Engine Manufacture TRIZ Cases

Sockets and spacer studs secure composite bypass turbomachine panels without bosses, cutting mass and manufacturing complexity.

Switchable hydraulic motor series and parallel modes let a wind turbine turner gear match torque and speed for unbalanced rotor blade installation.

Bridges between adjacent blade preforms raise rigidity during finishing, cutting chatter so blisks can be machined faster with high accuracy.

A blade tip support and lifting line suspend a jointed wind turbine blade tip for servicing without large ground cranes, reducing time and cost.

Pressurized fluid actuates a biased link to remotely disconnect jack conduits while preventing spillage in submerged structures.

Tilting the wind tower vibration damper into a compact transport state enables safer removal through standard openings after nacelle installation.

Placing the welded bush joint in the axial lubricant groove helps form a uniform oil film, reducing wear in wind turbine gearbox slide bearings.

A two-bolt fastening layout secures heavy gearbox parts and still releases a pin after plastic deformation causes jamming.

A multi-shaft bevel gearbox and adjustable bearing housing shrink gas turbine nacelle size while preserving accessory drive alignment.

A shaped baffle channel and deflecting surface redirect rotating oil outward, improving bearing chamber drainage and reducing compressor leakage.

Segmented nacelle receptacles and gravity-fed channels contain leaked oil and coolant without pumps, helping prevent offshore pollution.

Offset support members and a lifting apparatus let wind turbine gearbox housing sections be repaired uptower without a large ground crane.

Curved rails guide a cutting device to scarf rotor blade segments at the required angle and curvature, cutting time and joint errors.

A semi-submersible platform is assembled in shallow docks, then floated out for deep-water mooring to cut foundation cost and weight.

A serpentine ply wrapped around radial tubes redistributes thermal and pressure stress in CMC turbine airfoils to protect exterior coatings.

A curved-fold heating blanket fits blade tip geometry without wrinkles, improving heat distribution and reducing thermal damage during shell bonding.

A bushing-stud fixing lets composite bypass turbomachine panels mount without bosses, cutting mass and manufacturing complexity.

A mobile ring-shaped housing enables controlled on-site welding of wind turbine sections, cutting flange weight and factory infrastructure needs.

Mechanical interlocking and fill material let turbine airfoil joints open cooling paths at interface discontinuities while preserving strength.

Inclined serration teeth on a turbine engine flow splitter cut broadband noise while limiting aerodynamic losses and flow disruption.

Resilient members between guide vane bushings and casing pockets damp vibration, reduce wear, and accommodate thermal growth.

Radial boss orifices place oil closer to sun and satellite gear teeth, overcoming centrifugal effects while simplifying nozzle assembly.

Convex-concave inlet shaping helps pre-swirl nozzles suppress flow separation, raise swirl, and improve turbine cooling efficiency.

A cured fluoroelastomer patch with fibrous reinforcement restores eroded rear cone coatings and extends jet engine component life.

Rotating, translatable pillars and receptacles let a wind turbine gearbox be aligned and moved inside the tower without crane removal.

A valve-guided turbine assembly enables in-pipe power generation in pressurized conduits without shutting off water or cutting out pipe sections.

Multiple machining paths tailor blade shroud thickness by region, improving stress distribution, creep behavior, and weight control.

An anti-rotation spacer locks the retaining ring and lubricant deflector to the bearing housing, improving clocking alignment and oil flow.

A built-in lubrication channel and dispersion cone atomize oil into a mist, cooling ball bearings while removing cross-drilling complexity.

Circumferential barrier strips between the face sheet and containment doubler extend fragment interception in aircraft inlet cowls without added weight.

Coordinated workpiece rotation and axial laser motion enable homogeneous hardening of large rolls and cones without gaps or hardness traces.

A two-part bearing outer ring centers the housing flange between connections to reduce bending moments and improve load transfer in gas turbines.

A hollow ribbed connector enables radial elastic deformation to relieve CMC-metal thermal mismatch while maintaining precise turbine ring installation.

Radially protruding longitudinal flange pairs replace hard-to-weld T-joints in wind turbine tower sections, cutting testing and welding effort.

Mounting the blade root first and adding the extension later reduces gearbox torsional loads and widens the wind window for turbine assembly.

