A gas turbine engine has: a casing; a combustor liner delimiting a combustion chamber; a fuel nozzle in fluid communication with the combustion chamber; and an igniter having a base, a glow plug heater rod extending from the base along an axis and terminating in a rod end, and a sleeve extending around the glow plug heater rod, the sleeve radially spaced apart from the glow plug heater rod by an annular gap, the sleeve defines fins circumferentially distributed around the axis, each two circumferentially adjacent fins of the fins spaced apart from one another by a spacing communicating with the annular gap, the fins extending in a direction having an axial component from roots to tips, the roots axially closer to the base than the tips, the rod end extending axially beyond the tips of the fins such that the rod end is located outside the annular gap.

A gas turbine engine has: a casing; a combustor liner delimiting a combustion chamber; a fuel nozzle in fluid communication with the combustion chamber; and an igniter having a base, a glow plug heater rod extending from the base along an axis and terminating in a rod end, and a sleeve extending around the glow plug heater rod, the sleeve radially spaced apart from the glow plug heater rod by an annular gap, the sleeve defines fins circumferentially distributed around the axis, each two circumferentially adjacent fins of the fins spaced apart from one another by a spacing communicating with the annular gap, the fins extending in a direction having an axial component from roots to tips, the roots axially closer to the base than the tips, the rod end extending axially beyond the tips of the fins such that the rod end is located outside the annular gap.

When a diesel engine is determined to be in a motoring state, a hysteresis zero angle H.sub.0 is determined (step S14). Subsequently, a gradient d.sub.n is calculated (step S16). The gradient d.sub.n is calculated based on data (θ.sub.n, Δh.sub.n) of a deviation Δh.sub.n at a retardation side from the hysteresis zero angle H.sub.0 and at an advance side from a predetermined crank angle. Subsequently, the gradient d.sub.n and the hysteresis zero angle H.sub.0 are updated (step S18). When the diesel engine is determined to be in a non-motoring state, data (θ.sub.n, P.sub.n) of an actual in-cylinder pressure is corrected based on a newest correction coefficient η and hysteresis zero angle H.sub.0 (step S22).

A gas turbine engine has: a casing; a combustor liner delimiting a combustion chamber; a fuel nozzle in fluid communication with the combustion chamber; and an igniter having a base, a glow plug heater rod extending from the base along an axis and terminating in a rod end, and a sleeve extending around the glow plug heater rod, the sleeve radially spaced apart from the glow plug heater rod by an annular gap, the sleeve defines fins circumferentially distributed around the axis, each two circumferentially adjacent fins of the fins spaced apart from one another by a spacing communicating with the annular gap, the fins extending in a direction having an axial component from roots to tips, the roots axially closer to the base than the tips, the rod end extending axially beyond the tips of the fins such that the rod end is located outside the annular gap.

An engine includes a main combustion chamber; an intake duct configured to provide a lean fuel-oxidizer mixture to the main combustion chamber; a pre-chamber in fluid communication with the main combustion chamber, the pre-chamber including an ignition energy source operatively coupled to the pre-chamber, and a heating element in thermal communication with the pre-chamber; and a controller operatively coupled to the ignition energy source and the heating element. The controller is configured to initiate combustion of the lean fuel-oxidizer mixture in the main combustion chamber by activating the ignition energy source, and heat fuel and oxidizer in the pre-chamber via the heating element to a temperature sufficient to produce hydrogen peroxide (H.sub.2O.sub.2) in the pre-chamber.

Methods and systems for adapting pilot fuel injection pulse widths are disclosed. In one example, pilot fuel injection values are varied to determine adjustments to a fuel injector transfer function and a glow plug is activated in response to a request to adapt the fuel injector transfer function so that adaptation may be improved.

Provided is a subchamber diesel engine having excellent thermal efficiency and capable of appropriately controlling the ignition timing of fuel supplied to a combustion subchamber. A subchamber diesel engine according to the present invention comprises a main combustion chamber and a combustion subchamber communicated with each other by a communication hole, the diesel engine including: an electrically driven injector for injecting fuel into the combustion subchamber at a random timing; a fuel passage pipe connected to a fuel inlet of the injector; a fuel pump for supplying fuel to the fuel passage pipe; an engine operating state detector for detecting an engine operating state; and a controller, wherein the controller performs a preliminary fuel injection in the first half of an intake stroke, performs a main injection during a compression stroke, and after the main injection, performs an ignition control injection near a compression top dead center.

Provided is a subchamber diesel engine having excellent thermal efficiency and capable of appropriately controlling the ignition timing of fuel supplied to a combustion subchamber. A subchamber diesel engine according to the present invention comprises a main combustion chamber and a combustion subchamber communicated with each other by a communication hole, the diesel engine including: an electrically driven injector for injecting fuel into the combustion subchamber at a random timing; a fuel passage pipe connected to a fuel inlet of the injector; a fuel pump for supplying fuel to the fuel passage pipe; an engine operating state detector for detecting an engine operating state; and a controller, wherein the controller performs a preliminary fuel injection in the first half of an intake stroke, performs a main injection during a compression stroke, and after the main injection, performs an ignition control injection near a compression top dead center.

There is disclosed an igniter for a gas turbine engine including: a base including a securing assembly configured to be matingly connected to a casing of the gas turbine engine, a glow plug heater rod, the glow plug heater rod extending from the base along an axis and terminating in a rod end, a flow impeding member extending along the axis and having a distal end spaced from the base and extending axially relative to the axis beyond the rod end, the flow impeding member sized and configured such that the distal end extends into a combustion chamber of the gas turbine engine upon the base connected to the casing.

There is disclosed an igniter for a gas turbine engine including: a base including a securing assembly configured to be matingly connected to a casing of the gas turbine engine, a glow plug heater rod, the glow plug heater rod extending from the base along an axis and terminating in a rod end, a flow impeding member extending along the axis and having a distal end spaced from the base and extending axially relative to the axis beyond the rod end, the flow impeding member sized and configured such that the distal end extends into a combustion chamber of the gas turbine engine upon the base connected to the casing.