Continuous Combustion Chamber TRIZ Cases

See how a bell mouth with differential pressure measurement and feedback control maintains stab

See how a pulsed pressure vessel with non-return valves and turbine alternates heat transfer an

See how spring seal air holes and turn guides cool the air hole plate periphery to prevent swir

See how varying natural frequencies between upper and lower horizontal duct walls using reinfor

See how embedded cooling tubes in EDM-formed channels reduce production cost and scrap rates wh

See how spring seal air holes and turn guides cool the swirler lip outer periphery, preventing

See how a pre-assembled baffle unit with integrated brackets reduces turbine duct noise while e

See how rare earth phosphate fibers embedded in ceramic matrix composites resist oxidation abov

Rare earth phosphate fibers in a ceramic matrix help CMCs resist oxidation and degradation above 1200°C in gas turbine engines.

Connected tangs and a stress relief hole help the pilot nozzle heat shield resist warping, clogging, and cracking under turbine heat and vibration.

An integrated fuel cell stack in the combustion liner passage uses pressure-driven airflow and air conditioning to stabilize heat and extend hardware life.

A stiffener shifts effusion plate natural frequency to avoid flame-vibration resonance while preserving cooling holes in the combustor.

Waste-heat recuperation preheats air and fuel in a ceramic combustor, enabling higher-temperature TPV power generation with better efficiency and power density.

A fuel cell stack placed between the casing and liner uses chamber pressure differences to boost turbine efficiency and extend hardware life.

A dual-combustion gas turbine turns low-BTU biogenic methane tail gas into electricity and heat while cutting emissions and operating costs.

Rotor magnets and stator coils compress and accelerate air to generate thrust without combustion, cutting fuel use and emissions.

A fuel cell stack placed in the liner-casing passageway boosts gas turbine power and efficiency while improving hardware life.

Powered coils spin magnetized rotors to compress and accelerate air for thrust without combustion, cutting emissions and turbine-related losses.

A pre-burner heats compressor air for an integrated fuel cell-combustor assembly, cutting ducting, weight, and added heaters.

A hydrogen-optimized fuel cell feeds exhaust directly into the combustor, cutting conduit complexity while boosting electrical output and fuel use.

An angled fuel cell stack in the combustor passage uses pressure differences and cooling airflow to raise power output while extending hardware life.

A shared fuel and oxidizer architecture lets a fuel cell and bipropellant thruster switch or run together for efficient power and thrust.

A fuel cell stack placed between the casing and liner uses pressure-driven airflow and cooling to raise gas turbine power and hardware life.

A hybrid catalytic and flame burner layout boosts fuel cell heating speed while improving blowout resistance and reducing installation space.

Angled fuel cells in the combustor passage use pressure-driven airflow and cooling to boost turbine efficiency and extend hardware life.

A rotating jet tube switches tangential and radial flow in a spin chamber to deliver precise valve control without tight tolerances or high power.

A segmented arm and multi-axis base let one insertion tool inspect annular engine spaces of different sizes without tool changes or collisions.

Portable grinding and polishing with axial and radial adjustment removes interior thermal barrier coatings on-site to cut turbine repair downtime.

A compliant damping seal baffle rides on the seal platform to limit cantilevered inner wall deflection, cut vibration stress, and prevent cracks.

Preformed combustor panels are cast and worked before coating to match shell geometry, reducing preload, spallation, and sealing issues.

A septum with cooling apertures and cavity vanes directs air across the nozzle platform to cut turbine vane heat and thermal erosion.

Rotating blocking walls vary active swirl channels to keep vortex velocity stable across wider gas flow rates and pressures.

Angled baffles in a burner parting sheet create swirl cooling that avoids plugging, limits hot spots, and reduces cooling flow demand.

Directional bracket stiffness supports actuator loads while accommodating thermal growth, preventing tube stretching and fretting.

Laser cladding builds an elbow and braze joint on tube stock, cutting gas turbine nozzle part count, weight, waste, and machining cost.

Backlash-based hole overlap detection identifies where combustor bulkhead and outer liner positions need adjustment for uniform fastening.

An EDM electrode removes damaged micromixer tube ends without contact, reducing debris, vibration damage, repair time, and cost.

A through-hole lets the component be welded from the opposite side, improving access in deep or obstructed wall and tubular assemblies.

Direction-dependent bracket stiffness supports actuator position while accommodating thermal growth to prevent tube stretching and yielding.

Beveled substrate edges with recesses and channels create controlled coating faults that absorb thermal expansion and reduce spallation.

A guided grinding tool removes thermal barrier coating from turbine interior surfaces on site, cutting repair downtime without disassembly.

Electrical discharge removes damaged micromixer tube ends internally without cutting debris or vibration that can harm braze joints and nearby tubes.

A compliant damping seal baffle cuts cantilevered inner wall vibration stress and deflection while preserving turbine case sealing.

Hybrid additive builds combine PBF, WAAM, and DED to make large rocket combustion chambers with fine cooling features and integral manifolds.

