Guiding a sparkplug in a turbine engine combustion chamber
View Patent ↗A turbine engine combustion chamber including at least one ignition sparkplug carried by an outer casing and extending through a guide mechanism carried by a wall forming a body of revolution of the chamber. The guide mechanism includes a tubular guide having the sparkplug passing axially therethrough, which guide is mounted with axial and transverse clearance on a chimney fastened to the wall of the chamber and opening out therein. The guide includes an annular collar engaged with clearance in an internal annular groove of the chimney. The annular collar is urged to press against a wall of the groove by a resilient member mounted in the groove.
1. A turbine engine combustion chamber comprising:
at least one ignition sparkplug carried by an outer casing and extending through guide means carried by a wall forming a body of revolution of the chamber;
the guide means comprising a tubular guide having the sparkplug passing axially therethrough, which guide is mounted with axial and transverse clearance on a chimney fastened to the wall of the chamber and opening out therein, the guide including an annular collar engaged with clearance in an internal annular groove of the chimney,
wherein the annular collar is urged to press against a wall of the groove by a resilient member mounted in the groove.
2. A combustion chamber according to claim 1 , wherein the resilient member is a spring or a spring washer.
3. A combustion chamber according to claim 1 , wherein the resilient member presents a C-shaped or Ω-shaped section.
4. A combustion chamber according to claim 1 , wherein the annular groove is defined by two parallel walls that are substantially radial relative to the axis of the chimney, the resilient member being placed in an annular groove formed in one of the walls.
5. A combustion chamber according to claim 1 , wherein a wall of the groove is formed by a radial annular rim of the chimney and the resilient member is housed in a groove in the rim.
6. A combustion chamber according to claim 5 , wherein the wall of the groove against which the collar is pressed by the resilient member is formed by an annular plate fastened to the rim of the chimney.
7. A combustion chamber according to claim 1 , wherein the resilient member is a spring blade of undulating shape.
8. A combustion chamber according to claim 7 , wherein the spring blade comprises an annular central zone surrounding the tubular guide, together with two ends bearing against two opposite support tabs of the tubular guide extending radially outwards from the collar.
9. A combustion chamber according to claim 8 , wherein the chimney includes two openings through which there extend the support tabs of the tubular guide and the ends of the spring blade.
10. A combustion chamber according to claim 7 , wherein the wall of the groove against which the collar of the guide is pressed is formed by a radial annular rim of the chimney, the spring blade bearing against an opposite wall of the groove.
11. A combustion chamber according to claim 10 , wherein the opposite wall of the groove includes a setback of shape complementary to the shape of the spring blade and is configured to hold it in position.
12. A turbine engine or a turboprop or a turbojet, comprising an annular combustion chamber according to claim 1 .