Continuous Combustion Chamber TRIZ Cases

Convex baffle conforms to diffuser streamlines, reducing aerodynamic interference while injecting steam for NOx reduction.

Adjusting fuel pressure and volume through a flow restrictor generates heat from spillage, preventing icing without external heaters.

Segments combustion into separate units to eliminate mixing instability caused by temperature differences between exhausted and supplemental fuels.

A transition piece support structure uses a hinged connection piece to pivotally approach the turbine inlet.

A combustor nozzle design featuring a multi-tube structure with a dedicated cooling space for the tip plate.

A burner design uses cooling holes to inject mixed fuel near the nozzle surface, creating a protective fuel-rich boundary layer.

Internal cooling orifices in the support boss circulate air, reducing temperature gradients and stress on heat shields caused by local hot spots.

Inverting inlet positions on the combustor panel reduces residual stress near apertures while maintaining high cooling performance.

Nested barrier member and resonators attenuate broadband noise while maintaining compact size and low pressure drop.

Bi-casting separates porous cooling elements from structural walls, resolving differential thermal expansion while maintaining high heat conduction.

Segmented fuel injectors distribute air and fuel into secondary combustion zones to create homogeneous mixtures.

Multi-level protrusions on the heat exchange wall increase turbulence to reduce required cooling air quantity while maintaining combustor temperature limits.

A transition part assembly uses a collision sleeve and internal guides to direct cooling air toward the side surfaces of the component.

Local deflections in a gas turbine cooling jacket compensate for irregular thermal loads on the shell, extending component service life.

A multi-mode combustion system transitions between deflagrative and detonation modes by adjusting fuel flow through a control valve.

Strategic nozzle placement segments combustion zones to reduce NOx and CO emissions while maintaining stable ignition.

A fuel nozzle assembly integrates a micro-cooling channel along the aft plate to distribute cooling air through a dedicated plenum.

Adjusting impingement angles reduces turbulent accumulation on heat shield panels, maintaining cooling efficiency and preventing blockages.

Helmholtz resonators integrated into injector heads counteract combustion oscillations, extending component durability.

Angled swirl vanes in dilution openings generate swirled flow that fills wake regions behind jets, reducing NOx formation and extending combustor liner life.

Curved transverse edges and joint covers accommodate dimensional variations, maintaining consistent sealing contact between deflectors and the chamber bottom.

Double-wall combustor structure channels cooling air through slots to protect heat shield panels from high temperatures.

Infrared sensors measure turbine blade temperatures to adjust fuel flow, eliminating safety margins that reduce engine efficiency.

A rotor assembly for an open cycle engine uses pressure gain compression and expansion passages to drive gas flow through a central axis.

Asymmetric inclined upstream air holes create controlled swirl flow that suppresses circulating backflows and prevents flame holding in the premixer.

A contoured inner wall forms a converging nozzle to accelerate dilution air jets in gas turbine combustors.

Accelerating channels in combustor liners reduce NOx emissions by preventing cooling flow entrainment into fuel-rich zones.

A distributed fuel control system regulates individual multiplex delivery units using real-time sensor feedback and torque motor adjustments.

Programmable clutch control enables variable generation modes in compressed air energy storage, resolving operational flexibility constraints.

A geometrically segmented ceramic coating on turbine components includes an internal cooling passage that reduces compressor bleed requirements.

Cusped cooling holes reduce flow requirements while maintaining thermal protection, preserving engine efficiency and extending component service life.

Segmented flow sleeve directs compressed air through a cavity to mix fuel and air, reducing NOx emissions in high-pressure combustion environments.

Digital simulation determines fuel split derivatives to control T3.5 temperature, eliminating costly PI controller tuning and preventing combustor blowout.

Secondary fuel injection compensates for steam loss in turbine combustors, reducing power susceptibility while maintaining specific fuel consumption.

Refractory insulating layers shield supporting elements from high temperatures, preventing structural deterioration and maintaining heat shield integrity.

An annular cavity between the combustor liner and sleeve provides impingement cooling to reduce thermal distress in space-constrained turbine engines.

Protective housings and nested conduits prevent damage to axial fuel staging systems while safely dissipating fuel leaks into the combustion process.

Flexible couplings link combustor tubes to plates, absorbing thermal expansion and contraction to prevent seal leaks.

Plugging material blocks cooling orifices in turbine engine walls to define minimum porosity levels for initial operation.

An elliptical upstream shroud end matches compressor airflow geometry, reducing total pressure loss and improving lean burn combustion efficiency.

Segmented acoustic screen minimizes air mass flow diversion for cooling, maintaining damping efficiency and reducing NOx emissions.

Integral air wipe outlets deliver axial airflow to prevent carbon deposition and thermal erosion on fuel nozzle components.

Staggered impingement and ejector holes reduce flow interference while minimizing thermal gradients on combustor dome heat shield lips.

Burner assembly adjusts secondary burner convective time to maintain combustion stability while reducing polluting emissions.

Segmented cooling air supply units direct flow to inner and outer combustor regions within a gas turbine casing.

Vectored deswirl assembly redirects radial airflow from a centrifugal compressor into an axial direction for gas turbine combustion.

A boron-free ceramic surface layer forms on a silicon carbide composite via melt infiltration to prepare the substrate for environmental barrier coating.

Segmented combustion zones with venturi stabilization balance high efficiency against nitrogen oxide emissions.

Plate-fin combustor cooling and reverse-flow effusion reduce thermal stress on transition component walls while maintaining power output.