Engine Fuctions TRIZ Cases

A flexible support structure lowers transverse stiffness to isolate vibrations from the main engine casing.

A bearing hub design uses a spring arm to convert radial vibrations into axial motion for damping.

Radially oriented cooling conduits deliver fluid from the plenum to the wheel space, reducing stress and low cycle fatigue in the unaligned fillet region.

Strategic tabs widen the seal to prevent fall-out during cooling contraction while maintaining integrity against crushing during heating expansion.

Segmenting the cooling circuit into independent legs optimizes air distribution to resolve high tip temperatures and insufficient cooling effectiveness.

A turbine ring assembly uses transverse pins and radial springs to secure ceramic matrix composite sectors within a metal support structure.

Stacked planetary gears transmit low-speed torque from an electric motor to prevent rotor bowing and protect pneumatic starters.

Cutting and replacing the closing plate extracts debris without stripping the thermal barrier, preserving blade dimensions.

An airfoil stop on the core engine shares high-pressure airflow loads with the structure, reducing actuation system weight and complexity.

Prefabricated spar panels join to form segmented wind turbine blade modules, enabling parallel production and on-site assembly of large blades.

A thermal transport bus uses deoxygenated fuel as the heat exchange medium to remove accessory heat from a gas turbine engine assembly.

Aligning entry pipe centers with inhale ports reduces flow loss and improves inhale efficiency in linear compressor mufflers.

Active cooling via integrated pin passages resolves integration difficulties between ceramic and metallic components.

Twin counter-rotating M-VAWTs use clocked mirror airfoils to shield and divert wind forces for enhanced power conversion.

Solid propellant gas drives a turbine to supply mechanical power during autorotation, reducing damage rates without adding complex active controls.

Scalloped rails engage the forward hook to stabilize the blade outer air seal, reducing vibration and gas leakage in extreme heat.

Segmented carrier plates with impingement apertures heat the turbine casing to maintain optimal tip clearance during transient power increases.

A compressor rotor blade stiffener uses a trailing edge notch to relieve joint stresses from centrifugal forces while maintaining sealing support.

Variable thickness core sections reduce manufacturing fragility while maintaining efficient thermal energy transfer in gas turbine engine components.

Drainage orifices in reinforced outer wall stiffeners direct liquid flow away from the lip, reducing air leakage risk and structural mass.

Segmented trailing edge cooling zones prevent material degradation at high stress apex and base regions while maintaining structural integrity.

A hybrid drive system couples a gas turbine to a load via a reversible electric machine that supplements mechanical power or generates electricity.

A turbine tip shroud assembly uses segmented internal cooling passages to direct fluid flow through impingement apertures for targeted thermal management.

Segmented cooling passages distribute fluid through radial channels and film holes, preventing thermal stress damage from inadequate air distribution.

A wind turbine blade gripper uses a force transfer mechanism to increase gripping pressure during transport acceleration.

Electric motor starting device decouples from synchronous machine shaft after startup to enable pump operations without water turbine availability.

Flexible webs join gas turbine blades to allow relative movement, reducing thermo-mechanical fatigue caused by pressure and temperature differentials.

Segmented pull belts reduce tensile forces and tooth loads, extending service life while maintaining high torque transmission.

A fan drive gear system ejector utilizes motive flow to impart momentum on expelled lubricant for directed recovery.

Dynamic filter doors resolve the contradiction between engine protection and aerodynamic efficiency by eliminating spillage drag during high-speed flight.

A planetary gear reducer integrates an oil buffer chamber in the planet carrier to supply lubrication using centrifugal force.

Reciprocating blades drive a rotating disk to retrieve river energy while keeping complex mechanisms on land for easy maintenance.

L-shaped connecting members segment the fastening structure to maintain cooling tube positioning accuracy under thermal and vibratory stresses.

Modular segments resolve transport complexity while maintaining structural integrity.

A turbo-expander harnesses excess air from a gas turbine compressor to drive an auxiliary generator.

A rotor lock uses short and long tabs to secure minidisks in gas turbine engines.

Incorporating doped graphene into disc structures mitigates rim-to-bore temperature gradients while reducing component weight.

A controller automatically initiates starter motor operation via a single flight deck control input device.

Integral collapsible features accommodate thermal expansion forces, preventing seal failure and uncoupling during outage events.

Modifying blow-off and extraction lines prevents collisions with the existing foundation, avoiding downtime and costs from foundation replacement.

A replaceable grommet acts as a sacrificial layer between metallic pins and ceramic segments to absorb mechanical wear.

A solenoid valve system integrated with a pressure regulator manages compressor discharge pressure using a spring-loaded piston mechanism.

Tapping upstream compressor air and routing it through a heat exchanger inside a bifurcation duct lowers temperature while minimizing flow restrictions.

Universal extension unit with sliding pushing and pulling members transfers mechanical forces for aircraft engine component assembly.

A heat shield plate between the variable nozzle mechanism and bearing housing blocks thermal transfer to protect thrust bearings.

Alternating airfoils with distinct cavity arrays vary stiffness and mass distribution, altering natural frequencies to reduce aeroelastic flutter.

Concave cam varies contact angle with follower roller to reduce radial loads and optimize thrust vectoring in gas turbine engines.

Integrating damping and sealing functions into one stamped or sintered component reduces vibratory stresses while preventing cooling air leakage.