulus area sizes to distribute airflow uniformly through perforated plates, reducing component wear and vibration.

A metering plate with precise orifices meters airflow and fuel flow to restore original parameters without complex welding repairs.

A detachable metal bracket connects ceramic matrix composites to metallic engine components using rivets and pins.

A nozzle air jet section jets high-speed air from the tip to increase flow velocity and reduce fuel concentration.

Circumferential abutments limit radial tab displacement to reduce collar wear and improve centring reliability.

Segmented angled cooling passages maintain double-vortex structures to improve thermal performance while mitigating adverse emissions impacts.

A non-uniform thermal coating on ceramic matrix composite substrates regulates heat transfer across engine hot gas path components.

Connecting conduit couples perpendicularly to fluid passage to attenuate pressure oscillations in gas turbine engines.

Segmented fuel conveying members merge sealing functions into single joints, reducing leakage risk while maintaining structural integrity.

A compliant metal layer reduces wear at the ceramic matrix composite interface by accommodating surface asperities.

A pipe-shaped member with heat-resistant glass and cooling maintains component temperature at 400°C for stable ignition under high-pressure conditions.

Segmented internal cooling passage directs fluid through distinct zones to cool turbine airfoils.

CMAS traps capture particulate contaminants from intake air to prevent coating recession and extend component life at high temperatures.

Segmented vortex and impingement cooling suppresses pressure loss while improving reliability.

Spring washers compensate for thermal expansion differences between ceramic matrix composite arms and metal casings, reducing stress generation.

Differentiating combustor cap axial lengths decouples instability frequencies, reducing constructive interference and extending component operating life.

Segmented sheet metal shields interlock liner flanges to ease assembly while providing thermal protection and air cooling channels.

Varying combustor fuel port axial distances breaks acoustic coherence and reduces modal coupling in gas turbine arrays.

Differentiated positioning of small and large diameter dilution holes prevents hot spots on combustion chamber walls while maintaining mechanical strength.

Segmented effusion cooling apertures reduce coolant jet velocity to prevent surface detachment and improve heat transfer uniformity.

Radially positions the compressor inward from the combustor to shorten axial engine length while using compressed air for vane cooling.

Threaded swirler mount interface with circumferential tabs snaps over bulkhead ramps, eliminating bolt-and-nut arrangements that block cooling holes.

Pilot diffusion flames damp pressure and thermal pulsations during gas turbine fuel switching, preventing damage from harmful oscillations.