Continuous Combustion Chamber TRIZ Cases

A floating bowl and deflector assembly maintains radial clearance via a sliding plane.

A cap insert merges a fuel nozzle plate and impingement sleeve into one unit.

Relocating the torch igniter inside the high-pressure case removes exposure to damaging pressure differentials while maintaining efficient combustion.

A gas turbine combustor flow guide member directs air into nozzles while attenuating high-frequency pressure vibrations.

Single-part axial fluid injector reduces pressure losses and simplifies manufacturing while maintaining effective component cooling.

Reentrant microstructures in a zero-porosity material eliminate stress concentration while maintaining fluid impermeability for gas turbine components.

An inflatable member adjusts the resonating volume of a gas turbine resonator, eliminating the need for multiple fixed units.

High-pressure air flows through structural wall channels to cool the glow plug housing, preventing thermal stress on torch igniter components during operation.

A lateral flow injection device directs airflow across a heat shield panel to generate cross flow that separates particulates from cooling air.

Integrating cooling passageways into the seal engagement region directs fluid flow to manage exhaust temperatures and reduce thermal fatigue.

A sleeve-equipped washer guides coolant flow around threaded studs in a combustion chamber to enhance heat removal efficiency.

Auxiliary guides on the air hole plate suppress air flow separation in outermost circumferential rows, reducing NOx emissions and pressure loss.

Segmented intermediate rails maintain pressure drop across liner panels when perimeter rail damage reduces cooling efficiency.

A fuel nozzle guide plate mounts to an air swirler via a collar and retainer plate assembly.

Experimental correction factors applied to digitized models ensure flow compliance without extensive physical testing.

Radially offset cooling channels and integrated turbulators disrupt airflow to manage high heat loads in gas turbine engine combustors.

A gradient transition structure blends metal and ceramic phases to create a seamless composite component for gas turbine applications.

A turbine cooling aperture transition section accommodates lateral misalignment between meter and diffuser sections.

Segmented multi-tube nozzles with resilient seals mitigate thermal stresses and improve fuel-air mixing uniformity in gas turbine engines.

Flow diverters manage cross-flow in impingement cooling arrangements to maintain consistent heat transfer on duct walls.

Auto-tune controller adjusts fuel flow splits to maintain combustion dynamics, reducing manual tuning downtime during extended turndown operations.

A fuel injector center body assembly uses conical swirl slots to direct liquid fuel into an annular prefilm passage for uniform film formation.

Variable wall thickness in the inner diffuser case structural cone reduces localized thermal transient stress by ten percent.

A micro-mixer uses segmented fuel supply passages to deliver fuel into a mixing passage for compressed air.

Segmented baffles lower cooling air velocity inside the acoustic damper, preventing hot combustion gas ingestion and protecting burner components.

Premix plate passages manipulate fluid flow to ensure uniform fuel-air mixing, lowering peak combustion gas temperatures and reducing NOx emissions.

Segmented ceramic coatings manage thermal radiation scattering and reflection, resolving heat shield effectiveness limitations in gas turbine combustors.

Multi-lobed cooling holes reduce flow separation and lower cooling flow requirements while maintaining high blowing ratio performance.

Asymmetric diffusing section reduces flow separation at corners, maintaining engine efficiency.

Turning vanes between casings facilitate laminar flow through the flameholder to prevent upstream backflow.

A parallel cooling concept divides gas turbine transition piece airflow into independent paths to reduce pressure drop and leakage penalties.

Separating cooling from the main air cycle with supercritical carbon dioxide boosts power output while recycling emissions.

An elastic connection unit absorbs thermal expansion differences between the metal outer side wall and the CMC panel, ensuring reliable support.

A helicoidal rib guides cooling air at a predetermined angle to create vortex currents on the liner surface.

Modular annular combustor with adjustable oblique-injecting swirl nozzles resolves the contradiction between compact length and measurement accessibility.

An air guidance piece directs cooling air along a gas turbine combustion chamber wall, reducing cooling air loss into the hot gas path at the downstream edge.

Radial partition plates divide annular air flow passages into inner and outer streams, preventing fuel entry into protective film layers to suppress flashback.

Sliding flanges accommodate thermal expansion in gas turbine casings, reducing stress and simplifying assembly.

Strategically positioned injectors in a gas turbine mixer cancel mass flow oscillations caused by axial flame movement, ensuring constant combustion conditions.

A combustor liner element uses integral protuberances to secure tiles while enabling unobstructed access to effusion holes.

Guide vane arrangement deflects air at 25 degrees to form a spiral flame, reducing flow deflection and simplifying the turbine vane ring.

Segmented cooling openings and a downstream fence direct compressed air for film cooling and gas dilution, preventing heat shield deterioration.

A rail and lip on the heat shield create a cavity that directs cooling air radially to protect combustor corners.

Multi-stage diffuser system redirects compressor air flow through a turning portion to stabilize fluid dynamics within the annular combustor.

Interlocking tile members eliminate protruding studs that clash with laser heads during effusion cooling hole manufacturing.

An extended pilot mixing tube nested within a burner cavity improves fuel-air mixing homogeneity, reducing NOx emissions from fuel-rich pockets.

A leaf spring damper stack absorbs engine vibrations through elastic deformation and frictional sliding, stabilizing the fuel spray bar assembly.

Elongated hole borders and coated piston rings seal gas turbine combustion chambers, reducing fretting wear and air leakage.

Independent burner staging reduces unburned fuel and NOx emissions by activating specific nozzles based on operational load requirements.