Efficient Propulsion Technologies TRIZ Cases

Control systems regulate electric machine speed to drive rotors, reducing ground noise while maintaining rotor readiness.

Intercooling turbine section bypass routes core flow around cooling stages to adjust bypass ratios for variable cycle operation.

Thermocouples on the stator surface detect shaft failure to trigger fuel supply cutoff, preventing rotor overspeed and catastrophic blade damage.

A gas turbine intercooling turbine section bypass modulates core flow around the turbine to drive spools and reduce fuel consumption.

An annular rim catcher on the driving drum absorbs impact energy and retains the fan assembly during shaft breakage, reducing dynamic loads.

An aircraft propulsion system uses exhaust heat to condense water vapour and reduce contrail formation.

Flexible cable coupling connects gas turbine vane panels to absorb bending loads without inducing structural stress.

Variable fan outlet guide vanes pivot from nominal to open positions to prevent choking at high flight Mach numbers and maintain thrust production.

Single-piece lobed tubular fibrous structures eliminate overlapping fiber layers, reducing weight and aerodynamic imperfections in dual-flow turbojet nozzles.

A shroud hanger assembly uses a conformal seal to bias the ceramic matrix composite shroud against thermal expansion.

Ceramic composite inter-turbine ducts eliminate heavy cooling systems by using segmented structures to resist high temperatures.

Controllers govern electric motor torque to reduce speed error, improving responsiveness to load changes without requiring rapid fuel flow adjustments.

A flexible skin airfoil system uses a roller mechanism to change shape without gaps, preventing turbulence and flow separation.

Segmented fastening components accommodate thermal expansion in gas turbine exhaust liners without burdensome disassembly.

Segmenting the volute into isolated volumes minimizes pressure drops during heat exchange, reducing system mass and volume constraints.

A bearing hub design translates radial vibrations into axial vibrations, resolving critical speed instability in high-speed gas turbine engines.

Aligned fiber plies in composite flowpath structures transfer mechanical loads without metal backing, reducing inter-laminar shear stresses.

Axial passages guide pins through the annular distributor to engage transverse stops on the structural element, eliminating complex bolt assemblies.

A double outlet guide vane assembly with integrally formed end structures provides a continuous surface and primary load path.