Continuous Combustion Chamber TRIZ Cases

Hydrogen introduced downstream shifts CVD equilibrium to limit pyrophoric exhaust deposits and keep ceramic matrix composite production running.

Arcuate members and a linear actuator re-round an out-of-round combustor body in place, cutting repair time and avoiding removal.

A continuous curved seal enables axial nozzle installation and removal while reducing seal damage and leakage between combustor liner segments.

A spring-retained CMC combustor liner avoids direct threading and accommodates thermal growth to reduce cracking and delamination.

Relief-cut curved seals fit radially offset gas turbine slots, easing installation while reducing leakage between adjacent components.

Low-profile tabs and removable stop brackets stabilize a gas turbine combustion liner while reducing airflow blockage, wear, and emissions.

High-pressure bypass airflow keeps a segmented piston ring engaged with the combustor liner, limiting leakage during takeoff rotation.

Angled outer rib corners boost turbulence for cooling, while curved inner corners cut stress concentration and cracking in gas turbine passages.

A press-fit spacer in an oblong combustor shell aperture keeps panels secure during thermal expansion, reducing buckling, cracking, and fatigue.

A radiused perimeter step in a gas turbine case boss eases wall-to-boss transitions, cutting stress concentration and extending case life.

A coiled fuel conduit with locally thicker bend regions accommodates thermal expansion and limits stress fractures in gas turbine injectors.

Sacrificial Au-Cu braze plugs keep cooling holes open during thermal barrier coating, then are cleared by heat, gas, and vibration.

Additive manufacturing turns multi-part gas turbine fuel manifolds into seamless spray bars that cut joints, leakage risk, weight, and service complexity.

A non-circular washer and puck interface lowers pressure-driven force on internal components while preserving sealing and axial sliding under thermal expansion.

Pressurized fluid expands a fastener head inside a stepped cavity to secure ceramic composite parts while minimizing thermal stress.

Peripheral channels and airflow passages cool combustor attachment features, reducing hotspots, oxidation, and thermal damage.

Diffuser-shaped rail orifices direct cooling air into a protective film that cools combustor panels and liners while limiting oxidation and burnback.

A locking member and compliant interface secure a turbine engine grommet while reducing CMC delamination, wear, and tool-based removal damage.

Bevel-edge channels and recesses help ceramic thermal barrier coatings absorb thermal strain and resist edge spallation in turbine parts.

A splined fitting and drive-wheel tool speed gas turbine hose removal and installation while reducing injury risk, scrap, and gasket damage.

Laser drilling and weld-closing form impingement and effusion holes after bonding, avoiding distortion, masking cost, and bond-quality loss.

Laser drilling and welding form impingement and effusion holes after panel bonding, improving hole accuracy, bonding quality, and coating flow.

Incremental axial positioning and circumferential force distribution help install or remove combustion liners without coating damage.

A gas bearing with a transmission disk and damping member supports supercritical turbine shafts, cutting vibration, stress, and oil-bearing maintenance.

Wick-based heat transfer cells move liquid metal coolant without pumps, helping gas turbine combustors handle high heat loads and avoid hotspots.

Inclined first and second cooling holes focus compressed air on the combustor seal area, improving local cooling while limiting pressure drop.

Temporary braze plugs block coating entry into cooling holes, then remelt for removal to preserve heat transfer and coating coverage.

Staggered core extensions reshape internal airfoil cooling flow to improve heat transfer and reduce cooling-air cycle penalties.

Segmented honeycomb seal rings block compressed air leakage between the liner and transition piece while accommodating thermal expansion.

An integrated threaded insert seals the fastener interface in gas turbine engines, reducing fluid leakage and supporting fuel economy.

Localized wall thickening at curved sections helps a coiled fuel injector conduit absorb thermal gradients, reducing stress fractures and service needs.

A track-guided lift arm and engagement frame reduce handling force while improving combustor assembly alignment during turbine maintenance.

Impingement cooling holes and a plenum shield the fuel nozzle venturi from high thermal loads, extending heat shield life and easing replacement.

Angled rail-member orifices redirect cooling air across adjacent combustor panels to improve thermal protection and reduce oxidation distress.

Cooling holes cast and drilled along common vectors spread air uniformly across a combustor heat shield to improve thermal protection.

A crimped boss and annular element secure and position the flame tube without TIG welding, cutting deformation, rework, and replacement effort.

Capillary wick heat transfer cells move liquid metal coolant without pumps, helping combustor liners handle high heat loads and avoid hot spots.

Alternating members with different thermal expansion coefficients adjust turbine clearances automatically, reducing leakage and collision risk.

Multiple axial fuel stages split compressor air between nozzle and injectors to improve turndown, liner cooling, and NOx control.

Alternating primary and secondary injectors enable faster relight and stronger flame-out resistance in aircraft gas turbines, especially with hydrogen fuel.

Steam injected through a combustor quench aperture mixes with air to lower flame temperature, cut NOx, and preserve combustion efficiency.

Annular fuel galleries around each air passage improve hydrogen micro-mix uniformity, helping aircraft gas turbines cut NOx and avoid outlet blockages.

A split fuel-nozzle combustor and SAF use cut gas turbine nvPM emissions by tuning nozzle ratios and local fuel flow rates.

Radial and axial swirlers create a recirculation zone that improves turbine combustor light-off, re-light, and smoke reduction.

Separate hydrogen and hydrocarbon injection paths in mixing tubes stabilize flames and support low-emission gas turbine combustion.

