Engine Manufacture TRIZ Cases

Lattice venting line maintains flow velocity while containing oil fires to reduce jet engine weight.

A wind turbine rotor uses dynamic pitch control to adjust blade angles for optimized energy capture across varying wind speeds.

A monopropellant injection device uses a movable annular section to modulate flow rate through mechanical displacement.

Triangular tip shelves on gas turbine airfoils reduce fluid leakage and thermal fatigue while lowering cooling fluid flow requirements.

Integrating aerodynamic flow distribution with structural support reduces part count and radial envelope in aircraft engines.

A turbine blade tip pocket features a pressure side reinforcing bump that increases peripheral wall thickness and stiffness.

Centrifugal force pushes the spoiler against blade platforms, compensating for ceramic matrix composite manufacturing tolerances and reducing radial stress.

A tower-mounted positioning tool uses linear actuators to tilt and translate heavy wind turbine blades, eliminating complex crane requirements.

Internal transport system delivers tools to remote turbine arms, eliminating external access needs.

An integrated turbine bearing merges nozzle guide vanes with air bearings to reduce cooling air consumption while maintaining rotor speed.

Housing blocker doors and linkages within a forward cavity eliminates airflow disruptions and drag caused by exposed components.

A compact compound engine assembly uses a radial firewall to separate hot turbine sections from cold compressor zones.

Hardening liquid shims fill gaps between pin joint slots and bearing blocks, preventing bushing rotation under operational loads.

A self-climbing crane system uses radial beams to grip tower rings and hoisting winches to ascend vertically.

Controlled lubricant dispenser maintains gear lubrication during autorotation by switching configurations to prevent vacuum formation.

A dual contour nozzle combines an inner conical section with an outer bell contour to expand exhaust gases across varying flight regimes.

Prefabricated sealed caisson hydroelectric plant transported to sea base for rapid immobilization and pipe connection, reducing terrestrial site constraints.

A rotatable exhaust plug liner adjusts the cross-sectional area of the exhaust pathway in a gas turbine engine.

Five alternating bulges on a turbine guide vane shift eigenfrequencies to prevent vibration damage.

Pultruded rods in a segmented mold maintain circular shape during vacuum infusion, reducing deformation and stress at the blade root connection.

An axial turbine diffusor with non-constant opening angle and axial waste-gate injection reduces turbulence and improves pressure recovery.

A hollow multi-beam wind turbine blade structure using segmented carbon fiber crossbeams to reduce mass while maintaining structural rigidity.

Resupply holes link airfoil and platform skin cooling passages to the main core circuit, reducing pressure losses while sustaining convective heat transfer.

A manufacturing method segments existing turbochargers and generators to build cost-effective micro gas turbines.

A component platform lock uses expanding collets to secure wind turbine blade components during assembly.

Segmented microcircuits in a refractory metal core create serpentine pathways that boost convective efficiency while reducing cooling fluid flow by 40%.

Dual apertures spaced along the camber line eliminate stagnation zones and ensure effective cooling with minimal air.

Segmented core cavities and a cover plate direct cooling airflow to reduce thermal stress on gas turbine platforms while managing structural complexity.

An oil discharge passage with varying cross-sections directs lubricating oil flow to prevent reflow, reducing viscous resistance and rotational losses.

A series of rotating blades mounted on a translating runner blocks the bypass air stream to generate counter-thrust while minimizing weight and obstruction.

Segmenting the chevron into modular elements reduces manufacturing complexity while maintaining structural rigidity and aerodynamic performance.

Coupling a positioning rotary device to an auxiliary drive eliminates complex switching mechanisms while ensuring reliable rotor alignment.

Curved supporting flanks distribute mechanical stress uniformly across the bearing surface, resolving non-uniform load issues from manufacturing variances.

Shaft grooves create a self-supported lubrication system that eliminates auxiliary oil pumps, reducing parasitic energy loss in downscaled gas turbines.

A variable area bypass nozzle with a twin stream impeller resolves back pressure issues during off-design conditions by dynamically adjusting flow area.

Radial extension fins on a gas turbine seal seat dissipate heat to prevent non-uniform temperature gradients at the sealing interface.

Passive inner casing mechanism adjusts axial position via pressure differentials and biasing springs.

Mounting a service crane on the rotor hub eliminates time-consuming ground assembly while preserving critical nacelle workspace.

Elongated reinforcing members with conical heads enable secure screw connections through the blade shell.

Alternating bounding and common pedestals define branched cooling passages that merge to direct convective flow across gas turbine component walls.

Wire mesh members frictionally engage turbine nozzle openings to damp mechanical oscillations without adding mass.

Protruding alignment tools and guide pins fix rotational position to eliminate manual intervention risks.

A radial wall trough configuration with camber-matching curvature modifies boundary layer flow to suppress vortex generation near blade pressure surfaces.

Replacing nickel with MAX phase composites in gold alloys eliminates allergic reactions while maintaining mechanical strength.

Asymmetric tower design reduces material usage and weight while maintaining structural stability against predominant wind direction.

Actuated jaws and hooking members secure the tower to a crane vessel, maintaining upright position stability against wave forces during deep water assembly.

Reducing the axial width of a static nozzle airfoil at the midspan concentrates fluid flow away from high-loss endwall regions, improving turbine efficiency.

A turbomachine shaft uses a midshaft rating between 200 and 300 ft/sec half-power to shift critical speeds away from operating ranges.

Variable-pitch outlet guide vanes adjust airflow direction to mitigate fan blade forcing, stall, and flutter caused by intake pressure fluctuations.