Continuous Combustion Chamber TRIZ Cases

Clamping tabs and radial wall support keep steel and CMC combustion chamber parts sealed despite differential thermal expansion.

Stacked damping washers, a bushing, and a spring clip dissipate gas turbine fuel-line vibration to reduce cracking and leakage.

Spring-loaded feet and a central screw push a heat-deformed combustor aft plate off bound micromixer tubes without damaging fuel injectors.

A segmented arm with external multi-axis positioning adapts to annular engine cavities of different sizes while avoiding dedicated inspection tools.

A machined enlarged premix tube end and tapered replacement tip accommodate filler buildup and misalignment without restricting injector flow.

Two-stage surface measurement builds a corrected 3D model to reopen coated cooling holes faster and more accurately on turbomachine parts.

Elastic clamping tabs keep steel and CMC radial walls in axial contact, preserving combustion chamber tightness under thermal expansion.

A stepped retainer limits spool travel at higher pressure, holding flow geometry fixed to cut fuel flow variation in jet engine nozzles.

Swirling vanes and water saturation create a stable buoyancy vortex that concentrates ground-level airflow for lower-cost waste heat power generation.

Hybrid additive processes combine PBF, WAAM, DED, and cold spray to build large thrust chambers with fine cooling features and multi-material manifolds.

A spring element and recessed protrusion retain a CMC combustor liner while distributing loads and accommodating thermal expansion.

Hybrid additive processes combine PBF, WAAM, DED, and cold spray to build large rocket thrust chambers with fine cooling features.

A spacer jig fixes the interval between adjacent combustion cylinders, cutting fine adjustment work while improving turbine mounting accuracy.

Fused wick heat transfer cells move liquid metal by capillary action to dissipate combustor heat loads without pumps and reduce hotspots.

Machining an annular groove and welding in a replacement coupon restores fuel nozzle tip fit, cutting leaks, service time, and replacement cost.

A one-piece additively manufactured fuel manifold replaces many machined joints with seamless lumens, cutting assembly complexity and easing service.

Preformed combustor panels deform into shell curvature during assembly, improving fit, sealing, and coating life while reducing residual stress.

A hybrid brush, hard, and conformal seal maintains combustor-to-vane contact during rocking and twisting to reduce turbine leakage.

Machined channels on beveled substrate edges create fault lines in ceramic coatings to relieve thermal stress and resist spalling in turbines.

Laser cladding builds an elbow and braze joint on tube stock, avoiding separate elbow pieces to cut weight, waste, and part count.

A unitary additively manufactured concentric conduit assembly traps insulating fill in a sealed void to cut heat conduction and part count.

A dual bond coat repair rebuilds gas turbine TBCs to resist CMAS infiltration, oxidation, and spallation under thermal cycling.

An undulating fuel tube adds axial compliance and thermal contact inside the injector to reduce braze-joint fatigue from expansion and vibration.

A main pump sized for cruise and a support pump switched by valves cut parasitic draw and fuel heating while preserving peak flow.

Outer coating thickness and topology are measured to revise aperture machining, improving cooling flow and thermal management in turbine components.

A bayonet-mounted injector and baffle keep the baffle axially retained despite differential expansion, protecting downstream turbine parts.

Localized slots around cooling holes block CMAS infiltration paths while preserving thermal strain tolerance and coating life in turbine components.

Multi-angle boring forms diffuser-shaped rail orifices that raise cooling flow pressure and coverage in gas turbine heat shield panels.

A non-circular slider seal cuts pressure-exposed area to lower conduit force, reduce leakage, and accommodate thermal growth.

Hydrostatic shoes and spring elements keep rotor-stator clearance stable, cutting seal heat, stress, and replacement needs.

Saturated air and water injection stabilize a ground-level buoyancy vortex, raising waste-heat power density without tall structures.

Braze repair restores damaged dual-wall coversheets by joining replacement material to exposed pedestals, extending component life.

Angled multi-direction rail orifices route cooling air to the hot side and adjacent combustor parts, improving heat shield thermal protection.

Heated gas is directed through an insertion tube to burn or pyrolyze carbon deposits in installed gas turbine fuel components.

A sheet-based combustor thermal shield adds cooling and attachment features separately to cut fabrication time and simplify design changes.

Internal air passageways, a plenum, and impingement holes cool exposed turbine fasteners to prevent hot spots and premature failure.

Nonlinear helical cooling passages extend fluid residence time in a gas turbine injector, lowering metal temperature and preventing fuel coking.