Continuous Combustion Chamber TRIZ Cases

Integral flanges on the combustor shell, TOBI, and case enable secure alignment without temporary fasteners during assembly.

A multi-tube fuel nozzle uses an inlet flow conditioner to distribute airflow uniformly across separate tubes for combustion.

A distributed spark igniter system creates a pulsed electrical arc between a recessed terminal and a separate electrode to ignite the air-fuel mixture.

Recirculating cooling air via an impingement plate and flow conditioning passages reduces NOx emissions and thermal stresses on the cap plate.

Asymmetric fuel injection patterns disrupt coherent flame structures to reduce thermoacoustic pulsations without adding damping devices.

A unitary inner diffuser structure with inseparable tangential onboard injectors minimizes airflow perturbations in gas turbine engines.

Curved cooling holes boost heat transfer and film cooling effectiveness while reducing total cooling flow requirements.

Segmented through holes in the spring seal maintain joint stiffness while enabling film cooling for the combustion duct assembly.

Sealed baffle plate eliminates cross-flow to reduce pressure drop while maintaining high heat transfer efficiency in gas turbine cooling systems.

A ceramic matrix composite tile uses a hollow cell structure to provide thermal protection.

A fuel injection assembly uses a polygonal duct segment to enable additive manufacturing with minimal temporary supports.

Crowned pins distribute axial and tangential loads across bushings, eliminating concentrated wear from thermal expansion.

Elongated service tool compresses crossfire tubes to separate combustors without adjacent disassembly.

Instrumentation translator converts light-off detector signals to engine controller data via dedicated interfaces.

Additive layer manufacturing integrates cooling channels into the combustor dome to reduce assembly complexity and thermal stress.

Segmented fuel manifold design allows individual injector servicing without full assembly removal, resolving downtime and reliability trade-offs.

An additively manufactured combustor dome incorporates a floating ferrule and frangible support arm to reduce thermal stress between components.

A combustor panel features a peak-valley gridded pattern with recessed cells and effusion holes for enhanced cooling.

A swirlerhead cooling assembly directs cooler air into a prechamber to establish a thermal barrier along the central axis.

A turbine cooling hole features an asymmetrical diffusing section that expands toward the heated surface to produce a wider, slower cooling film.

A plasma generator ionizes fuel-air mixtures within a swirled combustion chamber to enhance reaction kinetics and flame stability.

A heat shield panel uses variable thickness rail members to define a cooling chamber and accommodate thermal expansion in gas turbine engines.

Fuel shield creates thermally insulating gap to reduce thermal gradients and prevent thermal cracking of pilot vanes during afterburner ignition.

A volute walled enclosure defines a spiral scroll pitch axis to maintain constant axial velocity through the combustion chamber.

Double bellows seals accommodate thermal movement in integrated combustor nozzles, reducing NOx and CO emissions.

Active patternation via an auxiliary circuit valve mitigates combustor noise without adding heavy mechanical hardware.

A turbine mixing chamber conditions cooling air by blending bypass flow with compressor discharge to maintain optimal component temperatures.

A fuel controller adjusts main and pilot fuel flow ratios to optimize combustion distribution across operating conditions.

A tangential radial inflow combustor design uses cavity air tubes to induce bulk swirl airflow for flame stabilization.

Caps reduce cooling air velocity in the burner front panel dampening chamber to prevent hot gas ingestion and protect acoustic integrity.

Elongate air/fuel premixing injection tubes incorporate porous walls to diffuse secondary fluids and stabilize the boundary layer.

An integrated retaining bracket shields a fuel nozzle from 2000°F flames, preventing tube disconnection and meeting FAA fire safety regulations.

Lobed vortex generator trailing edges create targeted turbulence for efficient fuel-air mixing while reducing manufacturing complexity and cost.

Segmented multi-walled turbine structure uses varying cooling element densities to resolve thermal management efficiency against structural complexity.

A liner panel grommet with radiused dilution passage edges directs cooling airflow to protect combustor surfaces.

Refractory ceramic annular resonator with spring elements compensates thermal expansion to reduce cracking in gas turbine combustors.

Peripheral channels and axial recesses circulate cooling air through the flange, reducing thermal stresses on bolts.

A moveable fuel nozzle assembly adjusts throat area to modulate shockwave geometry and maintain constant dynamic pressure.

A gas turbine control system monitors pulsation signals to mitigate thermoacoustic vibrations and protect engine components.

Screen holes tuned to damping frequencies suppress combustion pressure fluctuations without diverting airflow, maintaining gas turbine efficiency.

Segmented liner sections displace axially to optimize fuel burn efficiency and reduce nitrogen oxide emissions across varying power operations.

Axially staged mixer injects dilution air at half convective wavelengths to stabilize inlet temperatures, reducing pressure drops from conventional cooling.

Concentric micro-mixer nozzles with annular strips pre-mix fuel and air, suppressing pressure fluctuations from combustion instability.

Forward and aft flanges mate with fixture grooves to form a bi-directional seal, eliminating manual tape application and reducing vacuum leakage.

Segmented dilution openings with radial support walls disrupt recirculation zones, reducing liner wall temperatures by 500°F and minimizing NOx production.

Periodic catalyst injection controlled by feedback loops reduces solid particle emissions to regulatory limits while minimizing fuel additive consumption.

A dual mode combustor switches between deflagration and rotating detonation using dedicated initiators.

Aerodynamically enhanced premixer design controls boundary layer profile to reduce NOx emissions while maintaining fuel efficiency.