Engine Fuctions TRIZ Cases

An inlet orifice on the blade root forward face directs cooling air through a serpentine passage to reduce thermal loads and stress concentrations.

Adjustable radial locators center the bearing housing within the outer case, resolving tolerance stack-up from multiple components.

Segmented continuous cooling channels featuring rib protrusions enhance convection and turbulence to manage high thermal loads in gas turbine engine airfoils.

Spring portion positively locates seal member axially to damp vibrations between gas turbine vane segments.

A relief valve uses a moveable separation member to expand fluid chambers and vent fuel, maintaining high flow rates in stiff systems.

A tangential onboard injector system radially supports turbine vanes while distributing cooling air through an annular plenum.

This method resolves monitoring complexity during cold start by converting numerical parameters into intuitive visual trajectories on an operating line diagram.

A turbomachine monitoring method identifies the ignition instant by detecting a break point in engine speed variation within a bracketed time zone.

A tensioner nut with reversed threads secures a gas turbine engine shaft, enabling rear access assembly that eliminates front dismantling.

Non-linear perforation spacing in an aircraft acoustic panel resolves the trade-off between sound attenuation and aerodynamic drag.

Integrally formed inlet attachment flanges eliminate mechanical fasteners and reduce nacelle weight.

A turbomachine discharge valve uses cylinder position data to estimate the closing dead zone without individual testing.

Merging separate radial passages into one forced vortex passage suppresses rotor shaft elongation and maintains aerodynamic performance.

Integrating the ramp with the outer shroud reduces nacelle thickness and component count while maintaining structural stability.

Centrifugal acceleration device moves oil radially outward to prevent undersupply at planet wheel bearings.

Reverse flow from a rear plenum through interspaced apertures maintains pressure for effective turbine stage cooling.

Segmented baffle portions connected by a central joint accommodate thermal growth while maintaining constant offset for effective impingement cooling.

A gas turbine engine heat exchanger merges cooled airflow with dirty air from a particle separator to enable efficient thermal exchange between streams.

Interlocking mechanical joints join ceramic matrix composite shroud segments, replacing brittle bond lines with damage-tolerant mechanical interlocks.

Plant control apparatus manages inlet guide vane angles to execute a controlled heat soak process for steam turbines.

A variable displacement piston pump with a compensator valve dynamically adjusts discharge pressure to minimize fuel self-heating in gas turbine engines.

One-piece cast mid-turbine frame with internal cooling passages manages thermal loads in gas turbine engines.

A vent passage connects the turbocharger center housing oil cavity to the engine internal volume.

Bi-directional piston mechanism captures both wave curve phases to double energy output while maintaining continuous operation without complex control systems.

Segmented conical frames distribute loads across spaced bearing units, cutting rotor mass without sacrificing stiffness.

Segmented airfoil skin core cavities segregate cooling flow to reduce metal temperatures and extend part life.

Bypass coolant passage guides fluid through perforations without entering the resonator chamber, preserving acoustic admittance while cooling the liner.

A bleed flow assembly recaptures energy from extracted gas streams to drive auxiliary loads.

Embedded environmental barrier tubes in ceramic matrix composite airfoils create cooling passages for gas turbine engines.

Control system compensates for transportation delays between valve adjustments and intake manifold response using non-linear algorithms.

Electric motor decouples low-pressure compressor from turbine to resolve speed ratio constraints and improve specific fuel consumption.

A segmented degasser with a central pinion web blocks oil film discharge through axial inlets, reducing turbomachine oil consumption.

Pins insert into carrier grooves to fix the thrust collar, preserving sliding surface area and preventing scratches under high loads.

Radially inward cooling passages extend from a platform shank pocket to cool airfoil regions inadequately addressed by trailing edge apertures.

Segmented balance weights interlock with rotor components to adjust mass distribution, eliminating labor-intensive hard balancing and reassembly.

Radial arms integrate Helmholtz resonators to reduce fan noise at 2000-3000 Hz without increasing casing mass.

Progressive divided flow circuits distribute fluid streams across segmented sections, reducing weight and pressure drop while maintaining structural integrity.

A flexible support structure with specific transverse stiffness ratios isolates gears from maneuver loads.

A non-recuperated sCO2 Brayton cycle uses primary exhaust heat to convert insufficient aircraft thermal energy into gaseous natural gas for combustion.

Protrusions on fiber-reinforced airfoil rings form a toothed exit slot that emits cooling air, mitigating thermal stress in ceramic matrix composite structures.

Clamping plate assembly manages differential thermal expansion between housings, reducing mechanical fatigue in fasteners and preventing corrosion exposure.

An asymmetric inlet particle separator uses a tortuous duct path to remove contaminants from gas turbine engine airflow.

Higher expansion holder elements compensate for differential thermal growth between metal flanges and CMC sectors, maintaining positioning stability.

A coaxial shaft assembly connects the fan and fixed blades to enhance structural rigidity in aircraft propulsion units.

A radial pin fixing device with a flange and seal unit secures rotary machine components without welding.

Embedded receptacles in a blade root flange align hub fasteners, reducing weight-induced deformation during storage.

A segmented sealing sheet with embedded steel cables anchors to elastic elements to maintain fluid-tightness across large hydraulic pistons.

Segmented sensors measure gear and shaft angular positions to calculate torque, resolving the trade-off between measurement precision and device complexity.

A rotor turn drive bracket with a sprocket and chain enables manual rotation of the generator shaft.