Turbine/Propulsion Engine Cooling TRIZ Cases

Curvilinear plates merge the heat exchanger with the fan duct structure, eliminating elaborate piping and minimizing pressure loss.

Internal bypass routes warm oil between passes to heat the cooler core, reducing pressure drops during cold start decongealing.

A buffer system supplies cooled pressurized air to remote gas turbine components using a multi-source heat exchanger and selective valve regulation.

Segmenting the bore basket into nested cylinders distributes cooling flow independently, resolving the trade-off between heat protection and cooling efficiency.

Lubricant guides in the bent area prevent recirculation and increase wet surface area to resolve pressure drop and heat exchange contradictions.

Integrating thermal fluid passageways into outlet guide vanes manages heat rejection while avoiding pressure drop penalties in the bypass flow.

A turbine vane nozzle and swirler supply cooling air to a rotor cavity while maintaining equal pressure at the seal member interface.

Dual-stage filtration in tangential and radial cooling passages removes foreign substances, preventing blade fouling and stabilizing gas turbine operation.

Shape memory alloy adjusts turbine bucket cooling gas flow to reduce compressor bleed during part-load operations.

Internal passages in axial retaining segments route ventilation air to blade cavities, resolving stress concentration issues from drilling.

An interface compartment with a blower circulates air to insulate the accessory gear box from heat, enabling ventilation while stationary.

A shared heat sink exchanger selectively connects multiple heat source assemblies via a controller to optimize thermal fluid flow.

An asymmetric ventilation manifold optimizes cooling air distribution across the nacelle circumference, reducing fuel consumption caused by non-uniform airflow.

Two-stage air-to-air heat exchanger system reduces core airflow temperature while maintaining energy efficiency in aircraft turbine engines.

Scalloped turbine blades reduce weight and increase temperature tolerance, resolving gear complexity and blade stress trade-offs in high-bypass ratio engines.

Angled channels within hollow spokes direct cooling airflow into bearing support cavities, preventing overheating of low-rotor components.

A stator temperature control system directs heated air to the bottom casing portion to maintain thermal uniformity across the gas turbine structure.

Axial cooling fins on the radially outer face of a blade outer air seal increase surface area for convective heat transfer.

A cooling compressor system drives a gas turbine engine rotor during start-up using auxiliary pressurized air.

Asymmetric coating thickness balances heat loads on turbine airfoils, preventing thermal mechanical fatigue cracking at the trailing edge.

A heat engine frame uses a double wall plenum to distribute heated fluid along the inner and outer walls.

A segmented heat shield blocks thermal radiation between the fairing and casing in gas turbine engines.

Transduct segments in an annular heat exchanger minimize pressure loss by eliminating elaborate piping friction.

Integrated chevron and wavy corrugations eliminate downstream mist eliminators, reducing pressure losses and space requirements in gas turbine cooling systems.

An adaptively opening secondary cooling pathway delivers extra cooling medium flow to prevent overheating damage in gas turbine components.

Spiral cooling duct extracts bypass air to cool the engine core, avoiding performance loss from compressor bleeding.

Segmenting the fuel line with a recirculation cooler and throttle valve increases heat sink capacity while preventing oil and fuel coking.

An insertion portion reduces the cross-sectional area of a turbine blade pin fin channel to increase cooling fluid velocity.

Shared shaft links permanent magnet alternator rotor with cooling fan to reduce gearbox weight while maintaining thrust output.

A control method adjusts cooling air consumption in gas turbine stages using real-time pressure and temperature measurements.

Cooling jacket encases speed sensor and directs fluid flow to withstand extreme turbine temperatures for reliable over-speed detection.

A variable eductor apparatus mixes ambient air into a hot gas stream to reduce thermal stress on HRSGs during startup.

A scramjet fuel supply system uses a zeolitic catalyst to pyrolyze hydrocarbon fuel into reformed gas for stable combustion.

A gas turbine engine manages airflow through a nested three-stream architecture, resolving the trade-off between propulsion efficiency and device complexity.

A tertiary airflow duct extracts cool intake air to drive a heat exchanger, solving supersonic engine overheating.

Radial diversion of fan air across a heat exchanger recovers thermal energy, improving fuel efficiency while maintaining component cooling.

Integrating a recuperated supercritical CO2 cycle into gas turbines converts expelled cooling air waste heat into rotational work, reducing energy loss.

A heated bypass valve prevents ice blockages in gas turbine fuel systems by using a secondary heat exchanger to keep the valve warm and ensure continuous flow.

Segmenting the thermal management duct from the bypass passage prevents heat exchangers from disrupting airflow while maintaining efficient heat rejection.

A thermal management system dynamically transfers heat from specific source exchangers to a shared heat sink based on the engine operating mode.

An injection cooling system fluidly couples a thrust reverser locking mechanism to an engine pre-cooler using bleed air.

Transition manifolds decouple manufacturing precision requirements from micro-channel alignment, reducing hot gas leakage risks.

Integrating the heat exchanger into the sump eliminates external scavenge lines, reducing weight and complexity while maintaining reliable oil cooling.

Branch pipes channel cooling air along the fillet portion to prevent fatigue cracks caused by thermal stress concentration during operation.

A turbine blade tip winglet guides leakage air to compact the vortex, reducing pressure loss by 0.10 points in efficiency.

Separating cooling steam from reheat flow prevents thermal efficiency loss while maintaining effective turbine rotor cooling.

A pericritical fluid system uses acoustic and thermal sensors to detect phase properties for precise turbine engine thermal management.

Rotating vanes modulate airflow characteristics within a tangential on-board injector to optimize cooling distribution.

An annular metering device uses differential thermal expansion to radially modulate flow apertures without external actuators.

Turbocompressor blends high and low pressure air streams to reduce engine load while maintaining precise cabin temperature and pressure.