A fuel nozzle and a method for operating a combustor are disclosed. The method includes flowing a fuel and an oxidizer through a fuel nozzle (40), the fuel nozzle comprising an inner tube (52), an intermediate tube (54), and an outer tube (56) each configu...

A laser ignition system for an internal combustion engine, and more specifically a gas turbine engine, is provided. The system comprises at least one laser light source configured to generate a laser beam and an optical beam guidance component. The optical...

An igniter (100) arranged to ignite combustion in a primary flow (162) comprising a fuel and air mixture, the igniter comprising one or more geometric features (110, 120) arranged to: induce a shockwave flow structure (102, 150) at least partially disposed...

A combustor for a gas turbine engine includes an inner liner and an outer liner circumscribing the inner liner and forming a combustion chamber therewith. The outer liner is a dual walled liner with a first wall and a second wall. A fuel igniter includes a...

An assembly (38) for mounting an igniter in a gas turbine engine combustor between an outer casing (30) and an outer liner (16). The igniter mounting assembly (38) includes a first spring member (42) encircling a portion (44) of said igniter (36) and being...

The method involves setting up a global fuel/air mixture of greater than unity in the flame tube (40) of the ignition device (10) prior to igniting the combustion chamber (30). It is used where the mixture is the inverse of the global air number. The mixtu...

The thermal turbomotor has a housing (80), combustion chamber (30) and an ignition system (10). For the ignition, an air feed (70) and a fuel feed (60) lead to an ignition zone (50) with ignition (51). The ignition zone is linked to the combustion zone by ...