Blade Accessories TRIZ Cases

See how a single-stage radial turbine with optimized pressure ratio and dimensionless speed rep

See how a hybrid exchanger converts waste stream pressure and heat to electrical energy using t

See how heated humidified gas removes polymer coatings from ceramic fibers more efficiently tha

A low-pressure CO2 cycle uses a single-stage radial turbine and bearing-less diffuser to cut turbine cost while maintaining efficient power generation.

Layered puncture-resistant and energy-capture materials help turbine containment cases stop fan blade impact while cutting weight.

Rotating airfoils with embedded magnetic elements induce current in a circumferential winding, adding onboard power without larger generators.

Rotating airfoil magnetic elements induce current in a stationary winding to generate onboard engine power without larger generators, added weight, or drag.

A removable gearbox mounted to the fixed case keeps the gear assembly close to the main shaft, easing service while reducing size and losses.

A low-heat first weld pass followed by a higher-heat layer tempers the HAZ, speeding steel alloy repair while avoiding post-weld heat treatment.

FAST bonding joins cast replacement sections to damaged gas turbine parts with crystal matching, reducing cracking and preserving superalloy performance.

Finite element modeling screens IBR stack repairs against structural and aerodynamic criteria, reducing unnecessary scrapping.

A two-layer weld repair uses low then higher heat input to temper the HAZ in CrMo steel parts, cutting distortion and post-weld heat treatment.

A thin GTAW repair layer followed by GMAW tempers the hardened HAZ in CrMo and CrMoV components without furnace treatment.

A hydraulic tool uses a blocking pin and catch plate to separate seized gas turbine nozzle segments in tight casing clearances for faster removal.

A polymeric abrasive tip with hard particles and low thermal conductivity limits heat transfer, helping prevent adhesive softening and delamination.

FAST bonds cast replacement sections to damaged superalloy parts, reducing cracking and restoring repair yield in large damage zones.

A plenum-fed atomizing nozzle sprays ceramic-liquid droplets through a turbine case hole to restore internal coatings without disassembly.

Finite element and aerodynamic analysis identify repairable IBR defects that meet operational criteria and reduce unnecessary scrapping.

A hook-and-drawing mechanism pulls rotor blades axially from the disk, avoiding casing opening and reducing inspection steps.

A metal oxide layer lets lasers mark brittle CMC surfaces without direct damage, preserving optical contrast in high-temperature service.

Sensor, inspection, and virtual model data predict damage and guide additive or subtractive repair of turbine components before failure.

A gearbox removably fixed to the case keeps pinion-shaft alignment while simplifying maintenance and reducing turbomachine footprint and losses.

A horizontal clamping fixture and software-guided electrode holder automate vane slot EDM repair with repeatable positioning and no manual reset.

A mobile tool with C-axis arc guidance and radial adjustment machines turbine segments in situ, avoiding disassembly and cutting maintenance time.

A tip shroud datum surface guides PSP machining directly, avoiding transformation errors and improving turbine blade repair accuracy.

A staged HIP, heating, cooling, and two-step aging process restores DS superalloy creep strength and ductility while limiting melting and cracks.

A tongue-and-groove ring fastener maintains full circumference support while accommodating thermal expansion and resisting twist-induced instability.

A combined HIP and eutectoid heat treatment cuts cycle time and aluminum loss while forming gamma-rich TiAl bars for turbine blade machining.

An untethered maintenance robot moves on rotor or stator surfaces to repair turbine damage in situ, avoiding tether jams and factory outages.

Filler deposition restores damaged turbomachine air intake lips locally, cutting aircraft downtime and avoiding full replacement.

A rail-guided carriage and fastening system machine annular turbomachine flanges in place, restoring profile without dismantling.

FAST joins a replacement leading-edge component to a turbine airfoil to restore wall thickness, recover strength, and extend blade service life.

A sealed powder-filled damper adds mass without losing flexibility, improving rotor vane platform contact, vibration damping, and wear resistance.

An undercut near the shaft interface lets an aircraft engine rotary part deflect under heat and centrifugal load, stabilizing fit and reducing vibration.

Backside support stabilizes the clamped workpiece span in pECM, countering electrolyte forces to improve material removal accuracy.

Targeted endwall depressions and thickened areas cut secondary-flow losses and widen turbomachine operating range.

A high-Tg polymeric matrix in the abrasive tip cuts heat transfer during seal rubbing, reducing delamination and protecting blade-tip wear life.

Extensions on a spherical closure element let braze seal irregular internal passages, avoiding custom ball delays and poor seating.

A portable guided milling tool restores circumferential gas turbine brush seals in place, avoiding seal removal and reducing shutdown time.

Separating the hub, flowpath ring, and blades enables inspection before friction-welded assembly, cutting rotor defects and waste.

A recessed guiding tool with adjustable fixation and rollers controls trimming depth on wind turbine blades to avoid surface damage.

Repairs damaged wind turbine blade leading edges with conductive, erosion-resistant materials to restore lightning and wear protection.

A preloaded spline interference fit lets a composite gas turbine shaft survive ultimate loads without separation, debris release, or all-steel weight.

Triple smelting and tight nickel superalloy composition control prevent mixed crystals in integrated turbine discs, improving durability and LCF.

A bendable endoscopic shaft reaches engine blade leading and trailing edges through a lateral port, enabling in-situ surface repair without dismantling.

Ultrasonic vibration through a rolling tool imparts compressive stress in thin-walled components while avoiding geometry deformation.

Surface geometry and scale data are combined to calculate rotor blade moment weight accurately without fixture positioning errors.

Concurrent roller vibration and pressure impart compressive stresses in thin-walled components while preserving geometry and fatigue life.

Angled layer deposition and machining rebuild overhung blade sections that vertical build-up cannot form, extending turbomachine part life.

Angled material layering and machining rebuild turbomachine overhung sections with accurate geometry, extending part life without replacement.

Machining out a stressed airfoil fillet and inserting a higher-property plug helps resist creep cracking and extend turbine component life.

TLP and PTLP bonds with thermal protection structures join dissimilar engine materials while limiting thermal strain and cooling demand.

A blocking pin and hydraulic cylinder separate seized turbine nozzle segments inside cramped casings, easing safe removal and maintenance.

A burnished chromate-free repair coating restores corrosion resistance on turbine components while staying compatible with legacy Cr(VI) layers.

Controlled beta-stabilizer additions and heat treatment improve thick-section strength, fatigue resistance, and FOD deformation in turbine alloys.

FAST heating and pressure restore turbine blade leading edge wall thickness, enabling more repair cycles and lower replacement cost.

Defect scanning and rotor simulation identify repair paths that preserve structural and aerodynamic performance while reducing IBR scrap.

Coating vane singlets before FAST joining preserves TBC coverage while forming doublets that reduce leakage and avoid higher costs.

A boxed damper with adjustable powder mass separates weight from flexibility, improving rotor vane vibration damping in tight platform spaces.

Mechanical vibration and combined axial-circumferential force let interlocked turbine blades be installed or removed without major turbomachine disassembly.

A monoblock gas turbine hub integrates rings, cross members, and stiffening features to cut assembly time, cost, and machining needs.

A C-shaped shim wraps turbine disk tooth side walls and rim to stop shim disengagement, limit wear, and reduce rotor repair needs.