Turbine/Propulsion Engine Ignition TRIZ Cases

Electronic control computer adjusts starter torque via DC-DC converter to keep compressor speed inside the ignition window, preventing failed ignitions.

Periodic low-speed shaft rotation dissipates residual heat to control bending deformation while minimizing energy consumption.

An eductor assembly injects compressor discharge air into the heat recovery steam generator to cool superheated steam.

An auxiliary energy store preheats thermal power plant components, reducing cold start duration and operational stress.

Calculating actual flow coefficients from real-time fuel parameters positions valves to resolve ignition consistency issues caused by pressure regulator drift.

Dual electrical machines manage compressor rotation to prevent front end stall, reducing noise and weight compared to traditional bleed systems.

Segmented motor-driven and shaft-driven fuel gas compressors maintain elevated pressure during low-speed startup.

Segregated overspeed protection device uses independent electronic units and voltage sources to manage fuel supply via discrete signals.

Modulating starter air valve pressure via controller feedback prevents uneven thermal expansion and rotor blade deflection.

Segmented control paths manage fuel and oxidant ratios, resolving complexity trade-offs while optimizing power production efficiency.

Active modulation of start bleed extraction prevents compressor surge at low speeds, expanding the turbine operable space.

Dynamic start sequences purge excess fuel after failed attempts, increasing ignition opportunities while preventing engine damage from accumulated fuel.

Heated auxiliary air injection reduces gas turbine start-up time from 60 minutes to 15 while preserving component reliability.

Blending hydrogen and methane off-gas with natural gas lowers flame temperature, reducing NOx and CO emissions without structural hardware changes.

Dual electrical machines control low and high pressure compressor speeds to prevent front end stall without adding start bleed weight or noise.

An integrated inlet particle separator blower and engine starter unit combines turbine and geared components into a single housing.

An integrated e-machine replaces separate starter components, reducing weight and complexity while maintaining starting reliability.

A fuel metering control system selects weight flow rate calculations using temperature and permittivity signals.

A variable speed fuel pump controller adjusts delivery rates to achieve reliable turbomachine combustor light-off.

A starter-drive generator system integrates motor drive and hydraulic gearbox components to enable engine starting operations.

Extracted hot combustion gases warm the steam turbine during start-up, reducing thermal stress and accelerating power generation readiness.

Electronic regulation system verifies fuel cutoff member closure state during startup to prevent overspeed damage from unconfirmed protection function.

A detection system monitors inter-turbine temperature during gas turbine engine start to identify abnormal conditions before damage occurs.

Electric motor augments high speed spool rotational power during gas turbine engine starting, eliminating compressor stall margin loss from pneumatic bleeds.

Merging separate baffles into one additive manufactured structure reduces assembly labor and prevents cracking at joint interfaces.

A hybrid-electric propulsion system adds power via an electric machine to enable rapid turbomachine acceleration.

Compressed air preheats steam injection piping to eliminate slow startup delays and reduce excess steam production during power augmentation.

Periodic fuel pulses accelerate a turbine engine from low speed while preventing over-temperature damage during the starting cycle.

Bleed air heating raises fuel gas temperature quickly, shortening start-up time and maintaining efficiency.

A fuel control system manages secondary manifold filling in gas turbine engines by monitoring operational parameters to accelerate engine startup.

A gas turbine engine startup method modulates control parameters across sequential phases to achieve reliable light-up and flame propagation.

Modular gas turbines switch between mechanical and electrical loads using universal interfaces, resolving adaptability versus complexity trade-offs.

A separate safety instrumented system controller monitors turbine inputs to enhance operational reliability without modifying existing hardware.

Dynamic fuel flow adjustment stabilizes gas turbine acceleration during startup, preventing thermal stress that reduces component lifespan.

Embedding an electrical starter generator in the compressor eliminates accessory gearboxes, reducing weight and structural asymmetries.

A gas turbine starting process adjusts ignition speed based on ambient conditions to maintain optimal air mass flow.

A steam turbine controller manages startup sequences using predefined setpoints and release points to coordinate rotor speed with thermal conditions.

Dynamic safety margins adapt to inlet guide vane angle and vehicle Mach number, resolving the trade-off between surge prevention and thrust efficiency.

A turbine rotor lock uses a disposable fuse to block windmilling rotation, preventing bearing damage during transport.

An integrated fuel gas characterization system measures heating value and adjusts air-fuel ratios to maintain stable combustion conditions.

A twin engine starting system uses super-capacitors and a DC to DC converter to charge energy storage units for simultaneous engine ignition.

Preliminary purging cycles remove flammable mixtures before ignition attempts, reducing explosion risks during turbine start-up.

A heated fluid manifold and controller pre-heat fatigue-prone gas turbine components during standby mode.

Intermittent rotary power application mitigates shaft distortion and vibrations while shortening engine start times compared to continuous motoring.

A fuel control system modulates flow via pressure signals to ensure consistent delivery during engine start.

Helical gears in a speed reducer minimize torque transmission delay caused by backlash during direction changes.

Segmented pump architecture delivers high pressure fuel to auxiliary devices via a dedicated augmenter unit.

Varying engine speed and fuel pulses widens the air/fuel ratio window, resolving high altitude startup delays.

Intermittent rotor turning mitigates thermal bow while reducing gear wear through periodic action and variable speed control.

Turbopump starter uses compressor air to drive turbines, preventing thermal shock and extending lifespan.