Engine Fuctions TRIZ Cases

A shroudless turbine blade uses a main trailing edge cooling channel connected to a gallery channel for film cooling.

A vane arc segment seal isolates impingement spaces from leakage gaps in hollow airfoils.

Unconnected vertical joints in post-tensioned concrete wind towers distribute horizontal strains via friction, eliminating complex lateral connectors.

Alternating turbine rotor blades use segmented support members to reduce vibrations and maintain tight clearances between low-speed and high-speed stages.

A vibration damper arrangement uses a wheel-rail system to generate variable restoring forces for mass displacement.

Capitulating buoyant bodies adjust orientation under extreme forces, maintaining structural stability and energy capture efficiency.

Inward protrusions and wall holes direct particles outward, reducing pressure loss while increasing collection efficiency.

A supercritical carbon dioxide gas turbine engine uses angled heat exchangers to reject thermal energy from the power circuit into a bypass air stream.

Segmented CMC shroud and insertion members stabilize tip clearance by distributing load perpendicular to thickness, preventing heat deterioration.

Field assisted sintering bonds cover sections to wall sections forming a thermally isolated enclosure that minimizes tip clearances by slowing thermal response.

Positioning a heat exchanger in bifurcation ducts reduces compression work and temperature while maintaining airflow rates for efficient turbine cooling.

Shear bolts break under torque to decouple the electric rotor, preventing rotor-stator contact and fire risks.

Segmenting compression across three spools reduces specific fuel consumption while avoiding added device complexity and weight.

Elastomeric inserts bridge collector and manifold gaps to prevent leakage during thermal expansion.

A pivoting lock arm secures a translating sleeve against translation by engaging a ramp in a normal plane.

Heatable collecting elements induce coking upstream to detect fuel deposits, resolving aircraft weight constraints and unreliable oxygen-based monitoring.

A lightoff fuel pressure reduction system uses a bypass regulator to lower supply pressure during ignition.

Local wall thickening arrests high-energy debris to prevent fragmentation and further engine damage.

Preliminary pumping corrects biased readings caused by gravitational drainage, ensuring accurate measurement.

Segmented turbine shroud segments use an inter-segment seal arrangement to reduce leakage and enhance cooling efficiency.

A turbine blade damping coating uses a viscoelastic layer and constraint layer to dissipate kinetic energy.

A wind turbine converter uses time-dependent humidity data chronology to calculate the exact dry-out period needed for safe operation.

Extended flange geometries seal unsealed ends to prevent gas leakage and maintain structural integrity.

Nested blocker doors pivot on an aft ring while a translating sleeve exposes cascade vanes, reducing drag and noise in the bypass flow duct.

Electromagnetic induction heats the outer housing ring to maintain optimal clearance between static and rotating components during operation.

A dovetail fixture interlocks with a turbine wheel slot, preventing dangerous rotor rotation and hardware damage caused by strap failure.

Removable plug seals rotor blade drain hole to prevent noise ingress and enable maintenance access.

A blade outer air seal segment uses a stress-relief boss extending into the cooling channel to mitigate tensile stresses.

Segmented branch pumps reduce system pressure and pump burden while enabling cost-effective thermal control without complex three-way valves.

A radially floating heat shield maintains contact with a turbine carrier via a pin-and-slot joint, inhibiting gas leakage during thermal expansion.

Segmented high-pressure and low-pressure housings with counter-flow arrangement minimize thermal stresses while maintaining efficiency.

A wind turbine maintains a constant distance between its rotation axis and slider attachment to convert translational movement into rotational energy.

A liner creates a chamber to direct leakage flow, reducing thermal stress on the radially outer annular member.

A turbine nozzle sector applies differential cooling to central and end blades using distinct hole configurations.

Fan ramp pockets receive blocker door edges to eliminate gaps, reducing drag and optimizing airflow paths during thrust reversing.

Thickened tip rail with cooling holes directs fluid to the turbine blade tip, reducing temperature gradients and specific fuel consumption.

A controller detects fan shaft deformation by measuring speed differences across a geared architecture.

Counter-rotating vaneless turbine stages with an integral drive system reduce stage count and weight while optimizing operational speeds.

A turbine shroud assembly uses a tandem seal to block gas movement between metallic and ceramic components.

An oil accumulator stores pressurized fluid to supply gearbox lubrication during zero g-force events, resolving reliability issues caused by weightlessness.

Segmented suspension modules adapt to varying channel widths, eliminating complex beam adjustments and reducing installation time.

A gas turbine blade cover joins a pre-formed groove to define an internal cooling channel.

A coaxial ignition device injects fluid flows with different velocities to generate strong shear layers within an ignition chamber.

Air guides inside and outside generator end-windings enhance airflow velocity to reduce temperatures without excessive pressure drop.

A gas turbine vane insert supported by standoffs creates a radial gap for convective cooling fluid flow.

Radially discontinuous ribs in a ceramic-matrix composite airfoil manage thermal stresses by allowing independent expansion of structural segments.

Epicyclic gear train with differential arrangement optimizes speed ratios between fan and turbine spools, enabling higher low-pressure rotational speeds.

Lateral rib openings trap particles to prevent blockages, allowing smaller hole diameters that reduce cooling air consumption.

Interchangeable connectors and inserts reconfigure gas turbine airfoil cooling passages to adapt to varying temperature levels without recasting.

A propulsion system uses ammonia fuel to supply hydrogen and nitrogen components for simultaneous turbine and ramjet combustion.