Continuous Combustion Chamber TRIZ Cases

A jet engine fuel injector uses a self-extinguishing member to modify fuel injection direction based on flight time.

Feedback controller modulates shaker power to offset combustion dynamics vibrations, reducing high cycle fatigue.

A contoured shroud accelerates fuel-air mixing in a pre-swirling injector assembly.

Staged tangential fuel-air nozzles direct combustion reactants to enhance mixing and reduce peak flame temperatures in gas turbine engines.

Solenoid valves control pilot and mains fuel stages in a gas turbine combustor to replace complex active valve arrangements.

Fuel-air mixing tubes channel premixed fuel and air into a secondary combustion zone, lowering peak temperatures to reduce nitrogen oxide emissions.

Fastener coupling replaces welding on bundled tube fuel injector shrouds, enabling non-destructive pre-mix tube inspection and repair.

Asymmetric fuel injector housing shapes guide compressed air flow to reduce hotspots and improve combustion efficiency in reverse flow annular combustors.

A dual fuel gas turbine combustor burner with a swiveling flow path and alternately formed holes for stable flame holding.

A mixer assembly vane flow path incorporates a fluid diode to dampen swirler tone frequencies and mass flowrate oscillations in a turbine engine combustor.

Segmented zones in the pre-mixing apparatus manage flame propagation, reducing auto-ignition risks while controlling NOx emissions.

Segmented air supply paths using cooled, pressurized air from a sub-compressor suppress flashback and reduce NOx generation during high-temperature operation.

A fuel nozzle uses swirler vanes and a downstream injection peg to create a uniform flow field.

Annular combustor with shaped walls creates a Venturi effect to accelerate combustion gases and increase mass flow through the turbine.

Segmented impingement and serpentine channels cool combustor walls while reducing pressure drop, increasing gas turbine power output.

Heat shield member with offset dilution passages directs cooling airflow through a flow region to thermally decouple the transition piece wall.

Circumferential fuel distribution manifold routes supply lines around the outer casing, reducing physical footprint and flow disruption.

Alternating cooling ducts deliver homogeneous temperature distribution across the span extent while maintaining low coolant pressure drop.

Staggered spray rings distribute fluid to reduce thermal gradients and ensure comprehensive blade coverage in gas turbine compressors.

Removable fasteners secure circumferential combustion chamber segments to upstream and downstream ring structures for modular assembly.

A fuel injector assembly uses a cooling tube to direct airflow around the stem.

Flexible dome-deflector joints absorb thermal expansion and vibration to reduce stress on connections, enhancing combustor durability under intense heat.

Metallic swirler mounts to a pseudo-dome structure that interfaces with a ceramic matrix composite dome.

A perforated cupped mixer combines high-pressure and conditioned airflows within a diffuser assembly mixing chamber.

Convex and concave arcuate surfaces in the metering section reduce flow separation and hot gas entrainment at high blowing ratios.

A quaternary fuel circuit controls volumetric flow of ultra low calorific fuels through a secondary path.

Effusion apertures direct cooling air to form a protective blanket on the heat shield, reducing thermal stresses near quench apertures.

A control device calculates preselected fuel split using combustion chamber exit temperature and turbine input temperature.

An aerodynamic wake reducer redirects airflow around obstructing structures to minimize downstream turbulence.

A pilot injector establishes a recirculation zone to anchor the flame and increase residence time.

Integrates pin array extensions with structural protrusions to maintain precise cooling pin separation distances on float wall combustor panels.

Angled rails on adjacent combustor panels minimize circumferential gaps to restrict hot gas flow.

Biased radial fuel distribution enriches specific combustor zones, stabilizing flame holding while reducing nitrogen oxide emissions.

A turbomachine component uses a monolithic lattice structure to guide cooling fluid through internal voids for effective heat dissipation.

Vertical feed arm stacking and radial heat shielding reduce manifold complexity while preventing fuel breakdown from combustor heat.

A fuel feed strip shaped in a bow configuration increases natural frequency and axial flexibility without adding structural mass.

Splash plate atomizes fuel through hydraulic mixing to resolve low efficiency from simple nozzle structures.

Circumferential fuel injection and swirling flow increase residence time, resolving the trade-off between combustor complexity and combustion efficiency.

Axial air circulation flushes the cylindrical passage between the coaxial ring and bush, preventing coke formation that interferes with spark igniter guidance.

A porous surface slurry layer acts as a wick to transport molten material across ceramic preform surfaces, reducing infiltration time for complex geometries.

Biased circumferential fuel distribution via a segmented radial injection system mitigates combustion instabilities and reduces NOx emissions.

Turbulent flow promoting portions disturb crossflow to raise the heat transfer coefficient, resolving efficiency loss from gas swept into crossflow.

Segmented combustor liner planks replace monolithic designs to cut weight by 20 percent and extend life beyond 20,000 cycles.

Strategic sealing gas openings create an aerodynamic shield that deflects grazing flow, preventing interference with the damper's bias flow.

Polygonal external piping prevents oil coking by relocating the fuel chamber outside the high-temperature nozzle base.

Positioning members center a unitary flow path assembly, accommodating thermal expansion differences between ceramic matrix composite and metallic materials.

Counter-rotating swirler vanes eliminate recirculation zones to reduce NOx emissions and prevent auto-ignition in gas turbine combustors.

Drawing air from an intermediate compressor stage maintains pressure matching with exhaust gases, reducing turbine efficiency losses and NOx emissions.

Segmented spray bars with cooperative airflow streams improve fuel penetration and dispersion without increasing engine weight.

Positioning the igniter upstream protects it from extreme temperatures while an air passage conveys the spark into the combustion chamber for reliable ignition.