Continuous Combustion Chamber TRIZ Cases

Opposing axial channels and film holes divert air flow to enhance heat transfer, resolving insufficient cooling effectiveness under all operating conditions.

A radial turbine delivers fuel through internal cooling passages to the combustor inlet using centrifugal force.

An angled cone and guide vanes redirect rearward radar reflections to enhance aircraft stealth capabilities.

Segmented film-cooling channels with vortex chambers reduce coolant flow requirements while improving thermal insulation performance.

Segmented diffuser airfoils capture sand and dirt via adhesion, preventing combustor blockages while maintaining smooth airflow.

Self-sustaining gas turbine combusts ammonia using in-situ cracked hydrogen, eliminating external storage costs and safety risks.

C-shaped pedestals direct cooling fluid through tortuous paths to enhance convective heat transfer in gas turbine components.

Coating turbine blades with catalyst reduces nitrogen oxide emissions while maintaining thrust efficiency.

Wipe passages direct air along the premix tube inner surface to prevent fuel accumulation and coking in gas turbine injectors.

Radial ports invert axial swirl to stabilize combustion and reduce emissions.

A fuel nozzle assembly distributes combustion fuel through an intermediate duct structure within a gas turbine engine.

Film cooling via gap openings protects support elements from hot gas exposure without raising NOx emissions.

Differentiated aluminum content in coating layers resolves thermo-mechanical fatigue and oxidation resistance trade-offs.

An integrated combustor nozzle merges fuel injection and turbine sections into a seamless structure.

Segmented combustor outlets with varied orientation angles suppress high-temperature gas intrusion through axial gaps, reducing cooling medium requirements.

A fuel injector splitter features nested divergent surfaces forming internal cavities with fluid openings for directed airflow.

A bled diffuser directs compressor air to a secondary combustion system for mixing with fuel.

Segmented burner head plates apply localized impingement cooling to reduce thermal wear while maintaining combustion stability.

Segmented fuel nozzle groups adjust mixing ratios to stabilize flame generation, reducing combustion vibrations during ramp-up.

Scalloped slots in the front heat shield redirect impingement cooling jets to cool hot spots on dome lips, reducing thermal mechanical fatigue.

A control device adjusts fuel flow rates and valve openings to stabilize combustion in gas turbines.

Integrated rib cooling channels dissipate heat from gas turbine housings, reducing thermal stress and preventing material cracking.

Segmented cooling circuits within the hot gas path component reduce thermal expansion mismatch, extending component lifetime at higher firing temperatures.

Additive manufacturing creates integral voids in fuel injectors to inhibit heat transfer from airflow, reducing coking and simplifying production.

Staged combustion control reduces CO emissions during part-load operation by adjusting active burners and guide vanes to maintain optimal air-to-fuel ratios.

Selective corner radius variation in a fuel nozzle sheath reduces stress concentrations, preventing deformations and fretting damage.

Logarithmic spiral swirl vanes decouple inclination and stacking angles, reducing additive manufacturing costs while improving fuel atomization.

A fuel injector design with paired bodies and struts creates discrete outlet flow paths to enhance radial mixing of fuel and air.

Segmented shroud sections with varying curvature radii prevent flow separation and pressure loss in gas turbine combustors.

Inclined main nozzles extend the fuel-air mixing path to resolve poor combustion uniformity and reduce harmful emissions.

A combustion chamber monitoring method calculates cumulative fatigue damage from pressure oscillation data to estimate residual service life.

A combustion chamber shingle features a curved edge with distinct geometry to maintain secure abutment against the wall.

Axial helical conduits accommodate thermal expansion stress on rigid distribution arms, ensuring uniform fluid dispersion and maintaining system reliability.

Hollow elements in a combustor cooling chamber act as Helmholtz dampers to stabilize pressure.

Dual pipe cross fire tube assembly guides combustion air through openings to cool the outer tube wall.

Embedded lobes in the diffusion section minimize vortex formation, allowing cooling air to remain on the outer skin for extended duration.

A spacer fixed to inner and outer ducts maintains coaxial nozzle alignment despite thermal expansion, preventing axis shifting.

Helical vanes create a spiral flow path that mixes combustion products with cooling air, reducing thermal stresses and improving temperature uniformity.

Radial projection parts guide compressed air inward to reduce thermal stress on flanges joining the combustor and turbine casings.

An arcuate liner panel eliminates dead regions and adverse aerodynamics at interfaces, enhancing combustor durability and operational efficiency.

Chamfer or countersink enlargements reduce entrance-edge sensitivity to stabilize fluid flow and increase discharge coefficients.

Effusion holes in combustion liners channel cooling air from outer channels to inner walls, bypassing obstructed areas behind seals and baffles.

Primary and secondary nozzles stage fuel injection to control combustion gas temperatures, reducing nitrous oxide emissions while maintaining power output.

Helmholtz resonator liners suppress unwanted acoustic modes to maintain high power density and pressure gain combustion.

Segmented fuel nozzles with periodic actuation desynchronize combustion events, reducing pressure oscillations that damage engine parts.

A fuel injector premixer and distributor deliver staged fuel flow through multiple orifices to accommodate varying fuel compositions.