Continuous Combustion Chamber TRIZ Cases

Vent air sweeps fuel from vane surfaces to prevent auto-ignition and flame holding, enhancing reliability while maintaining manageable device complexity.

Varying lance tip positions in conical mixing devices damp pressure oscillations without requiring differential fuel control or temperature adjustments.

Orifice-induced pressure drop stabilizes flame and suppresses combustion oscillation while air hole plate swirl flow reduces NOx emissions.

A modular inlet transition section reshapes circular flow into polygonal geometry while maintaining constant cross-sectional area.

A fuel nozzle uses a sliding heat shield tube to accommodate thermal expansion while maintaining structural integrity.

Increasing outside diameter of premixing fuel nozzle root portion resists oscillation stress and prevents downstream scattering of broken pieces.

Segmented cooling injectors reduce temperature differentials and deformation risks in gas turbine combustor deflectors.

Segmented galleries in the housing manage varying heating values, maintaining combustion stability while reducing emissions from diverse gas fuels.

Segmented cooling nozzles minimize shear mixing and pressure loss by accelerating air via a convergent-divergent outlet for improved turbine efficiency.

Tapered cooling channels increase fluid velocity along the flow path, compensating for rising air temperature to sustain consistent cooling effectiveness.

Multi-axis pigtail assemblies reduce cross-threading and O-ring damage during installation of circumferentially distributed fuel injectors.

Dual cavity hollow plank combustor liner reduces hoop stress and damps combustion dynamic frequencies via frequency-tuned thermo-acoustic damping.

Segmented swirlers create intense mixing regions to reduce NOx emissions during high power conditions.

A segmented fuel injector design directs hydrogen-based primary fuel downstream of the swirler exit plane to anchor the flame and improve mixing efficiency.

Transition duct exit frame inserts use materials with different coefficients of thermal expansion to reduce structural distortion.

Segmented fuel supply prevents coke oven gas clogging in pilot nozzles by isolating impurities from the main combustion path.

An ablative vanishment section on a jet engine flame stabilizer adapts shape during flight to prevent inlet countercurrent flow and maintain stable combustion.

A controller cycles a fuel injector valve to dampen pressure oscillations, uncoupling heat release from harmful combustion instabilities.

Effusion holes and backside pin fins direct cooling air through the liner wall, reducing consumption while maintaining high-temperature survivability.

An annular convection plate delimits a stable air flow stream along the internal wall of a combustion chamber.

A sliding joint with a flexible arm and spacer absorbs thermal expansion between the combustor duct and turbine vane assembly.

Premixed pilot devices inject fuel gas into turbulent air streams to stabilize the main central flame in a convergent combustion chamber.

A combustor nozzle uses fluid vortex generators to swirl compressed air for thorough hydrogen fuel mixing.

A burner lance uses a pin and bayonet coupling to maintain nozzle alignment under thermal stress.

A reinforcing pad outside the flowpath distributes torque forces to reduce ring-strut-ring thermal fighting in a gas turbine engine.

Swage-joining a rivet fixes the nozzle guide support to an open flange, eliminating welding costs and preventing unlimited rotation.

A gas turbine combustor redirects air flow via a change member to position the flame surface, resolving combustion stability and flashback risks.

A combustion chamber segment uses a groove and hook interface to attach securely to a downstream ring structure.

Additively manufactured combustor body uses distinct materials for axial fuel stage immersed injectors to reduce part count by seventy percent.

Segmented nozzle design mixes fuel and air through primary and secondary channels, reducing hot spots and pressure drop in gas turbines.

An arcuate split-ring heatshield minimizes heat conduction to the diffuser case, reducing thermal stress and extending component operational life.

Inclined wedge spacer replaces threaded holes in vane carrier, reducing wear and maintenance time.

Adjusting circumferential air blowhole spacing prevents flame interference and reduces nitrogen oxides emissions while maintaining combustor reliability.

A convex profile liner assembly accelerates gas flow through a controlled area ratio, reducing NOx and CO emissions while maintaining engine performance.

An integrated combustor vane reduces nitrogen oxide emissions by stabilizing the combustion zone and controlling exit temperature profiles.

Rail grooves capture leakage air to form a mid-region passage, reducing coolant usage while maintaining heat shield durability.

Merging separate tiles into a single annular component eliminates air leaks through joints, restoring combustion efficiency in gas turbine engines.

Alternating injection outlets in the turbine nozzle surface optimize residence time to resolve incomplete combustion reactions.

Segmented fuel openings create staged mixing zones that prevent vortex breakdown and reduce carbon monoxide emissions.

Dilution slots and a fence structure increase turbulence to mix cooling air with combustion gases, reducing NOx emissions.

Integrates a resonator volume into the combustor transition side wall to suppress thermo acoustic pulsations via Helmholtz resonance.

Nested inner and outer liners with protrusions create a cooling chamber that reduces nozzle temperature without increasing structural complexity.

Segmented brackets with flexible bushings manage differential thermal growth between metal domes and ceramic liners, reducing attachment complexity.

Slanted outlet fins redirect cooling air to prevent stagnation and hot spots, maintaining high turbine inlet temperatures.

Inner and outer injectors create distinct swirl flows that optimize flame temperature and strain rates, reducing NOx formation by 2.5 to 5 times.

Struts in a reconfigured transition duct guide compressed air along the combustion liner, eliminating cross-flow interactions and reducing pressure drop.

A bond layer containing silicon and a boria stabilizing agent prevents boria migration and reduces silica scale viscosity, resolving coating adhesion issues.

Embedded imaging markers in a turbine composite assembly allow X-ray or ultrasound verification of fiber orientation, eliminating destructive testing waste.