Continuous Combustion Chamber TRIZ Cases

Segmented inner cooling shrouds reduce combustor liner vibrations and accommodate thermal expansion via staggered fastening rows.

Injected ammonia burns to create cooler combustion gas that flows through the deflection member, preventing thermal deformation and cracking.

An air flow guide cap with an inclined upper surface directs cooling air into combustion duct holes.

Obstruction elements split airflow into multiple channels within swirler slots to induce turbulence and improve fuel dispersion.

A fuel injector system uses a mechanically angled pintle to control atomization across varying operating conditions.

A burner system oxidizer fuel supply arrangement adjusts fresh gas proportions via pressure ratios to maintain stable combustion velocities.

Integrally cast fuel manifold eliminates stress risers to extend nozzle service life against corrosion cracking.

A combustor aft mount assembly uses an inner diameter mounting bracket with circumferentially extending bolting wings to secure the engine component.

Inner diameter support for the dividing guide body increases arrangement flexibility and reduces pressure loss.

Segmenting ignition into a torch pilot and laser source lowers laser output, preventing pressure-resistant glass damage in supercritical CO2 turbines.

Fluid diodes in a walled annular combustion chamber create rotating regions matching detonation wave speed, reducing backflow and improving pressure gain.

A baffle apparatus attached to a gas generator case creates passages that increase air flow velocity over the combustor.

Staged filters capture coke particles from heated fuel, preventing nozzle blockage and extending component lifespan in gas turbine engines.

A tubular combustor basket features a leading end with radially varying circumferential positions to generate flow vortices.

Image comparison detects combustion instabilities like flashback, allowing corrective actions that prevent component damage.

Guide vanes segment the expansion chamber to reduce pressure loss and air velocity, improving thermal efficiency in compact micro turbines.

Segmented nozzle outlets increase premixing surface area, resolving poor jet-root mixing and long burnout zones in gas turbines.

Segmented jacket plates enable double-sided rib welding, reducing crack growth under high pressure.

Axially spaced downstream injectors minimize reactant residence time in the combustion zone, reducing NOx emissions while maintaining high firing temperatures.

Curved fairings redirect airflow parallel to combustor surfaces, preventing separation and particulate buildup that reduces cooling efficiency.

Radial air jets from a bowed coolant channel shield combustor components from excessive heat while maintaining mechanical integrity.

Segmenting the flowpath into distinct zones reduces manufacturing complexity while maintaining atomization performance.

Aperture body directs cooling air through inlet and outlet passages to impinge against a cavity surface, reducing thermal stress in turbine engine combustors.

Dynamic pressure sensors monitor combustion chamber oscillations to identify specific burner locations through frequency spectrum analysis.

A premixer tube uses a non-circular cross-section to enhance fuel and air mixing efficiency.

Surface projections increase liquid contact angle to suspend droplets on cooling components.

A pre-diffuser ring-strut structure with hollow struts manages airflow diffusion and structural alignment.

Adjustable fuel injection locations and dual manifolds resolve the contradiction between liquid fuel versatility and low emissions in gas turbine combustors.

Segmented annular injectors and auxiliary passages prevent NOx generation during startup.