US 11,725,822 B2
Combustion module for a gas turbo engine with chamber bottom stop
Romain Nicolas Lunel, Moissy-Cramayel (FR); Damien Bonnefoi, Moissy-Cramayel (FR); Christophe Pieussergues, Moissy-Cramayel (FR); Luc Namer, Moissy-Cramayel (FR); Dominique Raulin, Moissy-Cramayel (FR); Dan Ranjiv Joory, Moissy-Cramayel (FR); and Benjamin Frantz Karl Villenave, Moissy-Cramayel (FR)
Assigned to SAFRAN AIRCRAFT ENGINES, Paris (FR)
Filed by SAFRAN AIRCRAFT ENGINES, Paris (FR)
Filed on May 28, 2019, as Appl. No. 16/423,953.
Claims priority of application No. 1854505 (FR), filed on May 28, 2018.
Prior Publication US 2019/0383489 A1, Dec. 19, 2019
Int. Cl. F23R 3/60 (2006.01); F02C 3/06 (2006.01); F02C 7/20 (2006.01); F02C 7/22 (2006.01); F02C 9/16 (2006.01); F23R 3/26 (2006.01); F23R 3/28 (2006.01)
CPC F23R 3/60 (2013.01) [F02C 3/06 (2013.01); F02C 7/20 (2013.01); F02C 7/22 (2013.01); F02C 9/16 (2013.01); F23R 3/26 (2013.01); F23R 3/28 (2013.01); F05D 2220/323 (2013.01); F05D 2260/30 (2013.01)] 17 Claims
OG exemplary drawing
 
1. A combustion module for an aeronautical gas turbine engine, the combustion module having a longitudinal axis and comprising:
an inner housing extending around the longitudinal axis,
an outer housing extending around the longitudinal axis and arranged, radially to the longitudinal axis, outside the inner housing,
an annular combustion chamber:
extending around the longitudinal axis, coaxial with said longitudinal axis,
in which a mixture of air and fuel can flow from upstream to downstream, and
disposed between the inner housing and the outer housing, the combustion chamber comprising an inner revolution wall and an outer revolution wall both extending annularly around the longitudinal axis, both arranged, radially to the longitudinal axis, between the inner housing and the outer housing and both connected upstream to a chamber bottom wall, and
a series of stop pairs disposed annularly around the combustion chamber, each stop pair of the series of stop pairs comprising a first stop part and a second stop part fixed respectively to the outer housing and to the combustion chamber, the first stop part and the second stop part being adapted to come to a substantially axial, in at least some of said stop pairs of the series of stop pairs:
the first stop part being an internal protrusion present on the outer housing, having an axial surface and a radial surface with respect to the longitudinal axis, and
the second stop part having a circumferential outer surface with an axial component parallel to the longitudinal axis, characterized in that an outer protrusion radial to the longitudinal axis, against which the radial surface of the first stop part comes into contact, projects locally, opposite the first stop part, from said circumferential outer surface with said axial component,
the combustion module further comprising at least one fuel injector passing through at least one orifice of the outer housing to bring fuel into the combustion chamber, and
in which, on at least one of said stop pairs:
the first stop part defines a portion of a ring mounted in the at least one orifice of the outer housing, at a location of a portion of the outer housing which is inclined at an angle with respect to the longitudinal axis, and
the second stop part belongs to a locally shouldered plate, fixed on an outer periphery of the combustion chamber.