Turbine engine combustion chamber with fixed duct geometry
AssigneeSafran Aircraft Engines
InventorJoseph Jean Marie BURGUBURU
Life of this patent
Estimating the term…
Abstract
The invention relates to a combustion chamber comprising: a duct (722) with a recess for a spark plug (13) emerging into an inner space of the combustion chamber, and a plug guide mounted on the duct so as to be movable transversely relative to the axis of the duct. The duct is crossed by openings (722b) which, parallel to the axis of the duct, are staggered in a plurality of rows (74a, 74b . . . ) over the height (H) of the duct, with at least some of the openings individually having a diameter of 0.2 to 0.6 mm.
Claims20
A combustion chamber of a gas turbine engine for aircraft, the combustion chamber comprising:
- a duct (720, 722) having an axis (X3), the duct forming internally a recess (721) for a spark plug (13) emerging into an inner space (15) of the combustion chamber,
- a plug guide (77) mounted on the duct so as to be transversely mobile relative to the axis of the duct, the duct being crossed by openings (720b, 722b), wherein, parallel to the axis of the duct, the openings (720b, 722b) passing through the duct (720, 722) are staggered in a plurality of rows (74a, 74b . . . ), with at least some of the openings individually having a diameter of 0.2 mm to 0.6 mm.
A combustion chamber of a gas turbine engine for aircraft, the combustion chamber comprising:
- a duct having an axis, the duct forming internally a recess for a spark plug emerging into an inner space of the combustion chamber,
- a plug guide mounted on the duct so as to be transversely mobile relative to the axis of the duct, the duct being crossed by openings,
- wherein, parallel to the axis of the duct, the openings passing through the duct are staggered in a plurality of rows, with at least some of the openings individually having a diameter of 0.2 mm to 0.6 mm, and wherein said openings passing through the duct number between 50 and 500.
A combustion chamber of a gas turbine engine for aircraft, the combustion chamber comprising:
- a duct having an axis, the duct forming internally a recess for a spark plug emerging into an inner space of the combustion chamber,
- a plug guide mounted on the duct so as to be transversely mobile relative to the axis of the duct, the duct being crossed by openings,
- wherein, parallel to the axis of the duct, the openings passing through the duct are staggered in a plurality of rows, with at least some of the openings individually having a diameter comprised between 0.25 mm and 0.45 mm.
Dependencies are inferred from the claim text.