Cooling apertures, a septum cavity, and internal vanes direct air across the nozzle platform to cut thermal stress and extend turbine life.

Rods and wrap-based CMC forming create blade outer air seal features that improve high-temperature sealing and structural integrity.

Spherical-joint ducting delivers coolant to movable exhaust flaps, enabling effusion cooling with lower airflow demand and less thrust loss.

A nested fuel nozzle coupling secures the casing connection, limits leaks, and supports cleaner combustion with hydrocarbon or hydrogen fuels.

Powered spline-driven torque speeds gas turbine hose installation and removal while reducing crew time, scrap, and injury risk.

Optical light-through-coating detection locates blocked cooling holes in gas turbine components so coatings can be cleared and cooling efficiency preserved.

A segmented shield around gas turbine fuel piping joints blocks radiative heat while leaving ventilation clearance to avoid trapped leaks.

Angled front-wall facets and a vortex cavity guide helical fuel-air flow, cutting pressure drop, weight, and extra flow-directing parts.

Laser cladding builds an elbow directly on tube stock, removing the separate nozzle joint piece to cut weight, cost, and material waste.

A washer-formed cooling passage directs airflow onto combustor studs and standoffs to cut thermal stress and extend fastener life.

Spring-loaded feet and a central screw remove a bound combustor aft plate from micromixer tubes without damaging fuel injectors.

A central screw and spring-loaded feet push the aft plate off micromixer tubes through the center passage, avoiding injector and tube damage.

Heated gas is directed through installed gas turbine fuel components to remove carbonaceous deposits without engine disassembly or long downtime.

By switching a jet between tangential and radial flow in a spin chamber, this case cuts actuator force, leakage, and valve manufacturing cost.

Beveled substrate recesses segment ceramic coating edges into expansion-joint faults that cut spallation and improve shrinkage tolerance.

Machined enlarged tube ends and tapered tube tips repair bundled fuel injectors while avoiding premix flow restriction and flame interruption.

Pressurized fluid expands a fastener head inside a ceramic panel to backlock the joint and resist loosening from thermal expansion mismatch.

Additive deposition builds a unitary dual-wall cooling structure on a substrate, improving yield, inspectability, and cooling-path alignment.

Additively manufactured seamless multi-lumen spray bars replace complex welded fuel manifolds, improving flow, integrity, and serviceability.

A removable sound attenuator cover opens the combustor liner cavity for easier particle removal and cleaner thermal barrier coating repair.

A lattice of hollow struts routes cooling fluid through turbomachine components to cut temperature gradients and reduce cooling air use.

Integrated Helmholtz and quarter-wave resonators damp combustor ringing and vibration, improving turbine durability with hydrogen-capable operation.

Quench apertures and swirlers shift RQL combustion into the fuel-air mixer to stabilize hydrogen burning and cut NOx in turbine engines.

Radiused dilution passage inlets smooth combustor airflow to cut flow separation, improve combustion efficiency, and reduce emissions.

Angled secondary combustor exhaust lowers oxygen and peak flame temperature in the primary chamber to cut NOx without sacrificing efficiency.

Curved annular dilution slots and deflector walls spread dilution air laterally to quench hot zones and cut NOx in gas turbine combustors.

An inner-duct pilot lance premixes H2-based fuel with air before injection, cutting NOx and flashback risk in gas turbine burners.

Shaped driver holes and ramps stabilize combustor vortices in a shorter gas turbine combustor, cutting pattern factor and turbine thermal stress.

Rich-lean swirling passages and counter-swirl mixing help hydrogen combustors cut NOx while reducing flashback and flameholding.

A threaded, replaceable fuel injector enables exterior installation and leak-proof servicing without gas turbine disassembly.

Converging premixer tubes and dual fuel apertures improve fuel-air mixing in a gas turbine combustor while preventing flashback and lowering emissions.

Radial outer airflow delays gas-air mixing and shifts the flame zone downstream, reducing injector heat load and flashback risk.

Uneven fuel flow across combustor nozzle subsets with SAF cuts nvPM emissions while preserving gas turbine engine thrust.

Staged fuel flow across combustor nozzle subsets using sustainable aviation fuel lowers nvPM emissions across thrust conditions in aircraft engines.

Differential fuel flow across combustor nozzle subsets cuts gas turbine nvPM and soot while preserving thrust across operating conditions.

An RQL combustor with 14-22 fuel spray nozzles and SAF use cuts nvPM, soot deposits, and contrail persistence across idle and cruise.

A helical static mixer, sensors, and flow control keep blended fuels near a target Wobbe Index for more uniform turbine combustion.

Dovetail panel attachments replace combustor mounting studs to prevent hot spots and distress while maintaining cooling flow paths.

Spherical joints keep coolant flowing to movable exhaust flaps, enabling effusion cooling with lower airflow demand and less thrust loss.

A vortex-generating jet nozzle with a baffle boosts crossflow mixing in the combustor liner, improving secondary combustion efficiency.