Continuous Combustion Chamber TRIZ Cases

Segmented circuits and a shroud stabilize a recirculation zone, resolving the conflict between fuel-air mixing efficiency and ignition reliability.

Segmented annular combustor volumes apply rich burn, quick quench, lean burn strategies to reduce NOx emissions while maintaining combustion efficiency.

Fuel blending prevents syngas combustor flashback by lowering reactivity while maintaining dry-low NOx emission control without added system complexity.

Radial air deflection in the introducing passage creates uniform pre-mixed gas, reducing NOx emissions without increasing combustor size.

A conjoined grommet assembly defines primary and wake dilution holes with closer centerpoint distances to enhance air penetration.

Porous injectors dampen pressure fluctuations and reduce mechanical stress while maintaining stable fluid distribution across varying mass flows.

Non-uniformly distributed cooling apertures in quench aperture bodies reduce thermal stresses by directing air via radial, tangential, and acute angled paths.

Impingement holes aligned with protuberances on a combustor dome heat shield enhance heat transfer while reducing coolant usage and emissions.

Positioning panels at specific angles directs vapor clouds onto hole edges, preventing oxidation distress from inadequate thickness.

A combustor bypass valve diverts core airflow around the gas turbine combustor, stabilizing operation against variable turbine flow area changes.

Deep-hole bores in the burner support tube supply fuel to separate pilot stages, expanding operational corridors and reducing emissions.

Integrating a flowpath heat exchanger into the compressor section reduces airflow temperature, increasing pressure ratio and operational efficiency.

Concentric premixing tubes with protruding fuel holes reduce pressure loss differences to ensure uniform fuel-air mixing in the plenum.

Curved baffles generate vortex rings in stator vanes to boost heat transfer while minimizing pressure loss.

Microwave reflection analysis replaces bulky optical sensors to resolve high-temperature reliability issues in gas turbine engine monitoring.

A gas turbine combustor uses axial and radial fuel injection systems to create distinct combustion zones.

Rail-based guide jigs stabilize combustor transition pieces, reducing worker load and device complexity during detachment.

A ceramic matrix composite insert sits between the heat shield panel and support shell to provide localized thermal protection at critical hot spots.

A fuel supply rail integrates an annular circulation portion within the dynamic seal to cool the injection wheel interface.

A hot-gas-generating apparatus uses electrolytic decomposition of anhydrous ionic propellants between integrated electrodes to initiate combustion.

Optical imaging detects combustion anomalies like absent flames or improper temperatures, allowing automated fuel flow corrections.

Radial injection aligns fuel with redirected air, preventing wall deposition and reducing NOx emissions.

A combustor bell-mouth inlet stabilizes compressed air flow through a semicircular cross-section, eliminating vortex formation and pressure loss.

Offset herringbone filmhole pattern directs cooling air across turbine surfaces to enhance convective heat transfer.

Wider tie piece recesses reduce displacement stress from thermal expansion, mitigating fatigue damage at welded portions.

Additive manufactured manifold tubes merge separate fuel circuits into a single body, enabling conduction heat transfer that prevents coking and reduces weight.

Segmented seal body accommodates relative movement between nozzle guide vane and rear inner discharge nozzle, reducing surface-to-surface wear.

Angled apertures discharge diffusion flow to cool diffusion tips, preventing soot deposits and reducing thermal stress concentrations.

A gas turbine control system modulates fuel division to deliver richer mixtures for cross-fire reignition of extinguished combustion cans.

A lobed mixer fuel injector routes alternate fuels radially outward to improve air-fuel mixing uniformity in gas turbines.

Cold spray deposition forms dense MAXMET composite coatings using kinetic energy to bond MAX phase particles and metal without melting.

Segmented resilient metallic seals accommodate thermal gradients in multi-tube fuel nozzles, mitigating stress concentration and extending operational lifespan.

Shielding air flows delay reactant ignition to reduce NOx emissions while reusing cooling air for efficient combustion.

A double-wall combustor wall assembly uses a metallic outer shell and ceramic inner panels connected by a flexible damper.

Axially staged gas turbine combustor premixer mixes fuel and air with swirl to minimize NOx and CO emissions.

A combustor dome heat shield uses radially extending lips with fins to maximize cooling surface area via impingement jets.

Segmented zones with orthogonal impingement and effusion holes optimize cooling air distribution, resolving random placement inefficiencies.

Impingement slots and triangular slot tabs direct lateral airflow across heat shield panels to enhance convective cooling.

A dry low NOx combustor injects water into fuel streams to minimize visible emissions.

Conditioned air flows through rotor drum webs to regulate temperature distribution, reducing thermal stresses and extending component lifespan.

Side wall extension decouples thermo acoustic pulsations between adjacent can combustors without adding bulky dampers or compromising emission performance.

Laser additive deposition applies high-strength alloy to fuel injector surfaces, resolving the trade-off between mechanical strength and component weight.

Segmented baffles with cooling holes direct airflow to reduce internal stresses, allowing independent thermal expansion of airfoil components.

Metallic mount extensions couple ceramic matrix composite turbine vanes to support structures for direct load transmission.

A transition duct with a late injection ring shifts hot gas flow radially and tangentially to eliminate first stage nozzles.

A plug assembly with a collar bypass passage redirects cooling air around obstructions in internal circuits.

Inclined retaining arms maintain natural air inclination to eliminate aerodynamic force losses.

Annular slot circulates cooling gas to reduce heat transfer, preventing hot gas penetration and maintaining lower component temperatures.

Segmented fuel injector assembly reduces nitrogen oxide and soot emissions by switching between non-premixed and premixed combustion modes.

Segmented plies tailor local mechanical and thermal conductivity to manage stress gradients and prevent crack growth in high-temperature turbine components.