Engine Manufacture TRIZ Cases

Segmenting the inlet geometry resolves sidewash misalignment, reducing fuel consumption by 0.2 percent.

Independent door deployment achieves aerodynamic matching without synchronized mechanisms, improving deceleration performance.

Rotating the load carrying structure approximately 180 degrees aligns components for single-crane lifting, reducing installation costs and unbalanced loads.

A turbine blade airfoil surface defined by scaled Cartesian coordinates to optimize the external profile geometry.

A buffer fluid delivery system provides redundant air supply routes to gas turbine engine shaft seals.

A stabilization beam on the blade holder contacts a rotor hub guiding element to constrain oscillations and reduce manual aid needs.

Parallel corrugated surfaces on a turbine blade reduce aerodynamic losses by promoting efficient wake mixing without increasing manufacturing complexity.

Submersible pump with lateral deflector plate generates swirling flow to harmonize water temperature and oxygen content across all strata.

Tapered pultruded composite strips distribute stress over a larger area to eliminate abrupt termination failures in wind turbine blades.

A turbine rotor blade airfoil shape defined by Cartesian coordinate values optimizes aerodynamic performance across scalable designs.

Curved rib profiles alleviate thermal expansion stress concentrations while maintaining high cooling efficiency in turbine airfoils.

An elastomeric damper nested within a link structure absorbs vibrational loads to protect gas turbine bleed valve components from damage.

A wind turbine apparatus with a load bearing means and raising mechanism for yaw brake calipers.

Interlaced trip strip arrays enhance turbulence within gas turbine airfoil cooling channels to boost convective heat transfer coefficients.

Axial engagement of arcuate restraining member with periphery locking element eliminates radial play and secures rotor against high torque loads.

A cam-driven blade array redirects bypass flow via translation and rotation, reducing system mass compared to traditional complex reversal mechanisms.

Actuator modulates blade outer air seal position to control turbine clearance.

Segmented ceramic matrix composite platforms with air gaps block hot gas radial movement toward the metallic disk, reducing thermal transfer.

Flared tip geometry directs cooling medium through a recessed cavity to reduce trailing edge surface temperatures.

Openable covers on drainage slots allow controlled liquid removal from an acoustic panel without compromising noise attenuation during freeze-thaw cycles.

A mobile gas turbine power generation system with a swappable transmission device for mechanical and electrical loads.

Pre-aligned stack arrangement prevents gravity-induced slippage on inclined molds during spar cap manufacturing.

Threads on the turbine wheel back surface block exhaust air leakage from high-pressure to low-pressure scroll passages, restoring turbine efficiency.

External retaining ring radially secures blade roots within segmented drum rotor, reducing moving mass while maintaining retention reliability.

A turbine bucket features a non-axisymmetric base contour to optimize fluid flow dynamics and enhance aerodynamic performance.

A cryogenic liquid turbine uses a cold barrier structure and diffuser pipe to manage thermal transfer and fluid dynamics.

Strain isolation pad and bonding layer reduce mechanical stresses in gas turbine exhaust ducts while maintaining structural integrity.

Adjustable bracing bars with low friction surfaces constrain cable bundle movement to reduce momentum and force transmission through yaw deck openings.

Offset attachment locations allow radial displacement to compensate for thermal expansion between engine components.

Strut lug mounts with upstream recess positioning optimize airfoil shape and mount geometry to reduce pressure losses in gas turbine engines.

Flexible coupling attachment absorbs thermal expansion while CMC lobes improve airflow mixing, reducing noise and increasing thrust.

Internal walls in a drainage mast cavity retain drained fluids, preventing discharge when the nacelle cowl opens.

Segmented trailing edge ejection holes with radiused inlets and metering sections manage extreme temperature differences across turbine blades.

Conic fillets increase strength and cyclic life in compressor sections without adding aerodynamic interference through optimized curvature.

Internal gas injection boxes in a bifid exhaust nozzle deflect thrust for precise yaw control while minimizing radar detection risks.

Decreasing radii in the platform undercut reduce stress concentrations at the airfoil interface, mitigating thermal mechanical fatigue.

Pre-formed flexible mounting bands adapt to rotor blade shoulder curvature, eliminating complex multi-part assemblies and reducing maintenance downtime.

Groove cavities between wind turbine blade shells guide adhesive injection, reducing excess material usage and weight while improving bond line control.

An inner shroud damper absorbs high energy oscillations through inertial mass elements coupled to the carrier structure.

Segmented cooling fins with apertures control thermal expansion in blade outer air seals, reducing weight and maintaining tip clearance.

A movable mixer fairing alters nozzle geometry to balance high airspeed efficiency against fan surge risk, maintaining optimal working lines.

Separate ceramic matrix composite platform and pin reduce thermal transfer to the blade root while simplifying manufacturing complexity.

A turbine blade platform edge features a stepped region merging into a beveled region to protect sealing slots during manufacturing.

Concave pockets paired with angled knife edge seals create vortices that block combustion product leakage past the seals.

Segmented trip strips with varying orientations in turbine blade cooling passages reduce pressure drop while maintaining effective heat transfer.

A delaminating wear indicator captures blade tip clearance through material removal on a gas turbine engine component.

Pre-formed outer damper face geometry establishes hot assembly sealing through thermal expansion.

An airfoil design applies a variable elliptical arc at the trailing edge to balance aerodynamic efficiency with structural robustness.

A radial turbine blade tip features concave and convex suction surfaces to manage clearance flow separation angles.