Continuous Combustion Chamber TRIZ Cases

A gas turbine rib end features a curved transition portion near the wall connection to distribute structural loads.

Guide members redirect compressed air toward the transition piece casing, preventing thermal deformation from high-temperature combustion gases.

An intermediate tube routes pilot air and fuel through a compact center body, resolving space restrictions that limit passage routing effectiveness.

Selective laser melting builds complex tube sections onto machined elements, resolving alignment precision trade-offs in hybrid manufacturing.

Segmented ceramic walls absorb thermal expansion differences via elastic bridges, reducing manufacturing complexity.

Integral ceramic matrix composite chute directs mixing air toward the chamber midline, eliminating attachment variability and improving combustion efficiency.

A gas turbine combustor introduces inert nitrogen into the premix chamber boundary layer to purge combustible mixtures and prevent flame flashback.

An integrated grommet design creates an annular cooling channel to manage combustion gas temperature profiles and protect turbine sections from overheating.

Multi-cornered film cooling slots in a combustor liner lower cooling air needs, improving fuel efficiency while preventing nitrogen oxide formation.

Radial boss extensions on the annular fairing create air intake scoops that reduce pressure drop and prevent flow detachment near injection devices.

A combustion arrangement uses a partitioning wall and valve to damp pressure oscillations.

Aligning the fuel injector, liner mount, and crossfire tube along a common axial axis minimizes wake turbulence between the combustion liner and flow sleeve.

A dome deflector uses a snap-fit connection to accommodate thermal expansion in gas turbine combustors.

Purge air ejected from the nozzle center shields oil fuel from high-temperature compressed air, reducing heat influence while maintaining combustion stability.

Curved guide surfaces redirect airflow to minimize swirl generation and pressure loss while stabilizing fuel pegs against vibration.

A fuel dome with cooling openings and a deflector directs air to form a protective film on the combustor liner.

Purge air flows through a notch introduction hole to prevent combustion gas accumulation and unwanted flame generation near connecting pipes.

Segmented annular diffuser partitions reduce wetted-perimeter length, minimizing friction loss while maintaining static pressure recovery.

Radial flow splitters guide compressed air through diverging side walls, eliminating strut-induced distortion and optimizing combustor gas distribution.

Deformable tabs engage ledges to prevent nozzle separation, enabling repair without replacing the entire fuel injector assembly.

Closed volumes coupled through flow restrictors break the combustor feedback loop, reducing fuel-coupled acoustics without adding engine weight.

Integrated air tube structure uses additive manufacturing to resolve thermal stress and consistency contradictions in gas turbine combustors.

Chamfered combustor dome apertures direct cooling air along inner surfaces, reducing manufacturing cost and structural deformation risk.

Impingement cooling reduces thermal stresses on quench aperture grommets and heat shields, preventing material degradation.

Glass modifier dopants in the intermediate layer inhibit thermally grown oxide crystallization, preventing spallation and extending component lifespan.

A sleeve assembly uses a unisleeve and flow sleeve to create a cooling duct between the liner and shell.

Optimized cooling hole orientation and passage area maintain sub-0.50 flow speed ratios, preventing dust accumulation from turbulence.

Segmenting fuel injection into primary and secondary nozzles expands flow range while maintaining spray stability.

Segmented swirl vane fuel injection maintains high local fuel-air ratios during partial load, suppressing CO and UHC emissions.

A mixing assembly uses axial fuel injection ports to discharge fuel into the central annular channel for improved atomization.

A turbomachine injection nozzle channels coolant along its exterior wall and around fluid delivery tubes to manage thermal loads.

A swirl-stabilized pilot burner combustor disperses combustion gases into a main chamber to generate internal flow rotation.

Boomerang film cooling holes diffuse air laterally to increase surface coverage while reducing flow separation risks.

Inlet plate projections disrupt airflow to enhance fuel-air mixing, avoiding increased nozzle weight and engine stress from longer tubes.

Radial and axial walls form a labyrinth seal that controls leakage and reduces combustion emissions by limiting flow variation.

Staggered angled openings in the combustion chamber duct reduce flow rate coefficient, ensuring reliable ignition during windmilling with minimal cooling air.

Radial edge extension tubes shape premix gas flow to suppress low velocity regions and prevent flashback in gas turbine combustors.

Serpentine sealing rails extend the coolant path to reduce air leakage and improve combustion efficiency.

Segmented ceramic walls with overlapping edges enable controlled cooling air passage in annular combustion chambers.

A sloped impingement surface diverts cooling air flow to reduce dirt accumulation and maintain heat transfer efficiency.

Diffuser holes in the injector tube introduce fuel into a vortex flow, stabilizing combustion and reducing NOx emissions in lean premixed burners.

Integrated retainer cooling holes channel airflow to the combustor dome, mitigating high temperature degradation while maintaining combustion efficiency.

Multiple resonance chambers with matched peak frequencies suppress high-temperature gas backflow and minimize NOx production in gas turbine combustors.

A bulged isolator design stabilizes shocks and facilitates flow mixing, reducing distortion to prevent engine stall in supersonic air breathing engines.

Varying hole densities and backside projections reduce temperature gradients while minimizing cooling air usage in jet engine combustors.

Distinct forward and aft vane angles in a combustor swirler decouple purge jets from primary flow, reducing autoignition risks.

Reducing the downstream diffusion angle in a gas turbine cooling hole improves film coverage while maintaining edge integrity.

A fuel-air premixer uses counter-swirling airflows to generate a turbulent mixing layer for efficient vaporization.

Adjusting nozzle-to-transition piece distances suppresses wake flow edge tones while maintaining aerodynamic efficiency.

Turbulators on combustion liners reduce melting risk by enhancing heat transfer via specific ramp angles and spacing.