US 11,841,140 B2
Pre-vaporization tube for a turbine engine combustion chamber
Thomas Jean Olivier Lederlin, Moissy-Cramayel (FR); Christophe Laurent, Moissy-Cramayel (FR); and Guillaume Gerard Joel Mauries, Moissy-Cramayel (FR)
Assigned to SAFRAN HELICOPTER ENGINES, Bordes (FR)
Appl. No. 17/766,602
Filed by SAFRAN HELICOPTER ENGINES, Bordes (FR)
PCT Filed Oct. 5, 2020, PCT No. PCT/FR2020/000247
§ 371(c)(1), (2) Date Apr. 5, 2022,
PCT Pub. No. WO2021/069808, PCT Pub. Date Apr. 15, 2021.
Claims priority of application No. 1911137 (FR), filed on Oct. 8, 2019.
Prior Publication US 2023/0184438 A1, Jun. 15, 2023
Int. Cl. F23R 3/28 (2006.01); F23R 3/32 (2006.01)
CPC F23R 3/32 (2013.01) [F23R 3/283 (2013.01); F23R 3/286 (2013.01); F23R 2900/03044 (2013.01)] 17 Claims
OG exemplary drawing
 
1. A pre-vaporization tube for combustion chamber of a turbine engine, in particular for an aircraft, comprising:
a main body having an elongate shape and defining a first internal longitudinal conduit configured to have a fuel injector mounted therein, said main body comprising a first longitudinal end configured to be fastened to a wall of the combustion chamber and a second longitudinal end,
at least two end pieces arranged at a level of said second longitudinal end and defining second internal conduits, said end pieces respectively comprising first portions, which are substantially coaxial and diametrically opposed, and second portions, which are parallel and oriented in a same direction, said first portions being in fluid communication with said first internal longitudinal conduit and said second portions being configured to open into the combustion chamber, wherein said second portions each comprise two coaxial cylindrical walls, respectively, internal and external, which define between them an annular cavity, and the internal wall defines an internal passage and comprises first orifices placing the internal passage in fluid communication with said annular cavity.