Engine Fuctions TRIZ Cases

Higher-expansion spacers and a connecting flange keep the exhaust cone aligned with the metal casing to preserve smooth primary airflow.

Notched stop ring segments and an annular flange keep blade roots axially locked while routing cooling air to both rotor slot cavities.

An auxiliary oil tank and switching valve keep hydraulic actuator oil flow stable during zero or negative g flight, avoiding air bubbles and thrust loss.

Flexible seal fingers and a biasing member maintain vane collar sealing under thermal mismatch, reducing air leakage and abrasion.

A mid-bearing stabilizes the power turbine shaft to cut wobble while integrated condenser and evaporator sections recycle water vapor into steam.

Temperature and pressure sensing compared with physics-based seal models helps predict wear, remaining life, and timely maintenance.

Actuated dual screens move relative to each other to shed inlet ice while blocking foreign object debris and preserving engine airflow.

A low-expansion CMC control ring restrains stator growth to keep rotor clearances tight, cutting seal leakage in gas turbines.

Optimized high-speed shaft rating, geometry, and materials suppress bending-mode vibration and stabilize high-bypass turbine engines.

Recovers exhaust heat through a turboexpander and steam injection to raise turbine mass flow, shaft power, and engine efficiency.

A twin-generator tandem tower uses gravity, buoyancy, and feedback power to sustain operation while limiting external energy input and pollution.

A segmented rotor blade combines drag and lift profiles with edge extensions to self-start early, cut vibration, and stay stable at higher speeds.

Axial stops and a metal support structure position CMC turbine nozzle sectors, absorb load, and reduce leakage under thermal stress.

A continuous acoustic liner bridges the inlet and fan cases to cut fan noise and flow disturbances while simplifying secure alignment and gap filling.

Contaminant monitoring in ingested air sets corrosion and erosion action frequency, cutting unnecessary maintenance while protecting engine reliability.

Real-time thrust ratio control balances motor and engine output across flight phases to use battery energy more effectively and cut fuel burn.

Switching valves route boost-compressed fan air through nacelle heat exchangers to reject hybrid-system waste heat during taxi and idle.

Elastic members in smooth metallic half-shells absorb vibration energy while reducing tangential forces and wear on turbine blade shanks.

Movable discharge fins align bleed air with reverse secondary flow, reducing counter-thrust disturbances and avoiding larger nacelle designs.

A straddle-mounted bearing layout supports fan and spool loads while a compliant ring gear flexure accommodates thermal expansion in a compact turbofan.

Tuned mass dampers in the wind turbine nacelle target sub-50 Hz motion modes to cut fatigue-driving vibrations without added structural weight.

An internal cable loop lets wind turbine blades measure lightning-path conductivity from the root, avoiding external wiring and downtime.

Independent tip and hub vane rotation redirects fan exit air under inlet distortion, improving stall margin and reducing thrust loss.

A controller switches flue-flow and auxiliary heat inputs to keep gas turbine power stable while improving waste heat recovery efficiency.

Flexible trailing edge projections bend with the local flow vector to cut airfoil noise and turbulence without sacrificing efficiency.

An electric motor and variable-ratio gearbox adjust compressor speed relative to the turbine to boost thrust, improve fuel use, and avoid surge.

Selective normal and hot start control adjusts inlet guide vane and bleed valve openings to prevent compressor surge and rotor-stator contact.

Placing the air-oil heat exchanger in a diverging tertiary flow cools oil efficiently while limiting thrust loss, noise, and foreign object exposure.

Low-pressure airflow over the bifurcation cools compressor bleed air through a CCA heat exchanger to protect hot turbine components.

A dual fan bearing layout supports the epicyclic gear system to hold alignment under load and improve gas turbine efficiency.

Varying parietal and central corridor heights improves airflow uniformity and heat exchange while limiting friction and pressure losses.

Multiple diverging secondary passages keep cooling air flowing when particles clog one inlet, protecting the stator vane airfoil.

Flexible mounts and couplings tune lateral, bending, and torsional impedance to limit gearbox misalignment and stress under engine loading.

A heat exchanger uses colder bifurcation airflow to cool high-pressure bleed air for turbine components without losing needed pressure.

A recessed rearward flange gap and compliant seal relieve tight-fit assembly stress while preserving concentricity in a cooling fan housing.

A movable inlet door modulates airflow through the heat exchanger to reject hybrid engine waste heat while limiting cruise drag.

Active oil or air cooling protects gas turbine tail-cone power cables from exhaust heat without bleed air, including after shutdown.

Independent thrust reverser opening avoids frequent fan cowl access, cutting nacelle weight, complexity, and support needs.

A dual-engine gearbox layout combines high and low rotor takeoff paths to raise extracted power without adding engine length, weight, or speed-margin loss.

Pressed-in sliding elements guide the turbomachine adjustment ring with fewer parts, reducing housing wear, weight, and installation space.

Placing the heat exchanger upstream of the fan rejects heat through intake airflow, avoiding bypass-air losses and extra cooling ducts.

A support bracket and cradle let engineers balance gas turbine modules in place, cutting repeated disassembly during vibration testing.

A movable flush panel in a short nacelle air intake creates blade removal space while preserving aerodynamic continuity during operation.

Composite fan blades paired with a reduction gearbox enable larger, lighter turbine fans while limiting drag and blade count.

Reciprocal working-fluid flow in a pivoted two-compartment container drives an impeller for steady power without weather or site limits.

Wave motion lifts circulation fluid to a higher position, replacing external pumping power and lowering operating cost for electricity generation.

By splitting and precooling aircraft exhaust before condensation, the bottoming cycle improves water recovery and supports lower engine emissions.

Pivoting lever arms and hydraulic or pneumatic tensioning clamp tower segments securely, then release quickly to reduce unbolting risk on moving vessels.

Water-soluble particle compaction densifies anticorrosion coatings without media incrustation, preserving conductivity and corrosion resistance.

Separate supply and scavenge pump load paths simplify aircraft engine oil plumbing, while a mechanical fuse disconnects both on pump failure.