Continuous Combustion Chamber TRIZ Cases

Integrally formed multi-zone fuel manifold reduces weight and complexity by merging separate conduits into a single compact assembly.

Angled burners induce tangential exhaust gas circulation within a combustion chamber to enable recursive sequential fuel oxidation.

Segmented flange design reduces grommet weight and thermal mass while maintaining continuous sealing contact during thermal expansion cycles.

Pneumatic valve alters flow channel area and blockage ratio to prevent shock wave forward transmission, ensuring stable operation during pressure deviations.

A control subsystem maintains compressor airflow above minimum rates to prevent aeromechanical stresses during turbine operation.

Deflection means divert cooling airflow toward the wake median plane, increasing total pressure to restore convective heat transfer through micro-perforations.

Dynamic fuel scheduling adjusts combustion parameters to prevent flame extinction and overtemperature when rejecting load in island mode.

A self-locating heat shield and burner collar assembly for annular combustion chamber heads.

Biasing elements and seal dividers secure high temperature material panels to manage thermal stresses and oxidation in gas turbine combustors.

Segmented pedestal exits direct cooling fluid to the trailing edge tip, preventing flow separation and stabilizing convective heat transfer.

Segmented pilot tube and cap design enables maintenance of gas turbine injectors, preventing leakage while maintaining stable combustion.

Convex portion inside cooling air hole guides airflow to spread and jet out over a wider range, preventing main flow gas from blowing away the cooling stream.

Angled injection ports generate swirling air flow that stabilizes the pilot flame against strong jets and high temperatures.

Asymmetric nozzle guide vanes mitigate hot spots by altering driving frequencies and forces, reducing the need for additional cooling air.

Aligning apertures with turbulator leading edges manages cross-flow buildup, maintaining high heat transfer coefficients along the duct wall.

Multi-lobed cooling holes use segmented inlet and metering sections to reduce flow separation and blow-off, extending engine service life.

Adjusting venturi inner wall angles and fuel impact zones prevents coke formation by maintaining stable temperatures during direct injection.

Segmented passages with non-rectangular slots and protrusions direct cooling airflow to reduce engine efficiency losses from excessive cooling air.

A ceramic matrix composite combustor liner embeds void patterns within intermediate plies to form internal cooling channels.

Multiple Helmholtz dampers defined by chambers between walls segment acoustic energy to resolve poor damping of pulsations and prevent hot gas recirculation.

Modular insert element with layered functional systems enhances heat resistance and cooling efficiency in gas turbine components.

Outer annulus injector elements confine mass flow within a converging combustion chamber geometry to optimize acoustic wave behavior.

Independent corner seal prevents air leakage at aft frame intersections, improving energy efficiency and reducing NOx emissions.

Cured polyimide fills open cooling holes in gas turbine components, preventing spallation and ensuring uniform thermal barrier coating application.

Annular fins in the purge circuit create airflow chicanes that cool the injector body and optimize fuel mixing for combustion chambers.

Segmented U-shaped cooling channels prevent entrainment of cooling flow into the fuel-rich zone, reducing NOx formation while maintaining liner integrity.

A cooling airflow divider region segments flow to prevent liner overheating and compressor casing damage from back pressure fluctuations.

Segmenting the picture frame into a seat and insert isolates cooling channels, reducing manufacturing costs while maintaining thermal reliability.

Segmented swirl channels in this dual fuel burner adjust flow resistance via a central damper to minimize NOx emissions during combustion.

A gas turbine engine cools combustion air using heat exchange with fuel ammonia during compression.

Springs and tabs deform radially to offset thermal expansion differences between ceramic and metal combustor parts.

A heating element positioned inside the urea spray cone directly heats the mixture to prevent crystal formation, avoiding backpressure from deposits.

A rich catalytic injector mixes heated fuel with air to stabilize flame aerodynamics in gas turbine combustors.

Raised features near dilution holes direct airflow to increase film cooling coverage and minimize thermal stress.

Segmented mixing tubes and a nested cap assembly reduce maintenance time while lowering emissions through precise air flow distribution.

Axially staggered premixer vanes create phase differences between heat release and pressure oscillations to dampen combustion dynamics.

A single-piece forged fuel injector stem integrates a gas gallery and fluid passages to eliminate brazing operations.

A gas turbine control unit adjusts air and fuel injection using flow meters to maintain the Wobbe Index within a predetermined range.

A tube connects bearing and ambient chambers with one end sealingly joined to a wall and the other free to move.

Integrated positioning elements on the tile component constrain spatial alignment, resolving manual mounting variability and improving air supply uniformity.

Segmenting the nozzle into independent components controls combustion dynamics and prevents lean blow-out across varying power conditions.

Temperature sensors detect downstream heat levels and trigger regulating valves to lower fuel flow, preventing thermal damage to the nozzle.

A gas turbine burner uses vortex generators and a lance with nozzles to inject fuel.

Correlating spectral components of optical and pressure signals identifies thermoacoustic instability, preventing combustion chamber damage.

Replacing vacuum tubes with solid-state converters in a triple helical flow vortex reactor achieves 70-80% efficiency and extends device lifetime.

A single cavity trapped vortex combustor uses a chute member to generate air vortices for efficient fuel mixing.

Segmented annular fairings with overlapping sectors reduce clamping force requirements, preventing deformation lobes and air leakage in combustion chambers.

Twisted mixing bars in a combustor nozzle create turbulence to mix fuel and air, reducing NOx emissions from incomplete combustion.