Turbines TRIZ Cases

Rotating the scroll with a stationary cutter eliminates high-hardness tool requirements, reducing costs and machining periods.

A support element with a controlled gap limits roughness on downward-facing surfaces by restricting powder interaction, reducing deformation.

Nested acoustic resonator cells reduce required liner depth while maintaining absorption bandwidth in gas turbine engine airfoils.

Silicon-free nickel germanium boron braze alloy creates ductile joints by preventing brittle intermetallic phase formation at elevated temperatures.

A spherical articulating fixture holds gas turbine components in any orientation to enable precise braze paste application.

An additive manufacturing process creates an integrated 3D lattice structure that reduces handling complexity while maintaining structural integrity.

Strategic apertures and pins in a turbine cooling article manage cross-flow effects, reducing compressed air usage before the combustor.

A laser-line imaging subsystem projects a line onto workpieces and captures the optical image via triangulation to compute three-dimensional coordinate points.

Measuring actual geometry data sets enables precise 3D article manufacturing without parametric CAD models, reducing material loss and repair costs.

Pulsed current MIG welding deposits filler metal on aluminum turbine components, minimizing heat affected zones and preventing hot cracking.

Preserve a trace of the original anti-wear layer on gas turbine blade shrouds to prevent fault propagation and maintain substrate integrity.

Optimized chromium and cobalt content in the alloy powder resolves high-temperature cracking while maintaining oxidation resistance.

A digital model modification adds sacrificial balancing portions to redistribute residual stresses during additive manufacturing of asymmetric components.

Segmenting convective and film cooling via an insert resolves limited hole length from reduced wall thickness, improving film cooling effectiveness.

Silicon-modified aluminide seals turbine nozzle slip joint clearances, preventing hot gas ingestion while fracturing to permit relative radial movement.

A hafnium-bearing superalloy composition enables precise carbide formation during additive manufacturing layer-by-layer solidification.

A sintered preform process fills openings in high temperature components using diffusion brazing.

Applying a braze paste over existing bond coatings eliminates stripping steps, reducing gas turbine modification time and cost.

Segmenting the rotor blade allows additive manufacturing to extend internal cooling features, reducing component density while maintaining structural integrity.

Segmented chambers maintain inert atmospheres to prevent superalloy oxidation during welding, resolving batch furnace delays.

Selective shielding resolves non-uniform heating in gas turbine components, improving braze joint quality and throughput.

Effusion passages permeate the shroud thickness to form a protective film, reducing temperature without sacrificing engine efficiency.

A frustoconical inner surface on a protective bell aligns with the spray nozzle to create a stable inert gas enclosure.

An aircraft lubrication system uses an oil-driven generator and electronic card to power sensors for autonomous parameter monitoring.

Replacing mechanical cables with magnetic mirror actuation resolves slow response times and positioning inaccuracies in boroscope laser processing.

Diffusion bonding a TiB particulate-reinforced band to a titanium disk increases tensile strength and fatigue resistance at high rotational speeds.

Segmented curved magnets guide electric arcs along mating surfaces, resolving uniform heating challenges in complex curvature welding.

Laser cladding repairs larger turbomachine damage up to 6 mm while minimizing thermal stress and preserving metallurgical bond strength.

Dynamic laser power and scan speed adjustments produce larger rim grains for creep resistance and smaller hub grains for fatigue performance.