Continuous Combustion Chamber TRIZ Cases

Elastic retainers isolate vibratory movements and reduce wear at sliding interfaces while simplifying assembly maintenance.

Side drillings in the shroud dissipate acoustic energy to reduce noise while equalizing pressure differences to prevent airflow separation.

Splitting fuel between main and pilot injectors reduces NOx emissions during cruise while maintaining combustion stability.

A retaining plate and housing coupling structure secures mechanical fasteners within a propulsion system hot section.

Ventilation orifices on the protective screen channel secondary flow to cool the fuel manifold, preventing thermal deformations and coking.

Segmented swirlers in the nozzle assembly improve fuel-air mixing uniformity, reducing NOx emissions in gas turbines.

A staged injection system reduces reactant residence time at high temperatures, minimizing NOx emissions while maintaining engine efficiency.

Concatenated dilution passage integrates discrete holes and annular slots to inject mixed air, resolving insufficient mixing from annular-only designs.

Dimpled pre-swirler blades reduce drag force and parasitic pumping losses while maintaining turbine performance.

A diverging cooling hole with a longitudinal ridge promotes diffusive flow, reducing flow separation and corner effects to lower cooling air requirements.

Vortex generators induce fluid rotation within a cooling passage to boost heat transfer coefficients while minimizing pressure losses.

Moving the casing split downstream lowers fluid pressure on flanges, enabling smaller components and easier maintenance access.

An integral fastener merges the component and attachment into one piece via simultaneous infiltration, resolving leakage gaps and tolerance control issues.

A tubular air deflector creates symmetrical flow to prevent wall damage and improve temperature homogeneity in microturbines.

V-shaped staggered air admission holes distribute quench jets across the annular liner to rapidly dilute fuel-rich gases and reduce thermal NOx formation.

A diverging hole portion generates counter-rotating vortices to promote diffusion of cooling air.

Optical sensors measure UV and visible light to generate a combustion quality spectrum, differentiating flame instability from acoustic pressure oscillations.

Segmented web indentations enable injector dismounting without increasing axial play, reducing turbine engine mass.

An insert with angled openings directs cooling air onto engine surfaces to enhance thermal management.

Segmented planar facets create independent bearing surfaces for deflectors, resolving narrow spacing constraints between closely spaced fuel injection orifices.

Merges combustor and turbine components to remove leakage paths and reduce device complexity while maintaining combustion completeness.

A push-lock device secures gas turbine engine tiles using a front-mounted locking-bracket mechanism.

Varying swirler spacing creates distinct fluid flow regions that ensure uniform fuel mixing, reducing carbon monoxide and nitrogen oxide emissions.

A monopropellant continuous detonation engine uses a dedicated feed assembly to deliver fuel into a wave channel for sustained thrust generation.

Radially staged manifolds reduce recirculation zones to lower NOx emissions across power ranges.

Multi-cone premix burner design varies cone angle along axis to stabilize flame front and eliminate axial oscillations without bluff body.

A precursor detection unit analyzes time series signals from combustors using Hurst exponent estimation and recurrence quantification to identify lean blowout indicators.

Segmented annular manifolds with tapered sides inject quaternary fuel upstream of nozzles, reducing flame-holding and combustion instabilities.

Separate injector caps segment flow paths to stabilize pressure distribution and prevent uneven fuel-air ratios in combustors.

A gas turbine system uses a heat exchanger to preheat compressed air from multiple compressors feeding a single combustor.

Rare earth silicide bond coats protect silicon carbide substrates from extreme heat and mechanical fatigue in gas turbine engines.

Integrated furcating nozzles partition flows to cool the cap, reducing emissions and maintenance complexity.

Calibrated slots in the fairing balance external and internal bypass flows, improving fuel penetration and cooling efficiency.

Radial spring compliance in a cantilever spring absorbs deflection to mitigate thermal binding between ceramic matrix composite and metal parts.

A self-purge system uses an additively manufactured dual ball valve assembly to selectively purge fuel passages in gas turbine engines.

A sealing coating on ceramic matrix composites prevents silicon loss during repair, maintaining structural integrity.

A base body with a cavity directs cooling air through passage openings to cool threaded bolts, preventing material creepage at the bolt base.

Inter-engaging ribs on exo-skeleton tiles provide radial reaction forces to enhance structural rigidity in gas turbine assemblies.

A gas turbine combustor uses a stepped recess in the fuel injection portion to direct fuel flow and promote air-fuel mixing.

Integrally formed transition nozzle channels combustion gases while surface features transfer heat away from the component.

Cooled air injection into fuel ducts prevents ignition of accumulated pre-heated fuel during first-stage operation.

A coolable wall element impingement plate uses a bendable retention tab to secure the component without welding.

Rim-rotor turbomachinery uses high g-field combustion to achieve elevated temperatures and low NOx emissions while maintaining ceramic blade reliability.

Concentric swirler vanes stabilize combustion and reduce NOx emissions by creating fuel-rich and fuel-lean zones within the inner tube.

Spring channels in swirler vanes provide mechanical flexibility to absorb thermal expansion, extending service life under high temperature gradients.

A gas turbine airfoil diffuser hole features a linear ridge covered by thermal barrier coating to anchor the layer and ensure smooth airflow.

An integral air swirler extends from an inner heat shield to direct airflow at a fuel distributor outlet.

A combustor dome bifurcates combustion gases into inner and outer streams for precise temperature management.

A ribbed support structure accommodates differential thermal expansion in nested ducts, eliminating internal stresses from rigid bulk supports.