Turbine/Propulsion Engine Cooling TRIZ Cases

Angled gussets connect hollow spokes to flanges, reducing stress concentrations while maintaining cooling airflow paths.

Circulating fluid through stator vane cavities reduces temperature-induced stress, extending component life and lowering reliance on high-temperature alloys.

A passive cooling system utilizes pressure differentials to cool turbine housings and optimize tip clearance gaps.

A gas turbine design integrates stator cooling air with an air bleeding system to enable low-load operation.

A gas turbine cooling system uses an ejector to route compressed fluid between cavities for thermal management.

A turbo-generator uses compressor bleed air to drive an integrated air cycle cooling system.

A fluid duct system generates a cooling jet via internal pressure gradients to ventilate temperature-sensitive regions within a turbo engine.

A film-cooled component features a curvilinear airflow passage that diffuses cooling air laterally and streamwise to enhance thermal protection.

Dual circulator loops regulate heat exchanger temperatures to prevent frost formation on the first heat exchanger during air-breathing operation.

Segmented impingement cooling channels increase heat transfer rates and maintain uniform temperature profiles across hot gas path components.

Bladder heat exchanger transfers thermal fluid to aircraft wings, preventing ice formation while reducing system weight and complexity.

A one-piece annular heat exchanger creates internal fluidic connections via a sealing member, eliminating complex welding operations.

A pin fin bank cooling circuit shields near wall channels in a multi-wall blade tip, resolving insufficient cooling effectiveness under extreme heat loads.

Segmented evaporative cooling media enable part-load operation, reducing water consumption while maintaining compressor discharge temperature.

Dual inlet ducts merge into a common path, allowing the system to maintain cabin pressure across varying engine power levels.

Segmented turbine exhaust paths decouple steam production from power load, maintaining efficiency while controlling emissions.

Position-dependent flow restrictors in the cooling air chamber equalize static pressure, ensuring uniform mass flow rates into the turbine chamber.

Circulating cooling air via shaft apertures prevents rotor bow caused by asymmetric thermal gradients in turbine compressor cavities.

Annular duct with sealing coupling directs impingement cooling air to turbine casing surfaces.

Guide surface redirects combustion gas along seal segment inner surfaces, suppressing heat loads and preventing mixing with cooler seal gas.

Merging air-oil cooler and air-air precooler into one unit reduces engine weight and complexity while maintaining efficient compartment cooling.

Segmented air and fuel lubricant heat exchangers optimize heat dissipation proportions, minimizing energy waste while preventing fuel thermal degradation.

Steam injection into the turbine section cools components without bleeding compressor air or causing combustor flameout.

A liquid harvester system extracts vapor from working fluid using a heat exchange component to inject condensate into an engine flow path.

Tangential cooling fluid injection manages thermal stress in gas turbine compressor rims while minimizing turbulence and pressure losses.

A heat pipe system transfers thermal energy between upper and lower rotor sections to equalize temperature gradients.

Real-time flow adjustment compensates for seal wear, reducing excessive cooling consumption while maintaining turbine efficiency.

An asymmetric hook turbulator generates a cavitation zone that entrains colder coolant, resolving low Mach number inefficiencies in gas turbine engines.

Radial wave springs accommodate thermal growth in gas turbine surface coolers while maintaining mechanical strength and vibration damping.

Impingement cooling holes in a partition wall eject compressed air toward turbine wheel attachment portions.

A gas turbine engine air-to-air heat exchanger uses a defined potential metric to optimize compactness and effectiveness.

Deployable ventilation assemblies with passive shape memory alloy actuators resolve the temperature-drag trade-off in aircraft turbine engine compartments.

High-pressure cooling medium flows through stator blades and rotor wheel passages to mitigate windage loss temperature rises near the exhaust stage.

A radial mixing chamber combines cooled high-pressure air with hotter streams to optimize turbine cooling.

Canted tapered fingers break dirt particles in gas turbine cooling fluid passageways, preventing plugging of high-pressure turbine blade outer air seals.

Additive manufacturing produces gas turbine blades with functionally graded materials, reducing costs while maintaining high-temperature strength.

A supplementary coolant injector reduces heat exchanger weight and manufacturing cost by using phase transitions to cool coolant instead of physical hardware.

Sectorized nozzle platforms use closed annular cavities to direct cooling air along faces, resolving temperature non-uniformity and rapid mixing issues.

A scupper channel system forms into the radially inner surface of a gas turbine bearing support ring to capture and direct leaking oil.

Segmented cooling paths with ceramic fiber insulation prevent heat infiltration into the airflow, maintaining low temperature for efficient component cooling.

Braided carbon fiber composite ducts replace metal aircraft bleed systems to achieve significant weight savings.

Segmented cylinders and struts create a unitary flow path that shields rotor bores from hot air while maintaining structural integrity.

A nested duct cooling arrangement directs separate fluid flows to reduce turbine casing surface temperature and improve space utilization.

Elongated pedestals in gas turbine airfoils accelerate coolant exit velocity to match the main gas stream.

Segmented cooling reduces compressed air consumption by applying ambient air to the inner diffuser while reserving compressed air for the outer diffuser.

A gas turbine engine system taps compressed air, cools it through a heat exchanger, and delivers the conditioned flow to turbine blades.

A fuel air heat exchanger uses a flow selection member to modulate pressurized air distribution through a secondary inlet.

Outer rotor fluid passages orient outlet centerlines to redirect cooling flow toward inner rotor rotation, reducing windage losses and increasing power output.