Tapered pins self-align wind turbine components, cutting bolted connection count, easing tolerances, and speeding assembly and maintenance.

A worm wheel that also serves as the epicyclic ring gear cuts speed in compact thrust reverser actuators without exceeding shaft design limits.

Tilting the wind tower vibration damper into a transport state cuts horizontal size for safe removal through standard openings.

Mounting equipment on the planet carrier bearing lets the ring gear carrier drive its rotor, shrinking the AGB box without enlarging the nacelle.

A wedge-and-cap bolt joint for modular blades achieves precise preload in tight spaces while reducing force, preload loss, and maintenance.

Localized internal ribs stiffen a gas turbine rotor shaft at key compressor stages, cutting weight 10% while maintaining bending stiffness.

Heavy damper units are moved and mounted inside a horizontal wind turbine tower section, improving vibration control while reducing lifting risk.

A tangentially movable coupling locks and releases a wind turbine rotor with precise positioning, lower maintenance effort, and hydraulic safety retention.

A tooth protrusion keeps curvic coupling halves engaged after tie rod breakage, inducing tilt and friction braking to limit turbine overspeed.

A hollow flanged shaft connector replaces heavy shrink discs to transmit torque with easier maintenance, inspection access, and load monitoring.

A semi-annular retaining ring uses anti-rotation tabs and recessed inner sections to ease turbine assembly installation while lowering radial loads.

Sliding-material bolt threads prevent galling in steel blade flange sleeves, avoiding lubricant residue while keeping strong rotor blade joints.

A holder-mounted sealing body lets pump check valves be removed through the closure body, reducing pressure risk and eliminating a separate filling opening.

Segmented mounting structures absorb fan blade out shock loads via mechanical fuses, protecting gearbox integrity.

A thrust reverser scoop with a serrated leading edge directs airflow into cascade flow passages to enhance fluid momentum.

A monolithic duct structure integrates inlet, transition, and bypass sections into a single body to simplify aircraft propulsion assembly.

A turbine exhaust strut airfoil profile removes residual swirl from hot combustion gases to enhance axial thrust production.

A turbine blade features a chamfered trailing edge surface paired with a thermal barrier coating to manage heat transfer at the tip.

Dual-layer cap with spaced metal sheets absorbs lightning energy to protect the blade structure from erosion and strike damage.

Spacers define a gap to control fluid flow and ensure uniform coating thickness, resolving uneven repair defects.

A turbine housing diffuser space directs exhaust gas flow toward axial ends to prevent cross-volute interference.

Cooling pins in the intermediate carrier conduct air to reduce thermal stress and leakage between ceramic blade tracks and metallic carriers.

Radial pushers on a shaft align deformed flange holes to reduce crane dependency and assembly time.

Strategic chevron placement at bend apices reduces flow separation and pressure losses in gas turbine engine cooling passages.

Segmented internal channels direct coolant through dedicated body and rail circuits, reducing tip temperatures while minimizing parasitic fluid losses.

A segmented anti-rotation tab prevents seal rotation in gas turbine engines, maintaining clearance integrity while allowing axial thermal expansion.

Axial and circumferential cooling channels in a gas turbine ring segment intensively cool high-temperature regions, reducing compressor air extraction needs.

Angled divider walls within a turbine blade root cavity direct cooling airflow to enhance structural stiffness.

A one-piece lightning receptor base with internal threads secures receptors on wind turbine rotor blades.

A retention device adjusts cooling tube position via threaded mechanisms to minimize wear risk while maintaining optimal clearance against the casing.

An elliptical piccolo tube directs heated fluid to impinge on an aircraft inlet lip, resolving uneven ice removal caused by circular tube designs.

A thermoforming system shapes flat thermoplastic sheets into curved rotor blade components using rollers and resin infusion.

Protrusions on a gas turbine heat sink surface enhance convective cooling efficiency while forming integral part identifiers to reduce weight.

A tapered radial cooling passage increases coolant Mach number toward the tip, preventing base overcooling from strong secondary flows.

Defining the airfoil geometry via precise X, Y, Z coordinates resolves aerodynamic efficiency and positional stability trade-offs.