Engine Manufacture TRIZ Cases

A bifurcated inlet housing separates airflow into distinct radial paths before mixing them downstream.

Segmented downstream walls with fixed flaps reduce pressure losses from turbulent recirculation zones while maintaining thermal exchange efficiency.

A swirl housing redirects exhaust gases into an annular path using circumferential vanes to produce uniform axial flow.

Branch passages deliver pressurized cooling air to prevent hot gas backflow, reducing thermal fatigue in the platform.

A turbine shroud carrier accommodates thermal expansion between metallic and ceramic components.

A split ceramic matrix composite turbine ring uses a wedge and elastic return elements to maintain contact under thermal stress.

Flexible ladder seal segments with angled flanges adapt to airfoil platform geometry, reducing fluid leakage and pressure loss in gas turbine engines.

A pump drip control system uses a slinger assembly and circumferential channel to direct liquid leakage into a gathering chamber.

Protrusions inside film cooling holes reduce stress concentration and prevent blade cracking by stabilizing airflow.

A rotor blade extension fitting element uses a positive-locking connection to join the original tip and the new shell.

Segmented drain holes in the intake duct bottom surface discharge condensation water externally, preventing accumulation that damages the compressor.

Segmented labyrinth channels distribute coolant flow to prevent stagnation and maintain mechanical strength under high operating temperatures.

Thermoforming a honeycomb core sandwich panel with overmolded mounts reduces cycle time and cost.

Flexible brush bristles adapt to thermal expansion gaps between the rotor and stator, reducing fluid leakage across varying temperatures.

A turbine wheel groove design uniformly distributes centrifugal force on fixation wires to enhance component durability.

Segmented tip shroud cavities fluidly couple distinct edge portions, reducing manufacturing complexity while enabling post-service modifications.

Specific fan blade tip angles direct bird strikes to the leading edge, improving reliability while reducing weight and complexity.

Automated deposition apparatus moves machine heads along multiple axes to fabricate composite rotor blades.

An elbow segment redirects coolant near the airfoil tip, discharging it at a shallow angle to minimize aerodynamic mixing losses.

External bonding element bridges pressure-side and suction-side conductors around the profile end edge to equalize potential and reduce flashover risks.

A turbine bucket airfoil profile defined by specific Cartesian coordinates to enhance gas turbine efficiency.

Segmented caps linked by spoolie jumper tubes eliminate rigid weld fatigue and piston ring wear while stabilizing rotor cavity temperatures.

Concurrent injection molding merges separate core components into one structure, reducing assembly time and positioning tolerances.

V-blade fittings engage V-grooves in a ducted fan case to retain engines under torque while enabling rapid disassembly for maintenance.

A segmented rotor blade component uses connection interface recesses to mount individual segments on a test stand for independent fatigue evaluation.

A dual-feed airfoil cooling circuit uses co-fed and counter-fed pathways to optimize coolant flow distribution.

Specific axial and radial spacing between the annular splitter and fan blade platform reduces foreign object debris intake into the compressor section.

Optical triangulation captures 3D groove geometry to document wear and deformation in gas turbine rotors.

Sand-prepared polyurethane primer and nanoparticle topcoat resist rain erosion and ice adhesion, preserving aerodynamic efficiency.

A scalloped turbine platform with a dedicated purge trough channels cooling gas along the airfoil junction to minimize core flow mixing.

Pin-fin micro-channels in a turbine blade trailing edge increase heat transfer area and reduce thickness, minimizing aerodynamic losses.

Radially arranged unit blades feature grooves that temporarily hold injected fluid for extended inertial force application.

A hybrid airfoil cooling circuit merges impingement and serpentine paths to direct cooling air across the turbine blade.

Separate ceramic matrix composite shells with a clamping member reduce interlaminar tension stresses and improve attachment strength.

A rotor blade root spacer uses a cellular structure to absorb impact energy through controlled deformation.

Offset unit cells increase moment of inertia to resist bending moments, reducing displacement and buckling under compressive forces.

A hollow steel spreader box filled with grout distributes tower loads to embedded foundation bolts, resolving strength limits in larger wind turbines.

Protective caps shield pultrusion ends from heat damage during plasma treatment, preventing delamination and preserving structural integrity.

A composite airfoil assembly features a bulbous root shape coupled to an interdigitated rotor structure.

A turbomachine places two electric machines in series with a reduction gear to transmit power from the engine shaft.

A mechanical arm with a torqueing tool removes hub fasteners, resolving tight clearance access and personnel safety risks during maintenance.

A long-arm flange connects and supports thin-walled gas turbine engine sections.

Variable thickness dovetail and spacer system distribute centrifugal stress while allowing passive blade tip clearance adjustment for impact resistance.

An integrated flange projection on a segment base body reduces welding deformation and improves dimensional accuracy in steel tower assembly.

Asymmetric vane geometry redirects airflow to generate a vertical thrust component that counteracts the nose-up pitch moment caused by high-mounted engines.

Curved shaped cooling pins reduce stagnation regions and particle accumulation, preserving heat transfer area in gas turbine engines.

Ridged abradable material on the inner shroud reduces hot gas leakage over blade tips while limiting wear through controlled contact.

Leaf spring retention element keeps pressure relief door open to enable visual detection of burst duct events without manual reset.

Curved blade tips minimize bending oscillations, enabling stable rotation at 111 kHz.