A position sensor and diagnostic unit detect when a gas turbine combustor ignition plug fails to reach insertion, avoiding wasteful restarts.

Integral heat-pipe and cavity features spread impingement cooling across combustor panels to cut hot spots and extend component life.

Heating fuel with engine oil lowers viscosity before the combustor, improving lean-burn atomisation while limiting pump wear and coking.

A multi-tube fuel nozzle uses an integral air diffuser to redirect flow radially inward, improving uniformity and reducing flow separation.

Raised walls segment the impingement surface into cells that block cross-flow and eliminate static zones, maintaining jet stability and improving heat removal.

Tribling devices create turbulence to prevent particulate buildup that reduces cooling efficiency and causes blockages in the combustor liner.

Discharge openings in toroidal afterburner vanes inject pilot flow for primary combustion, resolving efficiency limits in augmented thrust systems.

A control system adjusts fuel flow splits to stabilize combustor pressure fluctuations in gas turbines.

A liner stop system uses a damping insert between male and female components to retain combustion liners within flow sleeves.

Internal cooling channels transport air through the central tube sidewall to prevent flame attachment and backfire on hydrogen fuel combustion surfaces.

Thermoelectric generator assemblies attach to the outer surface of a gas turbine hot section cowling to convert waste heat into electrical power.

A gas turbine combustion oscillation suppressing device adjusts vent hole opening ratios based on varying gas space height to optimize acoustic absorption.

A combustor gap fuel injector directs fuel into airflow passing through the turbine interface.

A turbo machine heat exchanger cools compressor discharge air via conduits and a plenum.

Segmented electric pump modules provide redundant hydraulic pressure generation while eliminating energy diversion from the propulsion system.

Laser pulses create roughened diffusion sections in CMC film holes to reduce thermal gradients and improve component durability.

Annular combustor liner assembly manages air flow distribution to reduce nitrogen oxide emissions by controlling residence time and peak flame temperatures.

Fuel injector cover with segmented flow apertures enhances compressed gas delivery to secondary injectors.

Three pin supports manage thermal expansion mismatches by permitting radial growth and reducing assembly complexity.

Elastic member biases guide within groove to accommodate thermal expansion, reducing spark plug wear from vibration.

Dual venturi structures and counter-rotating orifices improve fuel atomization, reduce gaseous emissions, and prevent flashback in combustion chambers.

A fuel injector device with an undulating trailing edge generates small vortices to improve fuel and oxidant mixing quality.

A telescoping sleeve assembly with a bias mechanism connects adjacent combustors.

Crenellation features in diffusing sections improve film cooling effectiveness by reducing flow separation and lowering total cooling load requirements.

Heat shield panel with impingement holes directs cooling air to reduce temperatures.

Movable slides in a shaping tool enable removal of the hollow interior after pyrolysis, resolving manufacturing complexity for thermally stressed components.

Lobed trailing edges on streamlined bodies generate vortices to mix fuel and air, reducing pressure drop while maintaining homogeneity.

Cylindrical sleeve of inlet ring adapter absorbs thermal and vibrational stresses to extend spring clip seal operational life.

Integrated combustor assemblies channel combustion gases through turbine buckets, reducing flow energy loss at stationary stator vanes.

Azimuthal diffuser vane alignment separates water from fuel injectors, preventing combustion extinction during wet weather operations.

Segmented metallic fasteners behind insulating tiles resolve the trade-off between assembly ease and thermal insulation performance.

Nested heat shield and flow sleeve protect the liner from thermal damage while managing device complexity through integrated air extraction.

Quench zone geometry tailors radial temperature profiles to reduce thermal stress on turbine components.

Annular combustion chamber wall multiperforation with distinct hole characteristics provides effective cooling.

Alternating through and angled holes reduce grommet temperature, preventing oxidation and extending durability.

Intra-wall flow passages position dilution holes near inlets to reduce stress concentration and maintain combustion stability.

Segmented cooling sections with flow diverters prevent cross flow accumulation, preserving heat transfer coefficients and reducing pressure losses.

A lateral flow injection feature directs airflow across a heat shield panel to generate cross flow within the cooling channel.

A curved interface passage directs leakage flow along liner panels to promote film attachment, eliminating dead regions that cause adverse local aerodynamics.

A coaxial impingement cooling sleeve directs combustion air against the combustor liner to reduce wall temperatures.

Segmented caps with downstream attachment points reduce cantilevered vibratory stresses while maintaining aerodynamic separation.

Threaded collar and retainer secure the heat shield to the domeplate, enabling non-destructive removal for maintenance.

Retracting the cone creates maintenance access without removing the intake system, reducing downtime.

Integrated secondary nozzle design prevents flame-holding damage while enabling high reactivity fuel use in gas turbine combustors.

Segmented dendritic passages with a flow-restricting throat reduce blockage risks while maintaining heat extraction capability in gas turbine blades.

Optimized lobe orientations combine vortices to improve large-scale mixing, reducing NOx emissions and pressure loss without high-pressure carrier air.

Spring members bias extending members on ceramic matrix composite panels away from combustion faces.

Triangular mixing air hole patterns on inner and outer walls create axially offset jet flows to improve fuel-air mixing efficiency.

A slanted perforated plate damper fluidly connects a gas turbine combustion chamber to an external damping volume for acoustic resonance.

Optimized combustor transition piece contraction ratio reduces flow velocity at the outlet.