Turbine/Propulsion Engine Cooling TRIZ Cases

Movable deflector diverts bypass air flow to create pressure differential across heat exchanger, maintaining oil cooling at low power without fuel penalties.

A dummy ring channels cooling steam to lower rotor shaft temperatures, reducing reliance on expensive nickel alloys.

A gas turbine eductor distribution shield directs intake air around the combustor to improve cooling efficiency.

Segmenting compressor airflow into dedicated bleed and recuperator paths maintains heat exchanger effectiveness while cooling engine components.

Cooling communication holes connect blade passageways to platform discharge openings, eliminating cover plates and improving thermal stress resistance.

Relocating the heat exchanger into bifurcation ducts eliminates bypass airflow blockage while maintaining cooling effectiveness.

Nested tube banks and arcuate manifolds enable counter-flow heat exchange, resolving uniformity challenges in annular geometries.

A selectively positionable valve routes bypass airflow through a shared inlet to either the ECS pre-cooler or AOC peaker, reducing auxiliary openings and drag.

Profiled throat geometry allows fine-tuning of cooling air supply without distorting the optimized trailing edge outlet.

Heat pipes extract heat from compressor bleed-off air to bearing coolers, maintaining lower wheel temperatures without reducing cycle output capacity.

Three-stage cooling of engine bleed air via heat exchangers and vapor cycle evaporator expands gas through dual turbines to manage high heat loads.

Positioning a cooled heat shield between the fairing and frame blocks conduction heating, allowing cheaper fairing materials.

Lubricating oil absorbs bearing heat and transfers it to the nose cone, eliminating air bleed leaks and compressor efficiency losses.

Dynamic second combustor inlet temperature adjustment reduces carbon monoxide emissions in sequential combustion gas turbines.

Non-uniform curvature radii on the end wall section reduce total pressure loss by suppressing secondary flow whirls caused by cooling refrigerant mixing.

Electric fans force air through fire extinguishing pipes to ventilate engine and nacelle cavities, dissipating heat when the engine is not running.

A heat exchanger system selectively heats or cools conditioning air flowing into gas turbine rotor bore cavities.

Non-uniform hole distribution in a plate directs compressor air to manage inner casing temperature uniformity and radial clearance.

A reversible turning gear counter rotates the gas turbine rotor shaft to redirect exhaust flow through the heat recovery steam generator.

Regional through hole ratios in the stator vane impingement plate maintain cooling efficiency around the inspection probe communication hole.

A gas turbine cooling system uses a swirl flow guide nozzle to supply air while maintaining independent flow regulation.

Dynamic temperature regulation compensates for varying boil-off gas rates, keeping the Wobbe Index within limits without extra processing facilities.

A multi-width channel heat exchanger transfers thermal energy between air streams using a liquid intermediary fluid.

A universal thermal transport bus manages heat across a wide temperature range, reducing system complexity by consolidating multiple engine cooling functions.

An air recovery system redirects waste heat from bypass air to cool core air, reducing fuel consumption and performance loss in gas turbine engines.

Integrating a drag link fitting with a vent reduces drag while increasing acoustic treatment area in jet engine nacelles.

Manifold system directs air through interdigitated turbine bearings to reduce cooling air consumption and improve engine efficiency.

Varying the trailing edge cooling channel width preserves flow capacity when cutting back the blade for different engines.

Segmented hollow spokes transfer bearing loads while routing cooling airflow, reducing weight and maintaining structural integrity.

A modulating cooling system adjusts airflow pressure and volume to match specific engine operational demands.

Separate precooler and compressor flow paths cool bleed air below engine temperatures, reducing thermal loads by up to 90 kW.

A windage shield divides an annular cavity into separate flow paths to restrict heat transfer from rotating components.

A radial cooling conduit delivers fluid directly to the compressor rotor assembly to reduce temperature gradients.

A water discharge nozzle delivers cooling fluid to a turbine wheel space, maintaining temperature control without diverting compressor air.

A thrust reverser transcowl moves to a partially deployed position using sensors and actuators for thermal control.

Separate cooling circuit prevents solid fuel deposits by rejecting power electronics heat to ambient air or engine oil during sub-idle operation.

A rotating heat exchanger transfers thermal energy between compressed air and lubricant oil within a gas turbine assembly.

Fuel-powered turbo compressors reduce ambient pressure to an intermediate level, cutting electrical power consumption and pump-down time for large volumes.

Offset center of gravity pivots the valve disc to close passages under negative gravity, maintaining lubricant supply reliability.

A plug with a deflection surface redirects incoming air flow away from a hollow shaft bore, balancing cooling distribution across engine components.

A turbomachine valve diverts cooling air to the low-pressure turbine via a third channel.

Hollow spokes channel cooling airflow to manage temperature gradients and maintain engine roundness in gas turbine engines.

A bleed air duct central insert creates a venturi effect by reducing cross-sectional flow area, resolving pressure loss challenges in gas turbine engines.

Exhaust gas eduction draws cooling air through the tail bearing housing, reducing fan size and preventing bleed air leakage.

Segmented conduits and metering devices route lubricant to concealed pin-bushing interfaces, reducing wear while avoiding complex external alignment.

Split lubricant supply directs cooler oil to fan drive gears while routing warmer fluid to other engine bearings, preventing unnecessary cooling of all oil.

Nested heat exchangers in multi-bypass ducts increase cooling capacity without expanding the limited face area available for military gas turbine engines.

Stator overhang and rotor outboard face structures create an air curtain that blocks hot gas ingestion into the rim cavity, reducing purge air consumption.

An air guide directs cooling airflow onto a forward spool member to reduce operating temperature.

A gas turbine engine taps high-pressure air for cooling and passes it through a heat exchanger cooled by upstream compressed air.