Continuous Combustion Chamber TRIZ Cases

Segmented wall and cavity injection holes resolve thrust versus flame stabilization trade-offs by independently controlling fuel flow rates.

A fuel blending system mixes natural gas with process gases to regulate combustion dynamics.

A segmented exit seal uses a lid member to cover recessed spaces in the seal body.

Angled effusion rows maintain film effectiveness despite dilution interruptions, reducing thermal stress without added complexity.

Segmented combustion chamber bowls use claw connections to prevent component detachment while maintaining thermal protection against off-centering.

A liner retaining feature with a bolt and lock tab secures the combustor liner within the flow sleeve.

Silicon metal infiltrates the sacrificial layer to join it with the structural component, preventing fiber exposure and cracks during precision machining.

Orienting a venturi device at greater than 48 degrees reduces NOx concentrations below 3 ppmvd by decreasing residence time.

Capillary infiltration fills ceramic matrix composite cavities during densification, reducing thermal gradients and tooling complexity.

A control system applies Fourier transforms to pressure signals for automatic tuning.

Segmenting the bulkhead into a removable panel allows independent mixer servicing, reducing maintenance costs and material waste.

A CMC combustor panel uses an inverted attachment flange to position the metal interface away from hot regions.

A gas turbine control device adjusts fuel and air flow rates based on real-time fuel composition analysis.

Compressor discharge air flows through dedicated passages to purge and cool fuel nozzle tips, eliminating flame holding risks from quat fuel mixing.

Asymmetric vorticor pin design promotes targeted vortical flow elements within gas turbine cooling passages.

Ribs and flow turbulators direct cooling air to impinge on the flange, mitigating thermal deformation under high temperature loads.

A segmented gas turbine combustor controller adjusts individual burner fuel flowrates to maintain high combustion temperatures.

An annular cavity in the swirler ferrule plate manages oxidizer flow pressure into the primary venturi.

Variable thickness nozzle flaps mitigate thermal stresses in composite materials while maintaining efficient heat dissipation.

Thermally insulating material in an intermediary cavity reduces heat transfer to fuel supply passages, minimizing carbonaceous deposit formation.

Ribbed target surfaces shield cooling air from cross currents while accelerating impact jets to improve heat transfer efficiency.

Variable thickness combustion liners adjust impingement cavity spacing to control Mach number, reducing particulate accumulation on heat shield panels.

Swept swirl vanes reduce flow separation and pressure drop while increasing effective flow area in gas turbine fuel nozzles.

A nozzle assembly mixes liquid fuel with gas flow to produce a gas-liquid mixture for combustion.

Cut-outs around bolt holes reduce thermal stress by 26% and extend component life.

Non-axisymmetric end walls control cross-passage pressure gradients to reduce secondary-flow vortices and mitigate swirling flow incidence variations.

Liquid fuel cools chamber walls and heats for flash vaporization, balancing pressure-flow conditions via an adjustable throat.

A springless active combustion control valve modulates fuel flow via translation and rotation components to stabilize turbine engine operation.

Effusion holes cool gas turbine combustor liners, reducing pressure drop and improving efficiency.

Grooved swirl plates inhibit flame adhesion to prevent flashback while maintaining low NOx emissions under varying load conditions.

A deflector plate intercepts thermal energy from the combustion flame, protecting the dome portion from excessive heating while maintaining engine efficiency.

Inclined cooling passages in the sealing member reduce required cooling air volume while preventing combustion gas heat damage.

Retractable support pins allow internal mounting of a fuel manifold, bypassing external obstructions that complicate assembly and maintenance.

An expanding diameter exit lip thins the fuel film to resolve high pressure atomization quality trade-offs in gas turbine combustors.

Angled seal holes in metallic heat-insulating tiles reduce cooling air consumption by preventing hot gas ingestion at the expansion section interface.

Modular segmentation of the combustor liner cap assembly reduces manufacturing labor while accommodating thermal expansion through dynamic retention.

A gas turbine diffuser uses concentric tubes and transition ducts to form circumferential gaps between combustors for uniform compressed gas distribution.

A recessed igniter configuration reduces structural deformities in gas turbine combustors.

An aerodynamic peg injects fuel and steam into a gas turbine combustor.

A beaded bracket secures ceramic matrix composite components to metallic structures.

A fuel nozzle design with a larger inner diameter nozzle tube and distribution manifold provides consistent flame distribution across multiple combustor cups.

A sleeve with circumferential apertures distributes pressurized air into a combustor head end volume.

A robotic inspection system uses a multi-degree-of-freedom camera shaft to capture high-resolution images inside gas turbine combustors.

Evaporating liquid fuel before combustion reduces NOx emissions without water injection, maintaining gas turbine efficiency.

Asymmetric fuel injector inserts orient within swirl generator segments to direct combustion air flow.

A dry gas circulation circuit removes residual powder from internal cavities in additive manufactured intermediate parts.

A circumferentially extending split line between the blocker ring and support regulates compressed air flow in turbine engine fuel injectors.

Additive manufacturing creates monolithic pilot burners with thermal bridges, reducing complexity and weight while maintaining structural reliability.

Axial air introduction through flared walls resolves radial bulk constraints in turbomachine combustion chambers.

Variable opening ratio perforated plate guides air uniformly, reducing pressure loss and deviation without enlarging structure.